JP4937158B2 - Gas turbine combustor - Google Patents
Gas turbine combustor Download PDFInfo
- Publication number
- JP4937158B2 JP4937158B2 JP2008038968A JP2008038968A JP4937158B2 JP 4937158 B2 JP4937158 B2 JP 4937158B2 JP 2008038968 A JP2008038968 A JP 2008038968A JP 2008038968 A JP2008038968 A JP 2008038968A JP 4937158 B2 JP4937158 B2 JP 4937158B2
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- passage
- air
- gas turbine
- supply means
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Description
本発明は、ガスタービン燃焼器に関し、特に燃焼筒の基部に接続連通された予混合管によって空気の旋回流を生じさせるとともに、予混合管に設けた燃料供給手段によって燃料を均一に微粒化して噴射することにより、燃焼筒内の基部から離れた位置に火炎を安定的に保持して該基部の熱による耐久性悪化を防止し、同時に燃焼の安定化や低エミッション等をも実現したガスタービン燃焼器の構造に係るものである。 The present invention relates to a gas turbine combustor, and in particular, a swirling flow of air is generated by a premixing pipe connected to a base of a combustion cylinder, and fuel is uniformly atomized by a fuel supply means provided in the premixing pipe. A gas turbine that stably holds a flame at a position away from the base in the combustion cylinder by injecting to prevent deterioration of durability due to the heat of the base, and at the same time realizes stabilization of combustion, low emission, etc. This relates to the structure of the combustor.
図１０は、本願発明者等が本願発明の前に発明したガスタービン燃焼器の断面図である。このガスタービン燃焼器１００は、頂部が閉塞され、下部開口が図示しないガスタービンの排気側に連通された大略円筒形状の燃焼筒１０１と、燃焼筒１０１の頂部中心位置に配置され、その下部開口を燃焼筒１０１内に向けた予混合管１０２と、燃焼筒１０１及び予混合管１０２を包囲するとともに、下部開口が図示しないターボ圧縮機で発生する圧縮空気取入口に連通した空気取入用の外筒体１０３と、外筒体１０３の頂部を貫通して前記予混合管１０２の上部に接続・連通した燃料噴射弁１０４を備えている。そして、予混合管１０２の頂部には、燃料噴射弁１０４を取り囲んで複数のスワーラ（旋回羽根）１０５が同心円状に設けられている。 FIG. 10 is a cross-sectional view of a gas turbine combustor invented by the inventors of the present application before the present invention. The gas turbine combustor 100 is disposed at a central position of the top of the combustion cylinder 101, and a combustion cylinder 101 having a substantially cylindrical shape with a top closed and a lower opening communicating with an exhaust side of a gas turbine (not shown). For the intake of air that surrounds the combustion cylinder 101 and the premixing pipe 102 and the lower opening communicates with a compressed air intake generated by a turbo compressor (not shown). An outer cylinder 103 and a fuel injection valve 104 that penetrates the top of the outer cylinder 103 and is connected to and communicated with the upper portion of the premixing tube 102 are provided. A plurality of swirlers (swirl blades) 105 are provided concentrically around the top of the premixing tube 102 so as to surround the fuel injection valve 104.
燃焼筒１０１は冷却構造を有しており、その頂部には、予混合管１０２の周囲に遮熱プレート１０６が設けられるとともに、所定間隔をおいてその上方に冷却プレート１０７が設けられ、冷却プレート１０７に形成された多数の孔から内部の空間に空気を流入させて遮熱プレート１０６に衝突させてインピンジメント冷却を行うようになっている。また、燃焼筒１０１の周壁には、内部に空気を流入させるための孔が形成されるとともに、周壁の内面には孔に対面してガイド１０８が設けられ、孔から流入した空気を周壁の内面に沿って送り出してフィルム冷却を行うようになっている。 The combustion cylinder 101 has a cooling structure, and a heat shield plate 106 is provided around the premixing tube 102 at the top thereof, and a cooling plate 107 is provided above the cooling plate 107 at a predetermined interval. Impingement cooling is performed by causing air to flow into the internal space from a large number of holes formed in 107 and colliding with the heat shield plate 106. In addition, a hole for allowing air to flow into the inside is formed in the peripheral wall of the combustion cylinder 101, and a guide 108 is provided on the inner surface of the peripheral wall so as to face the hole. The film is cooled along the line.
このガスタービン燃焼器１００の運転時には、図示しないターボ圧縮機から圧縮空気が外筒体１０３に送り込まれ、圧縮空気は予混合管１０２の頂部からスワーラ１０５により旋回されて予混合管１０２に入り、予混合管１０２の内部で空気に強い旋回流を生じさせる。燃料噴射弁１０４から噴射された燃料は、予混合管１０２内でこの強い旋回流により微粒化されて空気と十分に混合されるものとされており、この混合された燃料と空気は予混合管１０２の開口付近、すなわち燃焼筒１０１の頂部で燃焼して火炎Ｆを生じる。燃焼によって生じた高温の燃焼ガスは、燃焼筒１０１の下端の開口からガスタービンに供給されることとなる。 During operation of the gas turbine combustor 100, compressed air is sent from an unillustrated turbo compressor to the outer cylinder 103, and the compressed air is swirled by the swirler 105 from the top of the premixing tube 102 and enters the premixing tube 102. A strong swirl flow is generated in the air inside the premixing tube 102. The fuel injected from the fuel injection valve 104 is atomized by the strong swirling flow in the premixing tube 102 and is sufficiently mixed with air. The mixed fuel and air are mixed with the premixing tube. A flame F is generated by burning near the opening of 102, that is, at the top of the combustion cylinder 101. The high-temperature combustion gas generated by the combustion is supplied to the gas turbine from the opening at the lower end of the combustion cylinder 101.
上述した本願発明者による先の発明は公知のものではなく、従来技術ではないが、この発明において使用された旋回羽根式のスワーラ１０５のように、燃料を燃焼させるために空気に旋回流を発生させるための手段としてのスワーラについては、いくつかの文献で公知となっている。例えば、次の特許文献１及び２には、燃料を燃焼させるバーナーにおいて、空気に旋回流を発生させて燃料と空気を十分に混合させ、燃焼の安定化や低エミッションを実現しうる手段として、スワーラが記載されている。
特に、特許文献１では、バーナー本体の混合領域内に燃料と空気をそれぞれの供給管から直接噴射することにより同領域で混合気を作り、次にこの混合気の流れにスワーラを用いて旋回を与えることにより、バーナー本体の出口の先方に火炎領域を保持しようとする構造である。
In particular, in Patent Document 1, an air-fuel mixture is made in the mixing region of the burner body by directly injecting fuel and air from each supply pipe, and then swirling is performed using a swirler in the flow of the air-fuel mixture. By giving, it is the structure which tries to hold | maintain a flame area | region ahead of the exit of a burner main body.
前述したような空気に強い旋回流を発生させる旋回羽根式のスワーラ１０５を用いたガスタービン燃焼器１００によれば、予混合管１０２が開口している燃焼筒１０１の上部（遮熱プレート１０６の部分）に火炎が接した状態にあるため、冷却プレート１０７による遮熱プレート１０６に対する冷却効果にもかかわらず、遮熱プレート１０６は燃焼ガスに曝されて熱劣化を生じやすく、耐久性の点で問題があった。このように、旋回羽根式のスワーラ１０５を用いたガスタービン燃焼器１００において、火炎が燃焼筒１０１の上部（遮熱プレート１０６の部分）に接した位置にある原因は、本願発明者等の研究によれば、図１０中に矢印で示したように、スワーラ１０５による強い旋回流により燃焼筒１０１の内側に向かう再循環流が燃焼領域に形成されるため、火炎Ｆが燃焼筒１０１の頂部に保炎されてしまうからであると考えられる。 According to the gas turbine combustor 100 using the swirl vane type swirler 105 that generates a strong swirl flow in the air as described above, the upper part of the combustion cylinder 101 (the heat shield plate 106 of the heat shield plate 106) in which the premixing tube 102 is open. Since the flame is in contact with the portion), the heat shield plate 106 is easily exposed to the combustion gas and is subject to thermal deterioration despite the cooling effect of the cooling plate 107 on the heat shield plate 106. There was a problem. As described above, in the gas turbine combustor 100 using the swirl vane type swirler 105, the cause of the flame being in contact with the upper portion of the combustion cylinder 101 (the portion of the heat shield plate 106) is researched by the present inventors. As shown by the arrows in FIG. 10, the recirculation flow toward the inside of the combustion cylinder 101 is formed in the combustion region by the strong swirl flow by the swirler 105, so that the flame F is at the top of the combustion cylinder 101. This is thought to be because the flame is held.
