JPH0313407B2 - - Google Patents
Info
- Publication number
- JPH0313407B2 JPH0313407B2 JP57107378A JP10737882A JPH0313407B2 JP H0313407 B2 JPH0313407 B2 JP H0313407B2 JP 57107378 A JP57107378 A JP 57107378A JP 10737882 A JP10737882 A JP 10737882A JP H0313407 B2 JPH0313407 B2 JP H0313407B2
- Authority
- JP
- Japan
- Prior art keywords
- gas turbine
- switching valve
- combustion
- air
- pressure feeding
- 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.)
- Expired - Lifetime
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
- Regulation And Control Of Combustion (AREA)
Description
【発明の詳細な説明】
本発明はガスタービン装置に関し、特にガスタ
ービンと空気圧送手段とを同軸に連結し、燃焼手
段から発生する燃焼排ガスによつてガスタービン
を駆動するとともに空気圧送手段を駆動して前記
燃焼手段に燃焼用空気を圧送するようにしたガス
タービン装置に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a gas turbine device, and in particular to a gas turbine device in which a gas turbine and an air pressure feeding means are coaxially connected, and combustion exhaust gas generated from a combustion means drives the gas turbine and the air pressure feeding means. The present invention relates to a gas turbine device configured to forcefully feed combustion air to the combustion means.
第１図を参照して典型的な先行技術を説明す
る。発電機１を駆動するためのガスタービン２
に、破線３で示すように供給される燃料を燃焼手
段４で燃焼することによつて発生した燃焼排ガス
が供給され、ガスタービン２に同軸に連結された
コンプレツサ５によつて燃焼用空気が燃焼手段４
に供給される。このようなガスタービン装置にお
いて、起動時においては、コンプレツサ５が駆動
されないので、コンプレツサ５による燃焼用空気
の供給を行なうために、電動モータ６を設け、ガ
スタービン２の自力運転が可能になるまで、電動
モータ６によりコンプレツサ５およびガスタービ
ン２を駆動している。この先行技術では、起動時
のみに用いられる電動モータ６が必要であり、し
かも電動モータ６およびガスタービン２を連動さ
せるためにガスタービン２の構造が複雑となる。 A typical prior art technique will be described with reference to FIG. Gas turbine 2 for driving generator 1
As shown by the broken line 3, the combustion exhaust gas generated by burning the supplied fuel in the combustion means 4 is supplied, and the combustion air is combusted by the compressor 5 coaxially connected to the gas turbine 2. Means 4
is supplied to In such a gas turbine device, since the compressor 5 is not driven at startup, an electric motor 6 is provided to supply combustion air by the compressor 5, and the electric motor 6 is installed until the gas turbine 2 can operate on its own. , a compressor 5 and a gas turbine 2 are driven by an electric motor 6. This prior art requires an electric motor 6 that is used only during startup, and the structure of the gas turbine 2 becomes complicated because the electric motor 6 and the gas turbine 2 are interlocked.
第２図を参照して、他の先行技術では起動時に
おける燃焼用空気を供給するためのブロア７を設
けている。すなわち切換弁８を備えコンプレツサ
５および燃焼手段４を連結する連結管９の途中に
おける切換弁８の下流側に、ブロア７の吐出口が
切換弁１０を介して連結される。また連結管９に
おける切換弁８の上流側には、開閉弁１１を備え
る放出管１２が連結される。この先行技術では、
起動時に切換弁１０および開閉弁１１を開弁し、
切換弁８を閉弁する。その状態でブロア７を駆動
して燃焼用空気を燃焼手段４に供給し、ガスター
ビン２が定常安定領域である高回転に達してから
切換弁１０および開閉弁１１を閉弁し、切換弁８
を開弁する。したがつてブロア７は高圧、高風量
であることが必要であり、しかもガスタービン２
が定常安定領域に達するまでにコンプレツサ５か
ら吐出される空気は放出管１２から無駄に放出さ
れる。 Referring to FIG. 2, another prior art includes a blower 7 for supplying combustion air during startup. That is, the discharge port of the blower 7 is connected via the switching valve 10 to the downstream side of the switching valve 8 in the middle of a connecting pipe 9 that includes the switching valve 8 and connects the compressor 5 and the combustion means 4 . Further, a discharge pipe 12 including an on-off valve 11 is connected to the upstream side of the switching valve 8 in the connecting pipe 9 . In this prior art,
At startup, the switching valve 10 and the on-off valve 11 are opened,
The switching valve 8 is closed. In this state, the blower 7 is driven to supply combustion air to the combustion means 4, and after the gas turbine 2 reaches a high rotation speed that is a steady stable region, the switching valve 10 and the on-off valve 11 are closed, and the switching valve 8 is closed.