また、本願発明者の先の発明に係るガスタービン燃焼器１００のような旋回羽根式のスワーラ１０５を用いたガスタービン燃焼器によれば、冷却プレート１０７に供給されて遮熱プレート１０６を冷却した冷却空気は、燃焼筒１０１の燃焼領域近傍に流出するので、燃焼筒１０１内の燃焼を阻害する原因になるという問題もあった。 Further, according to the gas turbine combustor using the swirl vane type swirler 105 such as the gas turbine combustor 100 according to the previous invention of the present inventor, the heat shield plate 106 is cooled by being supplied to the cooling plate 107. Since the cooling air flows out in the vicinity of the combustion region of the combustion cylinder 101, there is a problem in that the combustion in the combustion cylinder 101 is hindered.
さらに、このような旋回羽根式のスワーラ１０５を用いたガスタービン燃焼器１００によれば、前述したように、火炎Ｆは、スワーラ１０５による強い旋回流により燃焼領域に形成される再循環流によって保炎されているが、その強い乱流を伴う流れにより、燃焼振動等のような機器の破壊に至る不安定な燃焼挙動を示す場合があった。 Further, according to the gas turbine combustor 100 using the swirl vane type swirler 105 as described above, the flame F is maintained by the recirculation flow formed in the combustion region by the strong swirl flow by the swirler 105. Although it is flamed, the flow accompanied by the strong turbulent flow sometimes shows unstable combustion behavior that leads to destruction of equipment such as combustion vibration.
さらに、このような旋回羽根式のスワーラ１０５を用いた再循環流によるガスタービン燃焼器１００によれば、近年においてはさらに厳しくなった低エミッション化の要求に対して、十分に対応することが困難であるという問題もあった。 Further, according to the gas turbine combustor 100 based on the recirculation flow using the swirl vane type swirler 105, it is difficult to sufficiently respond to the demand for lower emission which has become more severe in recent years. There was also a problem of being.
そこで本発明は、以上の課題を解決するものであり、最も高温に晒されると考えられる遮熱プレートの温度低下を達成することにより燃焼筒等の熱劣化を防止できるため耐久性に優れ、エミッション特性も良好であり、さらには冷却空気による燃焼の阻害がなく、燃焼が安定しているガスタービン燃焼器を提供することを目的としている。 Accordingly, the present invention solves the above-described problems, and is excellent in durability because it can prevent thermal deterioration of the combustion cylinder, etc. by achieving a temperature drop of the heat shield plate that is considered to be exposed to the highest temperature. Another object of the present invention is to provide a gas turbine combustor which has good characteristics, and further has stable combustion without being hindered by cooling air.
請求項１に記載されたガスタービン燃焼器は、タービンに燃焼ガスを供給するために燃料と空気の混合気が燃焼する燃焼筒と、前記燃焼筒に開口して設けられ供給された燃料と空気が混合される予混合管と、前記予混合管に設けられて前記予混合管に燃料を供給する燃料供給手段とを有するガスタービン燃焼器において、
前記燃料供給手段は、環状の燃料通路と、前記燃料通路の接線方向に沿って前記燃料通路に燃料を供給する供給通路と、前記燃料通路に連通し前記予混合管内に燃料を噴射する環状のノズル部と、前記燃料通路及び前記ノズル部の近傍に構成されて前記予混合管内に供給される空気が通過する周状の空気通路とを有し、
前記予混合管は、周壁面の接線方向に沿って内部に空気が流入するように前記周壁面に形成された複数の孔を有することを特徴としている。
The gas turbine combustor according to claim 1 includes a combustion cylinder in which a mixture of fuel and air is combusted to supply combustion gas to the turbine, and fuel and air that are provided by being opened to the combustion cylinder. In a gas turbine combustor having a premixing tube in which the fuel is mixed and a fuel supply means provided in the premixing tube and supplying fuel to the premixing tube,
The fuel supply means includes an annular fuel passage, a supply passage that supplies fuel to the fuel passage along a tangential direction of the fuel passage, and an annular fuel passage that communicates with the fuel passage and injects fuel into the premixing pipe. A nozzle portion, and a circumferential air passage configured in the vicinity of the fuel passage and the nozzle portion, through which air supplied into the premixing tube passes,
The premixing tube has a plurality of holes formed in the peripheral wall surface so that air flows into the inside along a tangential direction of the peripheral wall surface.
請求項２に記載されたガスタービン燃焼器によれば、請求項１記載のガスタービン燃焼器において、
前記燃料供給手段が、前記燃料通路と、前記供給通路と、前記ノズル部と、前記燃料通路と前記ノズル部を連通する供給孔を一体に構成した環状部材であり、
径の異なる複数の前記燃料供給手段が同心状に配置されることにより、少なくとも隣接する前記燃料供給手段の隙間が前記周状の空気通路となることを特徴としている。
According to the gas turbine combustor described in claim 2, in the gas turbine combustor according to claim 1,
The fuel supply means is an annular member configured integrally with the fuel passage, the supply passage, the nozzle portion, and a supply hole communicating the fuel passage and the nozzle portion;
A plurality of the fuel supply means having different diameters are arranged concentrically, so that at least a gap between the adjacent fuel supply means becomes the circumferential air passage.
請求項３に記載されたガスタービン燃焼器によれば、請求項２記載のガスタービン燃焼器において、
最も小径の前記燃料供給手段の中心に起動用圧力噴射ノズルが設けられて、最も小径の前記燃料供給手段と前記起動用圧力噴射ノズルの間の隙間が前記周状の空気通路となり、
最も大径の前記燃料供給手段の外周に環状のガイド部材が設けられて、最も大径の前記燃料供給手段と前記ガイド部材の間の隙間が前記周状の空気通路となることを特徴としている。
According to the gas turbine combustor described in claim 3, the gas turbine combustor according to claim 2,
An activation pressure injection nozzle is provided at the center of the fuel supply means with the smallest diameter, and a gap between the fuel supply means with the smallest diameter and the activation pressure injection nozzle becomes the circumferential air passage,
An annular guide member is provided on the outer periphery of the fuel supply means with the largest diameter, and a gap between the fuel supply means with the largest diameter and the guide member serves as the circumferential air passage. .
請求項１に記載されたガスタービン燃焼器によれば、燃料供給手段では、燃料は供給通路から環状の燃料通路の接線方向に向けて供給されるので、燃料通路の周方向に移動して分布が均一化される。そして、この燃料は環状の燃料通路から環状のノズル部に移行し、ノズル部の全周において燃焼筒に向けて噴射される。噴射された燃料は、周状の空気通路から燃焼筒に向かう空気の流れと混合され、予混合管から燃焼筒に向かう燃焼筒の軸方向に平行な混合気の一様な流れが形成される。他方、予混合管では、周壁面の孔から空気が周壁面の接線方向に沿って内部に流入し、予混合管内に旋回流が形成されるので、燃焼筒の上部には前記一様な流れの周りを旋回する混合気の旋回流が生じる。このように、混合気は、燃焼筒の中心部における旋回のない均一な流れと、その周りを旋回する旋回流の２種類の流れを形成するので、火炎は燃焼筒内において予混合管が開口した燃焼筒の上部から離れた位置に保炎される。従って、予混合管が開口した燃焼筒の上部が炎によって高温に晒されることはなく、燃焼筒の耐久性に問題が生じることはない。特に、芳香族系燃料の場合には輝炎からの輻射熱の影響を緩和することができる。さらに、従来に比べて排気中のＮＯX 成分等を低下させることができ、未燃成分の排出も抑えることができる。さらに、スワーラを必要としないため、従来よりも安定した燃焼が得られ、価格も従来より低く抑えることができる。
なお背景技術で説明した特許文献１、２では、混合領域に燃料管と空気管を接続してそれぞれ燃料と空気を吹き込んで混合気を作り、次にスワーラを用いて混合気に旋回流を形成していたが、上述のように本発明は、この構造とは異なり、環状のノズル部によって燃料を環状に噴射するとともに、これに近接して設けられた環状の空気通路で空気を環状に噴射することにより全体として筒型のパターンで予混合管から燃焼筒に向かう燃焼筒の軸方向に平行な混合気の一様な流れを形成し、さらに予混合管の壁面に接線方向を向けて形成された孔によって該混合気に旋回流を形成し、もって燃焼筒の上部から離れた位置に火炎を確実に保持できるようにした燃焼器の構造である。
According to the gas turbine combustor described in claim 1, since the fuel is supplied from the supply passage toward the tangential direction of the annular fuel passage in the fuel supply means, the fuel is distributed in the circumferential direction of the fuel passage. Is made uniform. And this fuel transfers to a cyclic | annular nozzle part from a cyclic | annular fuel channel | path, and is injected toward a combustion cylinder in the perimeter of a nozzle part. The injected fuel is mixed with the air flow from the circumferential air passage toward the combustion cylinder, and a uniform flow of the air-fuel mixture parallel to the axial direction of the combustion cylinder from the premixing tube to the combustion cylinder is formed. . On the other hand, in the premixing tube, air flows from the holes in the peripheral wall along the tangential direction of the peripheral wall, and a swirling flow is formed in the premixing tube. A swirling flow of the air-fuel mixture that swirls around is generated. In this way, the air-fuel mixture forms two types of flow, a uniform flow without swirling in the center of the combustion cylinder and a swirling flow swirling around the center, so that the premixing tube is opened in the combustion cylinder. The flame is held away from the top of the burned cylinder. Therefore, the upper part of the combustion cylinder in which the premixing tube is opened is not exposed to a high temperature by the flame, and there is no problem in durability of the combustion cylinder. In particular, in the case of an aromatic fuel, the influence of radiant heat from the luminous flame can be mitigated. Furthermore, it is possible to reduce the NO X components and the like in the exhaust gas as compared with the conventional, it can be suppressed emission of unburned. Furthermore, since a swirler is not required, more stable combustion can be obtained than before, and the price can be kept lower than before.
In Patent Documents 1 and 2 described in the background art, a fuel pipe and an air pipe are connected to the mixing region, and fuel and air are blown respectively to create an air-fuel mixture, and then a swirl flow is formed in the air-fuel mixture using a swirler. However, as described above, the present invention, unlike this structure, injects the fuel in an annular shape by the annular nozzle portion and injects the air in the annular air passage provided in the vicinity thereof. As a whole, a uniform flow of the air-fuel mixture parallel to the axial direction of the combustion cylinder from the premixing pipe to the combustion cylinder is formed in a cylindrical pattern, and further, the tangential direction is formed toward the wall surface of the premixing pipe This is a structure of a combustor in which a swirl flow is formed in the air-fuel mixture by the formed holes so that the flame can be reliably held at a position away from the upper portion of the combustion cylinder.
請求項２に記載されたガスタービン燃焼器によれば、請求項１記載のガスタービン燃焼器の効果において、さらに、燃料供給手段において径の異なる複数の環状部材を同心状に配置することにより、隣接する環状部材の周状のノズル部の隙間を周状の空気通路とすることができ、隣接する環状のノズル部の全周から燃焼筒に向けて噴射される燃料を、その間を吹き抜ける空気の流れによってより効果的に微粒化することができる。 According to the gas turbine combustor described in claim 2, in the effect of the gas turbine combustor according to claim 1, further, by disposing a plurality of annular members having different diameters concentrically in the fuel supply unit, A gap between the circumferential nozzle portions of the adjacent annular members can be used as a circumferential air passage, and the fuel injected from the entire circumference of the adjacent annular nozzle portions toward the combustion cylinder can be blown through the air. It can be atomized more effectively by the flow.
請求項３に記載されたガスタービン燃焼器によれば、請求項２記載のガスタービン燃焼器における効果において、さらに、最も小径の燃料供給手段と起動用圧力噴射ノズルの間と、最も大径の燃料供給手段とガイド部材の間を、共に周状の空気通路として空気を噴出すことにより、環状のノズル部の全周から燃焼筒に向けて噴射される燃料を、さらに効果的に微粒化することができる。
なお、背景技術で説明した特許文献１、２において適用される燃料はガス化されたものであるが、本発明では、これとは異なり、上述したように燃料と空気を特殊な環状の態様で噴射して燃料を確実に微粒化し、混合気とすることができる燃料供給手段を備えているので、燃料としては液体燃料にも対応することができる。
According to the gas turbine combustor described in claim 3, in the effect of the gas turbine combustor described in claim 2, further, between the smallest diameter fuel supply means and the startup pressure injection nozzle, the largest diameter By spraying air between the fuel supply means and the guide member as a circumferential air passage, the fuel injected from the entire circumference of the annular nozzle portion toward the combustion cylinder is more effectively atomized. be able to.
Although the fuel applied in Patent Documents 1 and 2 described in the background art is gasified, in the present invention, unlike this, the fuel and air are combined in a special annular form as described above. Since the fuel supply means is provided that can inject fuel and atomize the fuel with certainty to obtain an air-fuel mixture, liquid fuel can be used as the fuel.
以下本発明の最良の実施の形態につき、添付図面を参照して詳細に説明する。
図１〜図９は本発明の実施形態を示し、図１は本実施形態のガスタービン燃焼器の縦断面図、図２は本実施形態における燃料供給手段の拡大縦断面図、図３（ａ）は図２のＣ−Ｃ切断線における横断面図、図３（ｂ）は同図（ａ）の燃料通路の部分拡大図、図４は図１のＢ−Ｂ切断線における拡大横断面図、図５は本実施形態のガスタービン燃焼器において予混合管の周壁面の孔を塞いだ場合の混合気の流れと火炎の位置を示す縦断面図、図６は本実施形態のガスタービン燃焼器において予混合管の孔による旋回流がない場合の燃料供給手段のノズル部における均一な液膜となった燃料噴射状態を示す図、図７は本実施形態のガスタービン燃焼器において予混合管の孔による旋回流がある場合の燃料供給手段のノズル部における均一な微粒化が達成された燃料噴射状態を示す図、図８はガスタービン燃焼器における全体当量比とＮＯX 排出量との関係を本実施形態と従来例とで比較して示す図、図９はガスタービン燃焼器における全体当量比とＣＯ排出量との関係を本実施形態と従来例とで比較して示す図である。
The best mode for carrying out the present invention will be described below in detail with reference to the accompanying drawings.
1 to 9 show an embodiment of the present invention, FIG. 1 is a longitudinal sectional view of a gas turbine combustor of the present embodiment, FIG. 2 is an enlarged longitudinal sectional view of a fuel supply means in the present embodiment, and FIG. ) Is a cross-sectional view taken along the line CC of FIG. 2, FIG. 3B is a partially enlarged view of the fuel passage of FIG. 4A, and FIG. 4 is an enlarged cross-sectional view taken along the line BB of FIG. FIG. 5 is a longitudinal sectional view showing the flow of the air-fuel mixture and the position of the flame when the hole in the peripheral wall surface of the premixing tube is closed in the gas turbine combustor of the present embodiment, and FIG. 6 is the gas turbine combustion of the present embodiment. FIG. 7 is a diagram showing a fuel injection state in which a uniform liquid film is formed in the nozzle portion of the fuel supply means when there is no swirling flow due to the hole of the premixing tube in the combustor. FIG. Uniform atomization in the nozzle of the fuel supply means in the presence of swirling flow due to holes Shows the achieved fuel injection state, FIG. 8 is a diagram showing comparison between the present embodiment and the conventional example the relation between the overall equivalence ratio and NO X emissions in a gas turbine combustor, 9 gas turbine combustion It is a figure which compares and shows the relationship between the total equivalent ratio in a vessel, and CO discharge | emission amount by this embodiment and a prior art example.
まず、本例のガスタービン燃焼器１の構造を説明する。
図１に示すように、このガスタービン燃焼器１は、頂部が閉塞され、下部開口が図示しないガスタービンの排気側に連通された大略円筒形状の燃焼筒２と、燃焼筒２の頂部中心位置に同軸で配置され、その下部開口を燃焼筒２に連通させた燃焼筒２より小径の予混合管３と、燃焼筒２及び予混合管３を包囲するとともに、下部開口が図示しないターボ圧縮機で発生する圧縮空気取入口に連通した空気取入用の外筒体４と、予混合管３の頂部に設けられ、燃料供給系の一部が外筒体４の頂部を貫通して外部に導かれている燃料供給手段５を備えている。
First, the structure of the gas turbine combustor 1 of this example will be described.