Open the door. Therefore, the blower 7 needs to have high pressure and high air volume, and the gas turbine 2
The air discharged from the compressor 5 until it reaches a steady state region is wastefully discharged from the discharge pipe 12.
なお、第２図の先行技術において、ブロア７の
容量を小形化するためには、ガスタービン２が不
安定な低速回転時に切換弁８，１０を切換えて自
力運転に移行しなければならず、圧力や風量バラ
ンスの制御が困難である。 In addition, in the prior art shown in FIG. 2, in order to reduce the capacity of the blower 7, it is necessary to switch the switching valves 8 and 10 and shift to self-operation when the gas turbine 2 rotates at an unstable low speed. Difficult to control pressure and air volume balance.
本発明は、上述の技術的課題を解決し、比較的
小容量の空気圧送手段により、容易に起動させう
るようにしたガスタービン装置を提供することを
目的とする。 SUMMARY OF THE INVENTION An object of the present invention is to solve the above-mentioned technical problems and to provide a gas turbine device that can be easily started using a relatively small capacity air pressure feeding means.
本発明は、ガスタービン１７と空気圧送手段１
９とを同軸に連結し、燃焼手段１５から発生する
燃焼排ガスによつてガスタービン１７を駆動する
とともに空気圧送手段１９を駆動して前記燃焼手
段１５に燃焼用空気を圧送するようにしたガスタ
ービン装置において、
前記空気圧送手段１９の出口と燃焼手段１５と
は途中に第１切換弁２０を備える連結管２１で連
結され、その連結管２１における第１切換弁２０
の上流側と下流側とを連結してバイパス管２２が
設けられ、前記バイパス管２２には上流側から順
に第２切換弁２３、起動用フアン２４および第３
切換弁２５が備えられ、(a)起動時には第１切換弁
２０を閉弁し、第２および第３切換弁２３，２５
を開弁した状態で起動用フアン２４を駆動し、(b)
ガスタービン１７の回転数が充分に安定して自力
運転できる程度の高い値に達したときに、第１切
換弁２０を開弁し、第２および第３切換弁２３，
２５を閉弁し、起動用フアン２４を停止すること
を特徴とするガスタービン装置である。 The present invention includes a gas turbine 17 and an air pressure feeding means 1.
9 are coaxially connected, and the gas turbine 17 is driven by the combustion exhaust gas generated from the combustion means 15, and the air pressure feeding means 19 is driven to forcefully feed combustion air to the combustion means 15. In the apparatus, the outlet of the air pressure feeding means 19 and the combustion means 15 are connected by a connecting pipe 21 having a first switching valve 20 in the middle, and the first switching valve 20 in the connecting pipe 21 is connected to the combustion means 15.
A bypass pipe 22 is provided connecting the upstream and downstream sides of the bypass pipe 22, and the bypass pipe 22 includes a second switching valve 23, a starting fan 24, and a third switching valve in order from the upstream side.
A switching valve 25 is provided, and (a) at startup, the first switching valve 20 is closed, and the second and third switching valves 23, 25 are closed.