As shown in FIG. 1, the gas turbine combustor 1 includes a generally cylindrical combustion cylinder 2 whose top is closed and whose lower opening communicates with an exhaust side of a gas turbine (not shown), and the center position of the top of the combustion cylinder 2. The premixing pipe 3 having a diameter smaller than that of the combustion cylinder 2 whose lower opening communicates with the combustion cylinder 2, the combustion cylinder 2 and the premixing pipe 3 are surrounded, and the lower opening has a turbo compressor not shown. Is provided at the top of the premixing tube 3, and a part of the fuel supply system passes through the top of the outer cylinder 4 to the outside. A fuel supply means 5 is provided.
なお、燃焼筒２は図１０に示した背景技術のガスタービン燃焼器１００と同様、冷却構造を有している。図１中、拡大図Ｙに示すように、燃焼筒２の頂部には、予混合管３の周囲に遮熱プレート６が設けられるとともに、所定間隔をおいてその上方に冷却プレート７が設けられ、冷却プレート７に形成された多数の孔８から矢印で示すように内部の空間に空気を流入させて遮熱プレート６に衝突させ、インピンジメント冷却を行うようになっている。また、図１中、拡大図Ｚに示すように、燃焼筒２の周壁には、内部に空気を流入させるための孔９が形成されるとともに、周壁の内面には孔９に対面してガイド１０が設けられ、矢印で示すように孔９から流入した空気を周壁の内面沿いに送り出してフィルム冷却を行うようになっている。 The combustion cylinder 2 has a cooling structure, similar to the gas turbine combustor 100 of the background art shown in FIG. As shown in the enlarged view Y in FIG. 1, a heat shield plate 6 is provided around the premixing tube 3 at the top of the combustion cylinder 2, and a cooling plate 7 is provided above it at a predetermined interval. The impingement cooling is performed by allowing air to flow into the internal space from the numerous holes 8 formed in the cooling plate 7 and collide with the heat shield plate 6 as indicated by arrows. In addition, as shown in an enlarged view Z in FIG. 1, a hole 9 for allowing air to flow inside is formed in the peripheral wall of the combustion cylinder 2, and a guide is provided on the inner surface of the peripheral wall so as to face the hole 9. 10 is provided, and as shown by the arrow, the air flowing from the hole 9 is sent out along the inner surface of the peripheral wall to cool the film.
本例のガスタービン燃焼器１の燃料供給手段５は、背景技術のものと異なり、図２の中心線から右側に図示した構造例のように、スワーラを有しない構造を基本タイプとする（スワーラ無しの場合）。図２又は図３に示すように、燃料供給手段５は、最も大径である環状のガイド部材１１と、燃料噴射構造を内蔵した大径及び小径の２つの環状部材１２，１３とを周状の隙間を置いて同心円状に配置し、さらに小径の環状部材１３の中心の孔には周状の隙間を置いて起動用圧力噴射ノズル１４を設け、同心円の径方向に沿って配置した複数本のステー１５によってこれらガイド部材１１、２つの環状部材１２，１３及び起動用圧力噴射ノズル１４を互いに連結して一体に構成したものである。 The fuel supply means 5 of the gas turbine combustor 1 of the present example is different from that of the background art, and a structure having no swirler as a basic type as in the structure example illustrated on the right side from the center line in FIG. If no). As shown in FIG. 2 or FIG. 3, the fuel supply means 5 has an annular guide member 11 having the largest diameter and two annular members 12 and 13 having a large diameter and a small diameter having a built-in fuel injection structure. Are arranged concentrically with a gap between them, and a pressure injection nozzle 14 for activation is provided with a circumferential gap in the center hole of the small-diameter annular member 13, and a plurality of nozzles arranged along the radial direction of the concentric circles. The guide member 11, the two annular members 12 and 13, and the starting pressure injection nozzle 14 are connected to each other by the stay 15 and are integrally configured.
２つの環状部材１２，１３の構造は寸法等の具体的な寸法等の設計事項を除けば略同一である。すなわち、図２又は図３に示すように、環状部材１２，１３は、その上部に密閉された環状の燃料通路１６（１６ａ，１６ｂ）を有している。この燃料通路１６には、燃料通路１６の接線方向に沿って内部に燃料を供給する供給通路１７（１７ａ，１７ｂ）が接続連通されており、燃料通路１６の周方向について燃料を均一に分布させることができる。各燃料通路１６にそれぞれ接続された各供給通路１７は、それぞれ環状部材１２，１３の外部において上方に向けて屈曲され、外筒体４の頂部のフランジ１８を貫通して図示しない外部の燃料供給源に導かれている。 The structures of the two annular members 12 and 13 are substantially the same except for design matters such as specific dimensions such as dimensions. That is, as shown in FIG. 2 or 3, the annular members 12 and 13 have an annular fuel passage 16 (16 a and 16 b) sealed at the upper part thereof. A supply passage 17 (17 a, 17 b) for supplying fuel to the inside of the fuel passage 16 along the tangential direction of the fuel passage 16 is connected to communicate with the fuel passage 16 in the circumferential direction of the fuel passage 16. be able to. Each supply passage 17 connected to each fuel passage 16 is bent upwards outside the annular members 12 and 13 and penetrates through the flange 18 at the top of the outer cylinder 4 to supply an external fuel supply (not shown). Led to the source.
図２又は図３に示すように、各環状部材１２，１３の下部には、後述する予混合管３内に燃料を噴射するために、環状に連続して開口したノズル部１９（１９ａ，１９ｂ）が形成されている。環状部材１２，１３の上側にある前記燃料通路１６ａ，１６ｂと、その下側にある周状に連続したこのノズル部１９ａ，１９ｂとは、周方向について均等に分布して形成された多数の供給孔２０によって連通している。この供給孔２０は、図２及び図３に示すように、平面視においては概ね燃料通路１６及びノズル部１９の周方向（接線方向）に沿った方向に向けられて全周にわたって設けられており、軸線方向に対しては所定の角度で所定方向に傾斜した姿勢で形成されており、燃料通路１６内で均一に分布した燃料を、周方向について旋回速度を与えてノズル部１９に送り込むことができる。なお、本例の供給孔２０は、一例ではあるが燃料通路１６又はノズル部１９の１周（３６０°）について等配分に形成されている。 As shown in FIG. 2 or FIG. 3, nozzle portions 19 (19 a, 19 b) that continuously open in an annular shape are provided below the annular members 12, 13 in order to inject fuel into a premixing tube 3 described later. ) Is formed. The fuel passages 16a and 16b on the upper side of the annular members 12 and 13 and the nozzle portions 19a and 19b which are continuously arranged on the lower side of the fuel passages 16a and 16b are provided with a large number of supplies distributed evenly in the circumferential direction. The holes 20 communicate with each other. As shown in FIGS. 2 and 3, the supply hole 20 is provided over the entire circumference in a direction along the circumferential direction (tangential direction) of the fuel passage 16 and the nozzle portion 19 in plan view. The fuel is distributed in a predetermined direction at a predetermined angle with respect to the axial direction, and the fuel that is uniformly distributed in the fuel passage 16 is fed to the nozzle portion 19 with a turning speed in the circumferential direction. it can. In addition, although the supply hole 20 of this example is an example, it is formed in equal distribution about 1 round (360 degrees) of the fuel channel 16 or the nozzle part 19. FIG.
図２又は図３に示すように、前記ノズル部１９の開口部には、外側の壁体が長く下方に突出するとともに、内方に向けて縮径するように傾斜したフィルマ２１が設けられており、ノズル部１９から噴射される燃料の液膜を形成するようになっている。 As shown in FIG. 2 or 3, the opening of the nozzle portion 19 is provided with a film 21 that is inclined so that the outer wall protrudes downward long and decreases inward. Thus, a liquid film of fuel injected from the nozzle portion 19 is formed.
図２又は図３に示すように、本例のガスタービン燃焼器１の燃料供給手段５では外側から環状のガイド部材１１と、大径の環状部材１２と、小径の環状部材１３と、起動用圧力噴射ノズル１４をそれぞれ間隔をおいて同心状に配置したので、各部材の間には合計３つの周状の隙間が構成されており、この隙間が、外筒体４内に取り入れられた空気が予混合管３内に供給される際に通過する周状の空気通路２２（２２ａ，２２ｂ，２２ｃ）となっている。 As shown in FIG. 2 or FIG. 3, the fuel supply means 5 of the gas turbine combustor 1 of this example has an annular guide member 11, a large-diameter annular member 12, a small-diameter annular member 13, and a starter from the outside. Since the pressure injection nozzles 14 are arranged concentrically at intervals, a total of three circumferential gaps are formed between the members, and these gaps are the air taken into the outer cylinder 4. Is a circumferential air passage 22 (22a, 22b, 22c) that passes when the air is supplied into the premixing tube 3.