Drive the starting fan 24 with the valve open, (b)
When the rotational speed of the gas turbine 17 reaches a sufficiently stable value for self-operation, the first switching valve 20 is opened, and the second and third switching valves 23,
This gas turbine device is characterized in that the valve 25 is closed and the starting fan 24 is stopped.
以下、図面によつて本発明の実施例を説明す
る。第３図は本発明の一実施例の系統図である。
燃焼手段１５には破線１６で示すように燃料が供
給され、その燃料の燃焼排ガスによつてガスター
ビン１７が回転駆動される。ガスタービン１７に
よつて発電機１８が駆動され、それによつて電力
が得られる。またガスタービン１７には遠心コン
プレツサや遠心ブロアなどの空気圧送手段１９が
同軸に連結されており、この空気圧送手段１９に
よつて燃焼手段１５に燃焼用空気が供給される。 Embodiments of the present invention will be described below with reference to the drawings. FIG. 3 is a system diagram of one embodiment of the present invention.
Fuel is supplied to the combustion means 15 as shown by a broken line 16, and a gas turbine 17 is rotationally driven by the combustion exhaust gas of the fuel. A generator 18 is driven by the gas turbine 17, thereby obtaining electric power. Further, an air pressure feeding means 19 such as a centrifugal compressor or a centrifugal blower is coaxially connected to the gas turbine 17, and combustion air is supplied to the combustion means 15 by this air pressure feeding means 19.
空気圧送手段１９の吐出口は第１切換弁２０を
備える連結管２１を介して燃焼手段１５に連結さ
れる。この連結管２１における第１切換弁２０の
上流側および下流側を連結してバイパス管２２が
設けられる。このバイパス管２２には、上流側か
ら順に第２切換弁２３、起動用フアン２４および
第３切換弁２５が備えられる。なお、起動用フア
ン２４にはモータ２６が設けられる。 A discharge port of the air pressure feeding means 19 is connected to the combustion means 15 via a connecting pipe 21 provided with a first switching valve 20 . A bypass pipe 22 is provided to connect the upstream and downstream sides of the first switching valve 20 in the connecting pipe 21 . This bypass pipe 22 is equipped with a second switching valve 23, a starting fan 24, and a third switching valve 25 in this order from the upstream side. Note that the starting fan 24 is provided with a motor 26 .
このようなガスタービン装置において、起動時
には第１切換弁２０を閉弁し、かつ第２および第
３切換弁２３，２５を開弁した状態で、起動用フ
アン２４を駆動する。起動用フアン２４によつて
吸引される空気は、空気圧送手段１９をわずかに
回転させながら燃焼手段１５に供給される。ここ
で燃焼手段１５に燃料を供給して、着火、燃焼さ
せることにより発生した燃焼排ガスはガスタービ
ン１７に送り込まれる。それによつてガスタービ
ン１７が回転駆動させるとともに、空気圧送手段
１９が回転され、圧縮された空気が起動用フアン
２４を介して燃焼手段１５に供給される。このよ
うにしてガスタービン１７の回転数が次第に増加
していく。ガスタービン１７の回転数が充分に安
定して自力運転ができる程度の高い値に達したと
きに、第２および第３切換弁２３，２５を閉弁
し、かつ第１切換弁２０を開弁し、フアン２４を
停止する。そうすれば、空気圧送手段１９から充
分な量の空気が供給されるので、安定した自力運
転に移行することができる。 In such a gas turbine apparatus, at startup, the startup fan 24 is driven with the first switching valve 20 closed and the second and third switching valves 23 and 25 opened. Air sucked by the starting fan 24 is supplied to the combustion means 15 while slightly rotating the air pressure feeding means 19. Here, fuel is supplied to the combustion means 15, and the combustion exhaust gas generated by ignition and combustion is sent to the gas turbine 17. As a result, the gas turbine 17 is rotationally driven, the air pressure feeding means 19 is rotated, and compressed air is supplied to the combustion means 15 via the starting fan 24. In this way, the rotational speed of the gas turbine 17 gradually increases. When the rotational speed of the gas turbine 17 is sufficiently stable and reaches a high enough value for self-operation, the second and third switching valves 23 and 25 are closed, and the first switching valve 20 is opened. Then, the fan 24 is stopped. In this way, a sufficient amount of air is supplied from the air pressure feeding means 19, so that stable self-operation can be achieved.