本例のガスタービン燃焼器１の燃料供給手段５は、以上のように構成されてそれぞれ単独で燃料を均一に噴射できる環状部材１２，１３を、径が異なるように２系統以上（図２中では、一例としてＭ１，Ｍ２の２系統）配しており、各系統ごとに供給通路１７ａ，１７ｂが設けられて燃料の供給を行えるようになっているので、１系統の場合に比べて噴射時の燃料分布をより一層均一化させて噴射することができる。また両環状部材１２，１３は、いずれも周状の空気通路２２ａ，２２ｂ，２２ｃで挟まれた構造になっているので、均一に噴射された燃料が空気の流れによって微粒化されやすい。 The fuel supply means 5 of the gas turbine combustor 1 of the present example is configured as described above, and each of the annular members 12 and 13 capable of uniformly injecting fuel independently is divided into two or more systems with different diameters (in FIG. 2). Then, as an example, two systems M1 and M2) are arranged, and supply passages 17a and 17b are provided for each system so that fuel can be supplied. The fuel distribution can be made more uniform and injected. Further, since both the annular members 12 and 13 are sandwiched between the circumferential air passages 22a, 22b and 22c, the uniformly injected fuel is easily atomized by the air flow.
次に、図１（特に図１中、拡大図Ｙ参照）及び図４に示すように、本例のガスタービン燃焼器１の予混合管３は、背景技術のものと異なり、その周壁面に複数の孔２５が形成されている。この孔２５は横長の楕円形であり、その軸方向は、予混合管３の周壁面の接線方向に沿って内部に空気が流入するように構成されている。従って、外筒体４内に取り入れられた空気は、これらの孔２５から予混合管３内に供給されて予混合管３内に周方向の旋回流を形成する。なお、図１では、予混合管３の軸方向（縦方向）の３つの領域に分かれてそれぞれ多数の孔２５が形成されているように図示されているが、孔２５の形成方向が予混合管３の内部に旋回流を形成するようなものであることを除き、その他の孔２５の条件、例えば孔２５の個数、配置、径等は、本例のガスタービン燃焼器１の種々の条件に応じて定められるものである。 Next, as shown in FIG. 1 (particularly, in FIG. 1, see enlarged view Y) and FIG. 4, the premixing tube 3 of the gas turbine combustor 1 of the present example is different from that of the background art in its peripheral wall surface. A plurality of holes 25 are formed. The hole 25 has a horizontally long oval shape, and its axial direction is configured such that air flows into the inside along the tangential direction of the peripheral wall surface of the premixing tube 3. Therefore, the air taken into the outer cylinder 4 is supplied into the premixing tube 3 from these holes 25 to form a circumferential swirling flow in the premixing tube 3. In FIG. 1, the premixing tube 3 is divided into three regions in the axial direction (longitudinal direction) so that a large number of holes 25 are formed. Except for the fact that a swirl flow is formed inside the tube 3, the conditions of the other holes 25, such as the number, arrangement, and diameter of the holes 25, are various conditions of the gas turbine combustor 1 of this example. It is determined according to.
次に、本例のガスタービン燃焼器１の作用効果を説明する。
本例のガスタービン燃焼器１の運転時には、図示しないターボ圧縮機から圧縮空気が外筒体４に送り込まれ、圧縮空気は予混合管３の頂部に設けられた燃料供給手段５の空気通路２２から予混合管３内に入る。起動時には燃料供給手段５の起動用圧力噴射ノズル１４から燃料が噴射されて空気通路２２からの空気と混合され、この混合気に図示しない点火装置が点火して燃焼が始まる。
Next, the effect of the gas turbine combustor 1 of this example is demonstrated.
During operation of the gas turbine combustor 1 of this example, compressed air is sent from the turbo compressor (not shown) to the outer cylinder 4, and the compressed air is supplied to the air passage 22 of the fuel supply means 5 provided at the top of the premixing pipe 3. Enters the premixing tube 3. At the time of start-up, fuel is injected from the start-up pressure injection nozzle 14 of the fuel supply means 5 and mixed with the air from the air passage 22, and an ignition device (not shown) ignites the air-fuel mixture to start combustion.
燃料供給手段５の環状部材１２，１３では、燃料が供給通路１７ａ，１７ｂから送られて燃料通路１６ａ，１６ｂに対して接線方向に沿って送り込まれるので、燃料は燃料通路１６ａ，１６ｂ内の周方向に均一に分布する。さらに燃料は、燃料通路１６ａ，１６ｂの周方向に均一な分布で形成された供給孔２０を通ることにより、所要の旋回速度を与えられてノズル部１９ａ，１９ｂ内に送られ、環状のノズル部１９ａ，１９ｂからフィルマ２１を経て吹き出される。環状のノズル部１９ａ，１９ｂは内側及び外側が周状の空気通路２２ａ，２２ｂ，２２ｃに囲まれているので、２つのノズル部１９ａ，１９ｂからそれぞれ均一に吹き出された燃料は、空気通路２２ａ，２２ｂ，２２ｃからの空気流により微粒化されて均一な混合気となり、予混合管３から燃焼筒２内に吹き出され、図１中に白抜きの矢印で示すように燃焼筒２内に軸方向の一様な混合気の流れを作る。 In the annular members 12 and 13 of the fuel supply means 5, the fuel is sent from the supply passages 17a and 17b and sent along the tangential direction with respect to the fuel passages 16a and 16b. Evenly distributed in the direction. Further, the fuel passes through the supply holes 20 formed in a uniform distribution in the circumferential direction of the fuel passages 16a and 16b, and is sent to the nozzle portions 19a and 19b at a required swirl speed. It is blown out from 19a, 19b via filma 21. Since the annular nozzle portions 19a and 19b are surrounded by the air passages 22a, 22b and 22c having the inner side and the outer side, the fuel uniformly blown out from the two nozzle portions 19a and 19b respectively flows into the air passages 22a and 22b. The mixture is atomized by the air flow from 22b and 22c to become a uniform air-fuel mixture, blown into the combustion cylinder 2 from the premixing pipe 3, and axially into the combustion cylinder 2 as shown by the white arrow in FIG. Make a uniform mixture flow.
他方、この予混合管３内には、周壁面に形成された複数の孔２５から接線方向に空気が吹き込まれており、この空気の流れが、図１中に実線の矢印で示すように、燃焼筒２内の予混合管３の開口付近に、前述した軸方向の一様な混合気の流れを取り巻くような混合気の旋回流を形成している。 On the other hand, air is blown into the premixing tube 3 in a tangential direction from a plurality of holes 25 formed in the peripheral wall surface, and this air flow is indicated by solid arrows in FIG. In the vicinity of the opening of the premixing tube 3 in the combustion cylinder 2, a swirling flow of the air-fuel mixture surrounding the above-described uniform air-fuel mixture in the axial direction is formed.