なお、起動用フアン２４は、燃焼手段１５で着
火時に安定した燃焼を持続しうる程度の比較的小
量の空気を供給する小容量であればよい。 Note that the starting fan 24 only needs to have a small capacity that can supply a relatively small amount of air to the extent that the combustion means 15 can maintain stable combustion at the time of ignition.
本件発明者の行なつた実験によれば、ガスター
ビン１７の自力運転が可能な燃焼手段１５の入口
圧は200mmAq、その風量は2Nm3／min.、モータ
２６の動力は0.3kWだけ少なくとも必要であつ
た。これに比べて、第２図に示された先行技術で
は、ガスタービン２を自力運転するには、燃焼手
段４の入口圧は500mmAq、ブロア７の風量は2N
m3／min.、そのブロア７の動力は1.5kWだけ少な
くとも必要であつた。このことから本発明によれ
ば、起動用フアン２４の吐出圧および動力を低減
することができることが明らかである。 According to experiments conducted by the inventor of the present invention, the inlet pressure of the combustion means 15 that allows the gas turbine 17 to operate on its own is 200 mmAq, its air volume is 2 Nm 3 /min., and the power of the motor 26 is at least 0.3 kW. It was hot. In comparison, in the prior art shown in FIG. 2, in order to operate the gas turbine 2 on its own, the inlet pressure of the combustion means 4 is 500 mmAq, and the air volume of the blower 7 is 2N.
m 3 /min., and the power of the blower 7 was required to be at least 1.5 kW. From this, it is clear that according to the present invention, the discharge pressure and power of the starting fan 24 can be reduced.
以上のように本発明によれば、比較的小容量の
起動用フアンを設けた簡単な構成によつて、ガス
タービンを安定して起動することが可能となる。 As described above, according to the present invention, it is possible to stably start a gas turbine with a simple configuration including a relatively small-capacity starting fan.
しかも本発明によれば、ガスタービン１７の回
転数が充分に安定して自力運転ができる程度の高
い値に達したときには、第２および第３切換弁２
３，２５が閉じられるので、空気圧送手段１９か
ら連結管２１および第１切換弁２０を経て燃焼手
段１５に導かれる比較的高い圧力、たとえば１
Kg／cm2の空気が起動用フアン２４に導かれること
がない。したがつて起動用フアン２４は、耐圧性
に優れた構成でなくてもよく、たとえば0.3Kg／
cm2程度の空気の漏れを防ぐ程度であればよく、こ
のことによつて、起動用フアン２４の構成を簡単
にすることができるという優れた効果が達成され
る。このことは特に、既存のガスタービン１７と
燃焼手段１５と空気圧送手段１９とを備えるガス
タービン装置において本発明を容易に実施するこ
とが可能となり、この点で本発明は広範囲に実施
され、優れたものである。 Moreover, according to the present invention, when the rotational speed of the gas turbine 17 reaches a sufficiently high value that it is stable enough to operate under its own power, the second and third switching valves 2
3 and 25 are closed, a relatively high pressure, e.g.
Kg/cm 2 of air is not guided to the startup fan 24. Therefore, the starting fan 24 does not need to have a structure with excellent pressure resistance, for example, 0.3 kg/
It is sufficient to prevent air leakage of about cm 2 , and this achieves the excellent effect of simplifying the configuration of the startup fan 24. This particularly makes it possible to easily implement the present invention in a gas turbine installation comprising an existing gas turbine 17, combustion means 15 and air pumping means 19, and in this respect the present invention can be widely implemented and is superior. It is something that
第１図および第２図は先行技術をそれぞれ示す
系統図、第３図は本発明の一実施例の系統図であ
る。
１５……燃焼手段、１７……ガスタービン、１
９……空気圧送手段、２０……第１切換弁、２１
……連結管、２２……バイパス管、２３……第２
切換弁、２４……起動用フアン、２５……第３切
換弁、２６……モータ。
FIGS. 1 and 2 are system diagrams showing the prior art, respectively, and FIG. 3 is a system diagram of an embodiment of the present invention. 15... Combustion means, 17... Gas turbine, 1
9... Air pressure feeding means, 20... First switching valve, 21
... Connecting pipe, 22 ... Bypass pipe, 23 ... Second
Switching valve, 24... Starting fan, 25... Third switching valve, 26... Motor.
Claims (1)
軸に連結し、燃焼手段１５から発生する燃焼排ガ
スによつてガスタービン１７を駆動するとともに
空気圧送手段１９を駆動して前記燃焼手段１５に
燃焼用空気を圧送するようにしたガスタービン装
置において、 前記空気圧送手段１９の出口と燃焼手段１５と
は途中に第１切換弁２０を備える連結管２１で連
結され、その連結管２１における第１切換弁２０
の上流側と下流側とを連結してバイパス管２２が
設けられ、前記バイパス管２２には上流側から順
に第２切換弁２３、起動用フアン２４および第３
切換弁２５が備えられ、(a)起動時には第１切換弁
２０を閉弁し、第２および第３切換弁２３，２５
を開弁した状態で起動用フアン２４を駆動し、(b)
ガスタービン１７の回転数が充分に安定して自力
運転できる程度の高い値に達したときに、第１切
換弁２０を開弁し、第２および第３切換弁２３，
２５を閉弁し、起動用フアン２４を停止すること
を特徴とするガスタービン装置。[Scope of Claims] 1. A gas turbine 17 and an air pressure feeding means 19 are coaxially connected, and the gas turbine 17 is driven by the combustion exhaust gas generated from the combustion means 15, and the air pressure feeding means 19 is driven to perform the combustion. In a gas turbine device configured to forcefully feed combustion air to the means 15, the outlet of the air pressure feeding means 19 and the combustion means 15 are connected by a connecting pipe 21 having a first switching valve 20 in the middle, and the connecting pipe 21 The first switching valve 20 in
A bypass pipe 22 is provided connecting the upstream and downstream sides of the bypass pipe 22, and the bypass pipe 22 includes a second switching valve 23, a starting fan 24, and a third switching valve in order from the upstream side.
A switching valve 25 is provided, and (a) at startup, the first switching valve 20 is closed, and the second and third switching valves 23, 25 are closed.
Drive the starting fan 24 with the valve open, (b)
When the rotational speed of the gas turbine 17 reaches a sufficiently stable value for self-operation, the first switching valve 20 is opened, and the second and third switching valves 23,
A gas turbine device characterized in that a valve 25 is closed and a starting fan 24 is stopped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10737882A JPS58222922A (en) | 1982-06-21 | 1982-06-21 | Gas turbine device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10737882A JPS58222922A (en) | 1982-06-21 | 1982-06-21 | Gas turbine device |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP7854690A Division JPH02283824A (en) | 1990-03-26 | 1990-03-26 | Gas turbine device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS58222922A JPS58222922A (en) | 1983-12-24 |
| JPH0313407B2 true JPH0313407B2 (en) | 1991-02-22 |
Family
ID=14457588
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP10737882A Granted JPS58222922A (en) | 1982-06-21 | 1982-06-21 | Gas turbine device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS58222922A (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5235812A (en) * | 1989-09-21 | 1993-08-17 | Allied-Signal Inc. | Integrated power unit |
| US5160069A (en) * | 1989-09-21 | 1992-11-03 | Allied-Signal Inc. | Integrated power unit combustion apparatus and method |
-
1982
- 1982-06-21 JP JP10737882A patent/JPS58222922A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPS58222922A (en) | 1983-12-24 |
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