図５は、本実施形態のガスタービン燃焼器１において、予混合管３の外側に予混合管３の外径よりも内径が若干大きく、高さが同程度である閉止筒体３０を配置し、予混合管３の壁体を覆って周壁面の孔２５を塞いだ状態を示しており、さらにこの状態で燃料を噴射して燃焼させた場合における混合気の流れと火炎の位置を示している。図６は、図５に示したように、閉止筒体３０で予混合管３の孔２５を塞いで予混合管３内に空気の旋回流が発生しない状態とし、燃料供給手段５から燃料を噴射した時のノズル部１９付近における燃料噴射状態の写真を示している。図６に示すように、ノズル部１９から噴射される燃料は均一な液膜となっているが、微粒化はされておらず、均一な混合気にはなっていない。このような状態で燃焼を行うと、図５中に実線の矢印で示すように、混合気は燃焼筒２内において予混合管３の開口の周縁部において逆流域を形成し、このために火炎Ｆは燃焼筒２の頂部（予混合管３が開口している付近）に保炎されてしまい、燃焼筒２の頂部が火炎Ｆに直接晒されてしまう。図５では、予混合管３の周壁面には軸方向に異なる３つの領域にそれぞれ複数の孔２５の群が形成されているが、軸方向の長さ（高さ）の異なる３種類の閉止筒体３０を順次用いて３つの群（領域）の孔２５を閉止する実験を行なった結果、すべての孔２５を閉止した時に火炎が燃焼筒２の頂部に付着した状態となった。 FIG. 5 shows that in the gas turbine combustor 1 of the present embodiment, a closed cylinder 30 having an inner diameter slightly larger than the outer diameter of the premixing tube 3 and having the same height is disposed outside the premixing tube 3. 2 shows the state in which the wall 25 of the premixing tube 3 is covered and the hole 25 in the peripheral wall surface is closed, and the flow of the air-fuel mixture and the position of the flame when the fuel is injected and burned in this state are shown. Yes. 6, as shown in FIG. 5, the closed cylinder 30 closes the hole 25 of the premixing tube 3 so that no swirl of air is generated in the premixing tube 3, and fuel is supplied from the fuel supply means 5. The photograph of the fuel injection state in the vicinity of the nozzle portion 19 when injected is shown. As shown in FIG. 6, although the fuel injected from the nozzle part 19 is a uniform liquid film, it is not atomized and does not form a uniform gas mixture. When combustion is performed in such a state, as shown by a solid arrow in FIG. 5, the air-fuel mixture forms a backflow region in the peripheral portion of the opening of the premixing tube 3 in the combustion cylinder 2. F is held at the top of the combustion tube 2 (near the premixing tube 3 is open), and the top of the combustion tube 2 is directly exposed to the flame F. In FIG. 5, a group of a plurality of holes 25 is formed in three axially different regions on the peripheral wall surface of the premixing tube 3, but there are three types of closures having different axial lengths (heights). As a result of conducting an experiment in which the holes 30 of the three groups (regions) were closed using the cylindrical body 30 in sequence, the flame was attached to the top of the combustion cylinder 2 when all the holes 25 were closed.
図７は本実施形態のガスタービン燃焼器１において予混合管３の孔２５によって予混合管３の内部に旋回流が生じている状態とし、燃料供給手段５から燃料を噴射した時のノズル部１９付近における燃料噴射状態の写真を示している。図７に示すように、この燃料供給手段５のノズル部１９では、均一に噴射された燃料が空気の旋回流と混合して微粒化が達成されている。このように、予混合管３の内部に旋回流を形成するための孔２５を予混合管３の周壁に設けることは、図１に示すように燃焼筒２の頂部から離れた位置に火炎Ｆを保持する効果を得るための必須の条件である。軸方向の長さ（高さ）の異なる３種類の閉止筒体３０を順次用いて予混合管３の３つの領域の孔２５を閉止する前記実験の結果によれば、予混合管３の壁体の高さ方向のいずれかの部分の全周に旋回流を生じる孔２５が形成されていれば、火炎Ｆは燃焼筒２の頂部から離れた下方の位置に保持され、遮熱プレート６が過熱する問題は解決された。 FIG. 7 shows a state where a swirling flow is generated inside the premixing tube 3 by the hole 25 of the premixing tube 3 in the gas turbine combustor 1 of the present embodiment, and the nozzle portion when the fuel is injected from the fuel supply means 5. The photograph of the fuel injection state in the vicinity of 19 is shown. As shown in FIG. 7, in the nozzle part 19 of this fuel supply means 5, the atomized fuel is mixed with the swirling flow of air to achieve atomization. Thus, providing the hole 25 for forming the swirl flow in the premixing tube 3 in the peripheral wall of the premixing tube 3 is possible because the flame F is located away from the top of the combustion cylinder 2 as shown in FIG. This is an indispensable condition for obtaining the effect of maintaining the. According to the result of the above-described experiment in which three types of closed cylinders 30 having different lengths (heights) in the axial direction are sequentially used to close the holes 25 in the three regions of the premixing tube 3, the wall of the premixing tube 3 is If the hole 25 which produces a swirl flow is formed in the whole circumference of any part in the height direction of the body, the flame F is held at a lower position away from the top of the combustion cylinder 2, and the heat shield plate 6 is The problem of overheating was solved.
このように、本例のガスタービン燃焼器１では、混合気は、燃焼筒２の中心部における旋回のない均一な軸方向の流れと、その周りを旋回する旋回流の２種類の流れを形成するので、燃焼筒２内で混合気の流れに乱れが発生することはなく、火炎Ｆは燃焼筒２内において予混合管３が開口した燃焼筒２の上部から離れた位置に安定した状態で保炎される。従って、予混合管３が開口した燃焼筒２の上部が火炎Ｆによって高温に晒されることはなく、燃焼筒２の頂部（遮熱プレート６等）の温度を下げ、製品の耐久性を向上させることができる。 As described above, in the gas turbine combustor 1 of the present example, the air-fuel mixture forms two types of flows, a uniform axial flow without swirling in the center of the combustion cylinder 2 and a swirling flow swirling around the uniform axial flow. Therefore, the flow of the air-fuel mixture is not disturbed in the combustion cylinder 2, and the flame F is in a stable state at a position away from the upper part of the combustion cylinder 2 where the premixing tube 3 is opened in the combustion cylinder 2. The flame is held. Therefore, the upper part of the combustion cylinder 2 in which the premixing tube 3 is opened is not exposed to a high temperature by the flame F, and the temperature of the top part (such as the heat shield plate 6) of the combustion cylinder 2 is lowered to improve the durability of the product. be able to.
特に、芳香族系燃料が燃焼する場合には、燃料が分解して生じた微細な炭素粒が発光する輝炎を生じるが、この輝炎は強い輻射熱を伴うため燃焼筒２の遮熱プレート６にとって大きな熱負荷となる。しかし、本例によれば遮熱プレート６から離れた位置に保炎することができるので、輝炎からの輻射熱の影響を大幅に緩和することができる。 In particular, when an aromatic fuel burns, a fine flame is generated in which fine carbon particles generated by the decomposition of the fuel emit light. Since this bright flame is accompanied by strong radiant heat, the heat shield plate 6 of the combustion cylinder 2 is produced. This is a great heat load. However, according to this example, since the flame can be held at a position away from the heat shield plate 6, the influence of the radiant heat from the bright flame can be greatly reduced.
従って、燃焼筒２の頂部（遮熱プレート６等）から離れた位置に安定して保炎できる本例のガスタービン燃焼器１によれば、輝炎が生じるような燃料でも使用することができる。輝炎の強さは、Ｃ／Ｈ比が大きいほど強くなり、灯油が約５．５であるのに対し、例えばトルエンは１０．５、キシレンは９．６であるように、芳香族Ｃn Ｈ2n-6はＣ／Ｈ比が大きく燃焼時には強い輻射熱を伴う輝炎が発生するが、本例のガスタービン燃焼器１であれば、このような芳香族系の燃料でも安全に使用することができる。 Therefore, according to the gas turbine combustor 1 of this example that can stably hold the flame at a position away from the top of the combustion cylinder 2 (the heat shield plate 6 or the like), it is possible to use even fuel that generates a bright flame. . The intensity of the luminous flame increases as the C / H ratio increases, and the kerosene is about 5.5, whereas the aromatic C n is 10.5 for toluene and 9.6 for xylene, for example. H 2n-6 has a large C / H ratio and generates a bright flame with strong radiant heat during combustion. However, with the gas turbine combustor 1 of this example, such an aromatic fuel can be used safely. Can do.
さらに、本例のガスタービン燃焼器１によれば、従来に比べて排気中のＮＯX 成分やＣＯ成分等を低下させることができ、未燃成分の排出も抑えることができる。
図８は、大気圧燃焼試験で排出された燃焼ガスにおける全体当量比とＮＯX 濃度との関係を、本例のガスタービン燃焼器１（実施形態１は灯油を燃焼、実施形態２は溶剤を燃焼）と従来例（スワーラを用いたタイプ）とで比較して示す図である。ガスタービン燃焼器の運転ポイントは通常横軸の全体当量比で０．２５付近であり、このポイントで比較すると、この図から理解されるように、本実施形態のガスタービン燃焼器１は、従来例に比べて排出されるＮＯX 濃度が低い。
Furthermore, according to the gas turbine combustor 1 of this example, the NO x component, the CO component, and the like in the exhaust can be reduced as compared with the conventional case, and the discharge of unburned components can also be suppressed.
8, the relationship between the overall equivalence ratio and NO X concentrations in combustion gas discharge at atmospheric pressure combustion test, the gas turbine combustor 1 of the present embodiment (Embodiment 1 the combustion of kerosene, the second embodiment the solvent It is a figure which compares and shows with a conventional example (type using a swirler). The operation point of the gas turbine combustor is usually around 0.25 in terms of the total equivalent ratio of the horizontal axis. As compared with this point, as understood from this figure, the gas turbine combustor 1 of the present embodiment is a conventional one. low NO X concentration discharged in comparison with the examples.
図９は、大気圧燃焼試験で排出された燃焼ガスにおける全体当量比とＣＯ濃度との関係を、本例のガスタービン燃焼器１（実施形態１は灯油を燃焼、実施形態２は溶剤を燃焼）と従来例（スワーラを用いたタイプ）とで比較して示す図である。ガスタービン燃焼器の運転ポイント（全体当量比で０．２５付近）で比較すると、この図から理解されるように、本実施形態のガスタービン燃焼器１は、排出されるＣＯ濃度が従来例と同等以下である。 FIG. 9 shows the relationship between the total equivalence ratio and the CO concentration in the combustion gas discharged in the atmospheric pressure combustion test. In this example, the gas turbine combustor 1 (the first embodiment burns kerosene and the second embodiment burns solvent). ) And a conventional example (a type using a swirler). When compared at the operation point of the gas turbine combustor (total equivalence ratio is around 0.25), as understood from this figure, the gas turbine combustor 1 of the present embodiment has a CO concentration discharged from the conventional example. Less than or equal to
図８及び図９に結果を示した実験において、実施形態２で使用した溶剤は芳香族燃料であるトルエンを主成分とするものであり、この実験結果から理解されるように、前述した如く本例のガスタービン燃焼器１によれば、燃焼器の遮熱プレート６の過熱防止の点だけでなく、エミッション低下の効果の点においても、芳香族系の燃料を使用できることが明らかになった。 In the experiments whose results are shown in FIGS. 8 and 9, the solvent used in the second embodiment is mainly composed of aromatic fuel, toluene. According to the gas turbine combustor 1 of the example, it has become clear that aromatic fuel can be used not only in terms of preventing overheating of the heat shield plate 6 of the combustor but also in terms of the effect of reducing emissions.
さらに、本例のガスタービン燃焼器１によれば、スワーラを必要としないため前述したように従来よりも安定した燃焼が得られ、価格も従来より低く抑えることができる。 Furthermore, according to the gas turbine combustor 1 of this example, since a swirler is not required, as described above, more stable combustion can be obtained and the price can be kept lower than before.
次に、本実施形態の変形例について説明する。
本例では、図２に示すように、外側から環状のガイド部材１１と、大径の環状部材１２と、小径の環状部材１３と、起動用圧力噴射ノズル１４をそれぞれ間隔をおいて同心状に配置することにより、各部材の間に合計３つの周状の空気通路２２（２２ａ，２２ｂ，２２ｃ）を構成し、外筒体４内に取り入れられた空気が予混合管３内に供給される際に通過するように構成している。
Next, a modification of this embodiment will be described.
In this example, as shown in FIG. 2, the annular guide member 11, the large-diameter annular member 12, the small-diameter annular member 13, and the starting pressure injection nozzle 14 are concentrically spaced from each other at intervals. By arranging them, a total of three circumferential air passages 22 (22a, 22b, 22c) are formed between the members, and the air taken into the outer cylinder 4 is supplied into the premixing tube 3. It is configured to pass through.
しかしながら、図２の中心線から左側に図示した構造例のように、前記空気通路２２（２２ａ，２２ｂ，２２ｃ）を構成する隙間の部分に、径の異なる旋回羽根を備えたスワーラ２６，２７，２８をそれぞれ設けることとしてもよい（スワーラ有りの場合）。 However, as in the structural example illustrated on the left side from the center line of FIG. 2, swirlers 26, 27, which are provided with swirl vanes having different diameters in the gaps constituting the air passage 22 (22a, 22b, 22c). 28 may be provided (when there is a swirler).
このように、スワーラ２６，２７，２８を設けることにより、予混合管３内に供給される空気は、環状に軸方向の勢いを与えられるとともに、旋回も与えられて筒状のパターンで噴射されるので、スワーラが無い場合に比べて環状のノズル部から環状に噴射される燃料と一層均一に混合される効果があり、また筒型のパターンで予混合管から燃焼筒に向かう燃焼筒の軸方向に平行な混合気の一様な流れを形成できる点では同様の効果が得られる。従って、この変形例によれば、予混合管の壁面に接線方向を向けて形成された孔によって該混合気にさらに強い旋回流を形成することができるので、燃焼筒の上部から離れた位置に火炎をより確実に保持できる効果が得られる。 In this way, by providing the swirlers 26, 27, 28, the air supplied into the premixing tube 3 is given an axial momentum in a ring shape, and swirled, and is injected in a cylindrical pattern. Therefore, compared with the case where there is no swirler, there is an effect that the fuel injected in an annular shape from the annular nozzle portion is more evenly mixed, and the axis of the combustion cylinder heading from the premixing tube to the combustion cylinder in a cylindrical pattern A similar effect is obtained in that a uniform flow of the air-fuel mixture parallel to the direction can be formed. Therefore, according to this modified example, a stronger swirl flow can be formed in the air-fuel mixture by the holes formed in the tangential direction to the wall surface of the premixing tube, so that it can be separated from the upper portion of the combustion cylinder. The effect that the flame can be held more reliably is obtained.
さらに、図２の中心線の左側に図示した前述した変形例では、空気通路２２（２２ａ，２２ｂ，２２ｃ）を構成する各隙間のすべてに、径の異なる旋回羽根を備えたスワーラ２６，２７，２８をそれぞれ設けることとしたが（スワーラ有りの場合）、空気通路の一部にスワーラを設け、一部の空気通路は周状の隙間として残しておくこととしてもよい。このような変形例の場合には、周状の空気通路からは、筒状のパターンで軸方向に向けられた強い空気の噴射が得られ、スワーラからは、環状に軸方向の勢いを与えられるとともに旋回も与えられた筒状のパターンで空気が噴射されるので、全体として空気と燃料（特に液体燃料）の混合がより一層確実に行なわれるとともに、予混合管の壁面に接線方向を向けて形成された孔によって該混合気にさらに強い旋回流を形成することにより、燃焼筒の上部から離れた位置に火炎をより一層確実に保持できる効果が得られる。 Further, in the above-described modification illustrated on the left side of the center line in FIG. 2, swirlers 26, 27, which are provided with swirling blades having different diameters in all the gaps constituting the air passage 22 (22a, 22b, 22c). 28 is provided (when there is a swirler), but a swirler may be provided in a part of the air passage, and a part of the air passage may be left as a circumferential gap. In the case of such a modification, a strong air jet directed in the axial direction in a cylindrical pattern is obtained from the circumferential air passage, and an axial momentum is given annularly from the swirler. In addition, since air is injected in a cylindrical pattern that is also given swirling, air and fuel (particularly liquid fuel) are more reliably mixed as a whole, and the tangential direction is directed to the wall surface of the premixing tube. By forming a stronger swirl flow in the air-fuel mixture by the formed holes, it is possible to obtain an effect of more reliably holding the flame at a position away from the upper portion of the combustion cylinder.
１…ガスタービン燃焼器
２…燃焼筒
３…予混合管
５…燃料供給手段
６…遮熱プレート
７…冷却プレート
１１…ガイド部材
１２，１３…環状部材
１４…起動用圧力噴射ノズル
１６…燃料通路
１７…供給通路
１９…ノズル部
２０…供給孔
２１…フィルマ
２２…空気通路
２５…予混合管の孔
２６〜２８…スワーラ
Ｆ…火炎
DESCRIPTION OF SYMBOLS 1 ... Gas turbine combustor 2 ... Combustion cylinder 3 ... Premixing pipe 5 ... Fuel supply means 6 ... Heat insulation plate 7 ... Cooling plate 11 ... Guide member 12, 13 ... Annular member 14 ... Pressure injection nozzle 16 for starting 16 ... Fuel passage DESCRIPTION OF SYMBOLS 17 ... Supply passage 19 ... Nozzle part 20 ... Supply hole 21 ... Filma 22 ... Air passage 25 ... Premixing tube hole 26-28 ... Swirler F ... Flame
Claims (3)
前記燃料供給手段は、環状の燃料通路と、前記燃料通路の接線方向に沿って前記燃料通路に燃料を供給する供給通路と、前記燃料通路に連通し前記予混合管内に燃料を噴射する環状のノズル部と、前記燃料通路及び前記ノズル部の近傍に構成されて前記予混合管内に供給される空気が通過する周状の空気通路とを有し、
前記予混合管は、周壁面の接線方向に沿って内部に空気が流入するように前記周壁面に形成された複数の孔を有することを特徴とするガスタービン燃焼器。 A combustion cylinder in which a mixture of fuel and air is combusted to supply combustion gas to the turbine, a premixing pipe that is provided in an opening in the combustion cylinder and in which the supplied fuel and air are mixed, and the premixing pipe A gas turbine combustor having a fuel supply means for supplying fuel to the premixing pipe,
The fuel supply means includes an annular fuel passage, a supply passage that supplies fuel to the fuel passage along a tangential direction of the fuel passage, and an annular fuel passage that communicates with the fuel passage and injects fuel into the premixing pipe. A nozzle portion, and a circumferential air passage configured in the vicinity of the fuel passage and the nozzle portion, through which air supplied into the premixing tube passes,
The gas turbine combustor, wherein the premixing tube has a plurality of holes formed in the peripheral wall surface so that air flows into the inside along a tangential direction of the peripheral wall surface.
径の異なる複数の前記燃料供給手段が同心状に配置されることにより、少なくとも隣接する前記燃料供給手段の隙間が前記周状の空気通路となることを特徴とする請求項１記載のガスタービン燃焼器。 The fuel supply means is an annular member configured integrally with the fuel passage, the supply passage, the nozzle portion, and a supply hole communicating the fuel passage and the nozzle portion;
2. The gas turbine combustion according to claim 1, wherein a plurality of fuel supply means having different diameters are arranged concentrically so that at least a gap between adjacent fuel supply means becomes the circumferential air passage. vessel.
最も大径の前記燃料供給手段の外周に環状のガイド部材が設けられて、最も大径の前記燃料供給手段と前記ガイド部材の間の隙間が前記周状の空気通路となることを特徴とする請求項２記載のガスタービン燃焼器。 An activation pressure injection nozzle is provided at the center of the fuel supply means with the smallest diameter, and a gap between the fuel supply means with the smallest diameter and the activation pressure injection nozzle becomes the circumferential air passage,
An annular guide member is provided on the outer periphery of the fuel supply means having the largest diameter, and a gap between the fuel supply means having the largest diameter and the guide member serves as the circumferential air passage. The gas turbine combustor according to claim 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2008038968A JP4937158B2 (en) | 2008-02-20 | 2008-02-20 | Gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2008038968A JP4937158B2 (en) | 2008-02-20 | 2008-02-20 | Gas turbine combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2009198054A JP2009198054A (en) | 2009-09-03 |
| JP4937158B2 true JP4937158B2 (en) | 2012-05-23 |
Family
ID=41141744
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2008038968A Active JP4937158B2 (en) | 2008-02-20 | 2008-02-20 | Gas turbine combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP4937158B2 (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP5807899B2 (en) * | 2011-05-25 | 2015-11-10 | 新潟原動機株式会社 | Gas turbine combustor |
| JP5636335B2 (en) * | 2011-05-27 | 2014-12-03 | 新潟原動機株式会社 | Gas turbine combustor |
| US9441543B2 (en) | 2012-11-20 | 2016-09-13 | Niigata Power Systems Co., Ltd. | Gas turbine combustor including a premixing chamber having an inner diameter enlarging portion |
| US8943834B2 (en) | 2012-11-20 | 2015-02-03 | Niigata Power Systems Co., Ltd. | Pre-mixing injector with bladeless swirler |
| EP2735797B1 (en) | 2012-11-23 | 2019-01-09 | Niigata Power Systems Co., Ltd. | Gas turbine combustor |
| EP2735798B1 (en) | 2012-11-23 | 2020-07-29 | IHI Power Systems Co., Ltd. | Gas turbine combustor |
| JP6185369B2 (en) * | 2013-11-01 | 2017-08-23 | 新潟原動機株式会社 | Gas turbine combustor |
| EP3143334B1 (en) | 2014-05-12 | 2020-08-12 | General Electric Company | Pre-film liquid fuel cartridge |
| JP5958981B2 (en) * | 2015-02-13 | 2016-08-02 | 新潟原動機株式会社 | Method for changing flame lift distance in gas turbine combustor |
| JP7298095B2 (en) * | 2020-06-09 | 2023-06-27 | 株式会社三井E&S | Gas turbine premixing tube structure |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH037738Y2 (en) * | 1984-12-21 | 1991-02-26 | ||
| JPH07305849A (en) * | 1994-05-13 | 1995-11-21 | Ishikawajima Harima Heavy Ind Co Ltd | Premixing tube |
| US6289676B1 (en) * | 1998-06-26 | 2001-09-18 | Pratt & Whitney Canada Corp. | Simplex and duplex injector having primary and secondary annular lud channels and primary and secondary lud nozzles |
| US6715292B1 (en) * | 1999-04-15 | 2004-04-06 | United Technologies Corporation | Coke resistant fuel injector for a low emissions combustor |
| JP3590594B2 (en) * | 2001-04-25 | 2004-11-17 | 川崎重工業株式会社 | Liquid fuel-fired low NOx combustor for gas turbine engine |
| JP4670035B2 (en) * | 2004-06-25 | 2011-04-13 | 独立行政法人 宇宙航空研究開発機構 | Gas turbine combustor |
-
2008
- 2008-02-20 JP JP2008038968A patent/JP4937158B2/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| JP2009198054A (en) | 2009-09-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP4937158B2 (en) | Gas turbine combustor | |
| RU2747009C9 (en) | Gas turbine combustor | |
| US8113000B2 (en) | Flashback resistant pre-mixer assembly | |
| JP6637905B2 (en) | Burners, combustors, and gas turbines | |
| US8276385B2 (en) | Staged multi-tube premixing injector | |
| JP5393745B2 (en) | Gas turbine combustor | |
| US8001786B2 (en) | Combustor of a gas turbine engine | |
| US9109553B2 (en) | Fuel injector | |
| US5410884A (en) | Combustor for gas turbines with diverging pilot nozzle cone | |
| JP4930921B2 (en) | Fuel injector for combustion chamber of gas turbine engine | |
| JP6812240B2 (en) | Air Fuel Premixer for Low Emission Turbine Combustors | |
| US20110265482A1 (en) | Pocketed air and fuel mixing tube | |
| JP2009250604A (en) | Burner tube premixer and method for mixing air with gas in gas turbine engine | |
| CN101294715A (en) | Combustion device and combustion method of burner | |
| JP6466102B2 (en) | Dual fuel combustor for gas turbine engines | |
| US20160201918A1 (en) | Small arrayed swirler system for reduced emissions and noise | |
| CN108885001A (en) | gas turbine burner | |
| CN104870901B (en) | The arrangement of concave type fuel injector | |
| JP4861910B2 (en) | Diffusion combustion type gas turbine combustor | |
| JP2005265232A (en) | Gas turbine combustor | |
| CN118361756A (en) | Burner and combustion nozzle for hydrogen gas turbine | |
| CN102997281A (en) | System and method for conditioning a working fluid in a combustor | |
| JP4977522B2 (en) | Gas turbine combustor | |
| JP2016023916A (en) | Gas turbine combustor | |
| JPH0443220A (en) | Combustion device for gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20101122 |
|
| A977 | Report on retrieval |
Free format text: JAPANESE INTERMEDIATE CODE: A971007 Effective date: 20111226 |
|
| TRDD | Decision of grant or rejection written | ||
| A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20120207 |
|
| A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 |
|
| A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20120221 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20150302 Year of fee payment: 3 |
|
| R150 | Certificate of patent or registration of utility model |
Ref document number: 4937158 Country of ref document: JP Free format text: JAPANESE INTERMEDIATE CODE: R150 Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
| S531 | Written request for registration of change of domicile |
Free format text: JAPANESE INTERMEDIATE CODE: R313531 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20150302 Year of fee payment: 3 |
|
| R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
| S533 | Written request for registration of change of name |
Free format text: JAPANESE INTERMEDIATE CODE: R313533 |
|
| R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |