JPH0637976B2 - Method of manufacturing transition piece of combustor for gas turbine - Google Patents
Method of manufacturing transition piece of combustor for gas turbineInfo
- Publication number
- JPH0637976B2 JPH0637976B2 JP60071056A JP7105685A JPH0637976B2 JP H0637976 B2 JPH0637976 B2 JP H0637976B2 JP 60071056 A JP60071056 A JP 60071056A JP 7105685 A JP7105685 A JP 7105685A JP H0637976 B2 JPH0637976 B2 JP H0637976B2
- Authority
- JP
- Japan
- Prior art keywords
- transition piece
- lower half
- half body
- eaves
- upper half
- 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
- 230000007704 transition Effects 0.000 title claims description 58
- 238000004519 manufacturing process Methods 0.000 title claims description 14
- 239000000567 combustion gas Substances 0.000 claims description 16
- 239000007789 gas Substances 0.000 claims description 13
- 238000000034 method Methods 0.000 claims description 9
- 238000005304 joining Methods 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 4
- 238000003825 pressing Methods 0.000 claims description 4
- 230000002093 peripheral effect Effects 0.000 claims description 2
- 238000000465 moulding Methods 0.000 claims 1
- 238000001816 cooling Methods 0.000 description 25
- 238000003466 welding Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Description
【発明の詳細な説明】 ［産業上の利用分野］ この発明は、ガスタービン用燃焼器の内筒に接続され
て、ひさし形フイルム冷却構造を有する尾筒の製造方法
に関するものである。TECHNICAL FIELD The present invention relates to a method of manufacturing a transition piece connected to an inner cylinder of a gas turbine combustor and having a canopy-type film cooling structure.
［従来技術］ 近年、発電機などに用いられるガスタービンの高性能、
高効率化が進められ、それによる高温化に対して、ガス
タービンの耐久性向上のため、燃焼器の内筒に接続され
る尾筒を冷却する必要性が年々高まってきている。[Prior Art] In recent years, high performance of gas turbines used for generators,
High efficiency has been promoted, and it has become increasingly necessary to cool the transition piece connected to the inner cylinder of the combustor year by year in order to improve the durability of the gas turbine against the increase in temperature.
従来の尾筒としては、第６図で示すように、冷却構造が
形成されていないものが一般的であった（特公昭５１−
１２７６３号公報参照）。As a conventional transition piece, as shown in FIG. 6, a transition piece having no cooling structure is generally used (Japanese Examined Patent Publication No. 51-
No. 12763).
同図において、４２は燃焼器の内筒で、ガスタービンの
回転軸心（図示せず）に沿って多数設けられている。尾
筒４１は、上記内筒４２の後端部に接続されて、燃焼ガ
スＧをタービン４３へ導くものであり、その横断面形状
は、内筒４２との接続部付近では、第７図で示すよう
に、円形であるが、タービン４３との接続部付近では、
第８図に示すように、タービン形状に合わせて箱扇形へ
と徐々に滑らかに変化している。In the figure, reference numeral 42 denotes an inner cylinder of the combustor, which is provided in a large number along the rotational axis (not shown) of the gas turbine. The transition piece 41 is connected to the rear end portion of the inner tube 42 and guides the combustion gas G to the turbine 43. The cross-sectional shape of the transition piece 41 is shown in FIG. As shown, it is circular, but near the connection with the turbine 43,
As shown in FIG. 8, the shape of the fan gradually changes smoothly in accordance with the shape of the turbine.
［発明が解決しようとする課題］ このように、尾筒４１は複雑な形状をとるものであり、
さらに冷却構造を付加して、かつ、簡単に製造できるよ
うにすることは、容易ではない。[Problems to be Solved by the Invention] As described above, the transition piece 41 has a complicated shape,
It is not easy to add a cooling structure and to make it easy to manufacture.
すなわち、従来から燃焼器の内筒４２を効果的に冷却す
る構造として、第６図で示すようなひさし形のフイルム
冷却構造が用いられている。この冷却構造は、内筒４２
を流れ方向に複数の内筒段部４２１，４２２，……４２
ｎに分割してよろい状に重ね合わせ、その重ね合わせ部
に生じるひさし４５を案内に、空気孔（図示せず）から
冷却空気を内筒４２の内面に沿ってフイルム状に導入し
て、内筒４２を冷却するものである。このひさし形のフ
イルム冷却構造は、上記内筒４２がストレートな円筒形
であることから、分割された複数の内筒段４２１，４２
２，……４２ｎはすべて同一形状になる結果、単一のプ
レス型で上記内筒段４２１，４２２，……４２ｎを形成
できるので、製造が容易である。That is, conventionally, as a structure for effectively cooling the inner cylinder 42 of the combustor, an eaves-shaped film cooling structure as shown in FIG. 6 has been used. This cooling structure has an inner cylinder 42
A plurality of inner cylinder steps 42 1 , 42 2 , ... 42 in the flow direction
It is divided into n pieces and superposed in an armored shape, and cooling air is introduced in the form of a film along the inner surface of the inner cylinder 42 from an air hole (not shown) using the eaves 45 generated in the superposed portion as a guide. The cylinder 42 is cooled. In this eave-shaped film cooling structure, since the inner cylinder 42 is a straight cylindrical shape, a plurality of divided inner cylinder stages 42 1 , 42 are formed.
As a result, all of 2 , 2 , ... 42 n have the same shape, so that the inner cylinder stages 42 1 , 42 2 , ..., 42 n can be formed by a single press die, and therefore the manufacturing is easy.
しかしながら、このひさし形のフイルム冷却構造を上記
した複雑な形状の尾筒４１にそのまま採用すると、第９
図で示すように、分割された多数の尾筒段４１１，４１
２，……４１ｎの形状が個々に異なるので、各尾筒段４
１１，４１２，……４１ｎごとに１組のプレス型と治具
とを準備する必要があり、製造がきわめて面倒になる。However, if this eaves-shaped film cooling structure is directly adopted for the complicatedly formed transition piece 41,
As shown in the figure, a large number of divided transition pipe stages 41 1 , 41
2 , ... 41 n has different shapes, so each tail tube stage 4
It is necessary to prepare a set of press dies and jigs for each of 1 1 , 41 2 , ... 41 n , which makes manufacturing extremely troublesome.
そこで、上記尾筒４１の壁に空気孔を斜めに開けて、尾
筒４１の周囲から内部へ冷却空気を導入するようにした
ものもあるが、これでは尾筒４１の内面に冷却空気のフ
イルムが円滑に形成できず、大きな冷却効果が得られな
かった。Therefore, there is also one in which an air hole is obliquely formed in the wall of the transition piece 41 to introduce the cooling air from the periphery of the transition piece 41 to the inside, but in this case, the cooling air film is formed on the inner surface of the extension piece 41. Could not be formed smoothly and a large cooling effect could not be obtained.
この発明は、上記課題を解消するためになされたもの
で、複雑なひさし形フイルム冷却構造を有する尾筒を簡
易に製造できるガスタービン用燃焼器の尾筒の製造方法
を提供することを目的としている。The present invention has been made to solve the above problems, and an object of the present invention is to provide a method of manufacturing a transition piece of a gas turbine combustor that can easily produce a transition piece having a complicated eaves-shaped film cooling structure. There is.
［課題を解決するための手段］ 上記目的を達成するため、この発明は、平板状部材を上
下２つ割りのプレス型に入れて燃焼ガスの流れ方向に沿
った接合面を有する尾筒の上半体と下半体とをそれぞれ
プレス加工する工程と、上記尾筒の上半体と下半体のプ
レス加工時に上記燃焼ガスの流れ方向にほぼ直交する面
内で上記尾筒の上半体および下半体の各全周にわたり外
方へ突出するひさし取付段部を一体形成する工程と、上
記ひさし取付段部に連なって上記燃焼ガスの流れ方向に
ほぼ直交する面内で上記尾筒の上半体および下半体の各
全周にわたり外方へ突出する空気導入段部を一体形成す
る工程と、この空気導入段部に複数の空気孔を形成する
工程と、上記プレス成形した尾筒の上半体および下半体
のつば部を切断する工程と、帯状板材をプレス加工して
上記尾筒の上半体および下半体の各ひさし取付段部の内
周面に密に嵌合されるひさしの上半部および下半部をそ
れぞれ成形する工程と、この尾筒の上半体および下半体
の各取付段部にそれぞれ対応する上記ひさしの上半部と
下半部とを接合する工程と、上記ひさしの上半部および
下半部を接合した尾筒の上半体と下半体とを燃焼ガスの
流れ方向に沿った接合面で接合させる工程とを具備した
ことを特徴とする。[Means for Solving the Problem] In order to achieve the above object, the present invention is directed to a case where a flat plate member is placed in a press die that is divided into upper and lower halves, and a top surface of a transition piece having a joint surface along the flow direction of combustion gas A step of pressing each of the half body and the lower half body, and an upper half body of the transition piece in a plane substantially orthogonal to the flow direction of the combustion gas when pressing the upper half body and the lower half piece of the transition piece And a step of integrally forming an eaves mounting step portion projecting outward over the entire circumference of the lower half body, and a step of connecting the eaves mounting step portion to the tail pipe in a plane substantially orthogonal to the flow direction of the combustion gas. A step of integrally forming an air introducing step portion projecting outward over the entire circumference of each of the upper half body and the lower half body, a step of forming a plurality of air holes in the air introducing step portion, and the press-molded transition piece The process of cutting the flanges of the upper half and lower half of the And a step of forming the upper half and the lower half of the eaves, which are closely fitted to the inner peripheral surfaces of the eaves mounting steps of the upper half and the lower half of the tail cylinder, respectively, A step of joining the upper half and the lower half of the eaves corresponding to the mounting step portions of the upper half and the lower half of the cylinder, respectively, and a transition piece in which the upper half and the lower half of the eaves are joined And a step of joining the upper half body and the lower half body at a joint surface along the flow direction of the combustion gas.
［作用］ この発明によれば、尾筒形成用部材を上下２つ割り型に
挿入して上半体および下半体を別々にプレス成形するの
で、複雑な形状の尾筒が簡単に製造できる。[Operation] According to the present invention, since the transition piece forming member is inserted into the upper and lower halves and the upper half body and the lower half body are separately press-molded, a transition piece having a complicated shape can be easily manufactured. .
また、帯状板材を簡単な治具を用いて折曲してフイルム
冷却構造用ひさしが成形されるので、形状が異なる複数
のひさしが簡単に製造できる。Further, since the strip-shaped plate material is bent using a simple jig to form the eaves for film cooling structure, a plurality of eaves having different shapes can be easily manufactured.
また、上記ひさしを尾筒の取付段部に接合させ、このひ
さしを接合させた尾筒の上半体と下半体を接合する簡単
な工程で、ひさし形フイルム冷却構造を形成した複雑な
構造の尾筒が製造できる。In addition, the eaves-shaped film cooling structure is formed by a simple process in which the eaves are joined to the mounting step of the transition piece and the upper half and the lower half of the transition piece to which the eaves are attached are joined together. Can be manufactured.
［実施例］ 以下、この発明の実施例を図面にしたがって説明する。Embodiments Embodiments of the present invention will be described below with reference to the drawings.
第１図は、この発明による方法で製造されるガスタービ
ンの燃焼器部分を一部切欠して示す側面図である。FIG. 1 is a side view showing a combustor portion of a gas turbine manufactured by the method according to the present invention with a part thereof cut away.
同図において、１１は燃焼器の内筒であり、第６図で示
したものと同様に、ひさし形のフイルム冷却構造を有す
る。In the figure, reference numeral 11 denotes an inner cylinder of the combustor, which has an eaves-shaped film cooling structure similar to that shown in FIG.
第１図の上記内筒１１の後端部には、ひさし形フイルム
冷却構造を形成した尾筒１２が接続されている。回転軸
１には、圧縮機２およびタービン３が固定されており、
上記圧縮機２からタービン３へと連なる空気通路４内
に、上記内筒１１および尾筒１２が配置され、上記内筒
１１で生成された燃焼ガスＧを、上記尾筒１２によりタ
ービン３へ導くようになされている。なお、１０は燃料
ノズルである。A rear cylinder 12 having an eaves-shaped film cooling structure is connected to the rear end of the inner cylinder 11 of FIG. A compressor 2 and a turbine 3 are fixed to the rotary shaft 1,
The inner cylinder 11 and the transition piece 12 are arranged in an air passage 4 communicating with the compressor 2 to the turbine 3, and the combustion gas G generated in the inner tube 11 is guided to the turbine 3 by the transition piece 12. It is done like this. In addition, 10 is a fuel nozzle.
第２図は、上記尾筒１２の外形を示す側面図、第３図
は、第２図の要部を示す縦断面図である。FIG. 2 is a side view showing the outer shape of the transition piece 12, and FIG. 3 is a vertical sectional view showing the main part of FIG.
上記ひさし形フイルム冷却構造を形成した尾筒１２は、
つぎに示す工程で製造される。The transition piece 12 having the eaves-shaped film cooling structure is
It is manufactured by the following steps.
すなわち、まず、第４図で示す上下２つ割りのプレス型
２３に平板状部材を挿入し、これをプレス成形して、第
２図で示されるように、燃焼ガスＧの流れ方向Ｘに沿っ
た面Ｆで２分割される尾筒１２の上半体１２ａを成形す
る。上記尾筒１２の下半体１２ｂも上記と同様にして、
別の上下２つ割りの型でプレス成形する。このとき、第
３図で示される空気孔７を、このプレス成形と同時に打
ち抜いて形成する。That is, first, a flat plate-shaped member is inserted into the upper and lower halves of the press die 23 shown in FIG. 4, and this is press-molded, and along the flow direction X of the combustion gas G, as shown in FIG. The upper half 12a of the transition piece 12 which is divided in two by the raised surface F is formed. The lower half 12b of the transition piece 12 is also similar to the above,
Press-mold with another mold that is split into two parts. At this time, the air holes 7 shown in FIG. 3 are formed by punching at the same time as this press forming.
第５図は、上記のようにプレス成形した上半体１２ａと
下半体１２ｂの組立工程を示す横断面図である。FIG. 5 is a cross-sectional view showing an assembling process of the upper half body 12a and the lower half body 12b press-molded as described above.
第５図（Ａ）で示すように、まず、プレス成形した上半
体１２ａと下半体１２ｂのつば部９，９をＷ面とＺ面で
それぞれ切断する。つぎに、第５図（Ｂ）に示すよう
に、帯状板材を折曲して形状が異なる複数の上半部８ａ
と下半部８ｂとに分割されたひさしを別に製造し、これ
らをそれぞれ対応する前記上半体１２ａと下半体１２ｂ
の取付段部にはめ込んで、溶接接合する。ついで、第５
図（Ｃ）で示すように、上記ひさしを接合した上半体１
２ａと下半体１２ｂを、第２図で示されるように、燃焼
ガスＧの流れ方向Ｘに沿った接合面Ｆで溶接接合して尾
筒１２を製造する。As shown in FIG. 5 (A), first, the flange portions 9, 9 of the press-formed upper half body 12a and lower half body 12b are cut along the W plane and the Z plane, respectively. Next, as shown in FIG. 5 (B), the strip-shaped plate material is bent to form a plurality of upper half portions 8a having different shapes.
And eaves divided into a lower half portion 8b are separately manufactured, and these eaves are respectively corresponding to the upper half body 12a and the lower half body 12b.
Insert it into the mounting step of and weld it. Then, the fifth
As shown in FIG. (C), the upper half body 1 in which the above eaves are joined
As shown in FIG. 2, the tail piece 12 is manufactured by welding the 2a and the lower half 12b at the joint surface F along the flow direction X of the combustion gas G.
上記上半体１２ａと下半体１２ｂには、上記燃焼ガスの
流れ方向Ｘとほぼ直交する面Ｙ上に位置して、第３図で
示すように、尾筒１２の全周にわたって、外方へ突出す
る取付段部５および空気導入段部６が一体形成されてお
り、上記空気導入段部６に外部から、すなわち、第１図
の空気通路４から冷却空気２１を導入する空気孔７が設
けられている。第３図の８はひさしで、前記上半体１２
ａおよび下半体１２ｂとは別の部材からなり、細い帯状
の板材を簡単な治具を用いて折曲して製造され、上記上
半体１２ａおよび下半体１２ｂの取付段部５の内面に溶
接により取り付けられている。The upper half body 12a and the lower half body 12b are located on a plane Y substantially orthogonal to the flow direction X of the combustion gas, and as shown in FIG. The mounting step portion 5 and the air introducing step portion 6 projecting to the above are integrally formed, and the air introducing step portion 6 has an air hole 7 for introducing the cooling air 21 from the outside, that is, from the air passage 4 in FIG. It is provided. Reference numeral 8 in FIG. 3 denotes an eaves, which is the upper half 12
a and a lower half body 12b, which are different from each other, and are manufactured by bending a thin strip-shaped plate material using a simple jig, and the inner surface of the mounting step portion 5 of the upper half body 12a and the lower half body 12b. It is attached by welding.
上記方法で製造される尾筒１２は、前記するようにガス
タービンの燃焼器用として使用され、第１図の尾筒１２
の内面には、第３図で示すひさし８によって、冷却空気
２１のフイルムが形成されるから、尾筒１２が効果的に
冷却される。また、第３図で示されるように、尾筒１２
の取付段部５にひさし８が溶接で取り付けられているか
ら、ひさし８の前端部８ａが尾筒１２の内方へ突出しな
くなるので、上記前端部８ａによって尾筒１２の内部の
空気の流れが乱されるおそれがなくなり、冷却性能が高
く維持される。The transition piece 12 manufactured by the above method is used for the combustor of the gas turbine as described above, and the transition piece 12 of FIG.
The eaves 8 shown in FIG. 3 forms a film of the cooling air 21 on the inner surface of the tail tube 12, so that the transition piece 12 is effectively cooled. Further, as shown in FIG. 3, the transition piece 12
Since the eaves 8 is attached to the mounting step portion 5 by welding, the front end portion 8a of the eaves 8 does not project inward of the transition piece 12, so that the air flow inside the transition piece 12 is prevented by the front end portion 8a. There is no risk of being disturbed, and cooling performance is maintained high.
するがって、ガスタービンの高性能、高能率化による高
温化に対して十分な耐久性を持ち、ガスタービンの耐久
性向上が可能となる。Therefore, the gas turbine has high performance and sufficient durability against high temperature due to high efficiency, and the durability of the gas turbine can be improved.
さらに、尾筒１２は、上半体１２ａと下半体１２ｂとい
う２つの部材を接合して形成されるから、第１図のプレ
ス型２３を上半体用と下半体用との２組を準備すればよ
いので、製造工程が簡略化される。Furthermore, since the transition piece 12 is formed by joining two members, an upper half body 12a and a lower half body 12b, the press die 23 of FIG. 1 is provided in two sets, one for the upper half body and one for the lower half body. Therefore, the manufacturing process is simplified.
第３図のひさし８は、形状の異なるものを多数作成する
必要があるが、前記するように簡単に製造できるので、
製造工程の複雑化を招くことはない。As for the eaves 8 of FIG. 3, it is necessary to make many eaves having different shapes, but since it can be easily manufactured as described above,
The manufacturing process is not complicated.
なお、上記実施例では、尾筒の空気導入段部に形成する
空気孔を、尾筒成形部材をプレス成形すると同時に形成
するようにするが、プレス成形後、機械加工によりこの
空気孔を形成してもよい。In the above embodiment, the air hole formed in the air introduction step portion of the transition piece is formed at the same time when the transition piece forming member is press-formed, but after the press formation, this air hole is formed by machining. May be.
［発明の効果］ 以上説明したように、この発明によれば、尾筒形成用部
材を上下２つ割りのプレス型に入れて上半体および下半
体を別々にプレス成形するので、プレス型を２組準備す
ればよく、製造工程が簡略化されて、複雑な形状の尾筒
を簡単に製造できる。[Effects of the Invention] As described above, according to the present invention, since the transition piece forming member is put into the upper and lower halves of the press die and the upper half body and the lower half body are separately press-formed, the press die It is only necessary to prepare two sets, and the manufacturing process is simplified, and a tail cylinder having a complicated shape can be easily manufactured.
また、簡単な治具を用いて帯状板材を折曲し、形状が異
なる複数のひさしが簡単に製造でき、これらのひさしを
それぞれ尾筒の取付段部の内周にはめ込み接合させた上
半体と下半体とを接合する簡単な工程で、ひさし形フイ
ルム冷却構造を有する複雑な構造の尾筒が製造できる。In addition, a strip-shaped plate can be bent using a simple jig to easily manufacture multiple eaves with different shapes.Each of these eaves is fitted and joined to the inner circumference of the mounting step of the transition piece and joined together. With a simple process of joining the lower half and the lower half, a tail pipe having a complicated structure having an eaves-shaped film cooling structure can be manufactured.
また、この発明によれば、ひさし形フイルム冷却構造を
有する複雑な構造の尾筒が簡単に製造できるので、これ
をガスタービン用燃焼器の内筒に接続して、ガスタービ
ンの耐久性を向上させることができる。Further, according to the present invention, since a tail pipe having a complicated structure having an eaves-shaped film cooling structure can be easily manufactured, it is connected to the inner cylinder of the gas turbine combustor to improve the durability of the gas turbine. Can be made.
第１図は、この発明による方法で製造されるガスタービ
ンの燃焼器部分を一部切欠して示す側面図、第２図は尾
筒の外形を示す側面図、第３図は第２図の要部を示す部
分縦断面図、第４図は上下２つ割りのプレス型を示す縦
断面図、第５図は尾筒の製造工程を説明するために第２
図のＶ−Ｖ線に沿って示す断面図、第６図は従来の一般
的な尾筒を説明するための燃焼器部分を一部切欠して示
す側面図、第７図は第６図のVII−VII線に沿った線図、
第８図は第６図のVIII−VIII線に沿った線図、第９図は
従来の内筒の冷却構造を尾筒に適用する状態を断面にて
示す線図である。 ３…タービン、５…取付段部、７…空気孔、８…ひさ
し、８ａ…ひさしの上半部、８ｂ…ひさしの下半部、１
１…内筒、１２…尾筒、１２ａ…尾筒の上半体、１２ｂ
…尾筒の下半体、２１…冷却空気、Ｆ…接合面、Ｇ…燃
焼ガス、Ｘ…流れ方向、Ｙ…直交する面。FIG. 1 is a side view showing a combustor portion of a gas turbine manufactured by the method according to the present invention with a part thereof cut away, FIG. 2 is a side view showing the outer shape of a transition piece, and FIG. FIG. 4 is a vertical sectional view showing a press die which is divided into upper and lower halves, and FIG. 5 is a second vertical sectional view showing a manufacturing process of a transition piece.
FIG. 6 is a cross-sectional view taken along the line V-V in FIG. 6, FIG. 6 is a side view showing a combustor portion partially cut away for explaining a conventional general transition piece, and FIG. 7 is FIG. VII-VII line diagram,
FIG. 8 is a diagram taken along the line VIII-VIII in FIG. 6, and FIG. 9 is a diagrammatic sectional view showing a state in which the conventional cooling structure for the inner cylinder is applied to the transition piece. 3 ... Turbine, 5 ... Mounting step, 7 ... Air hole, 8 ... Eaves, 8a ... Upper half of eaves, 8b ... Lower half of eaves, 1
1 ... inner cylinder, 12 ... tail cylinder, 12a ... upper half of tail cylinder, 12b
... lower half of the transition piece, 21 ... cooling air, F ... joining surface, G ... combustion gas, X ... flow direction, Y ... planes orthogonal to each other.
───────────────────────────────────────────────────── フロントページの続き (56)参考文献 特開 昭56−25622（ＪＰ，Ａ) 特開 昭50−25918（ＪＰ，Ａ) 実開 昭58−154367（ＪＰ，Ｕ) 実開 昭56−89570（ＪＰ，Ｕ) 特公 昭59−41010（ＪＰ，Ｂ２) ─────────────────────────────────────────────────── ─── Continuation of the front page (56) Reference JP-A-56-25622 (JP, A) JP-A-50-25918 (JP, A) Actual opening Sho-58-154367 (JP, U) Actual opening Sho-56- 89570 (JP, U) JP 59-41010 (JP, B2)
Claims (2)
ビンへ導く尾筒の製造方法であって、平板状部材を上下
２つ割りの型に入れて燃焼ガスの流れ方向に沿いかつ上
記燃焼器の内筒と上記タービンとの間にまたがって連続
した曲線状の接合面を有するとともに上記燃焼ガスの流
れ方向の横断面が順次異なる尾筒上半体と下半体とをそ
れぞれプレス加工する工程と、上記尾筒の上半体と下半
体のプレス加工時に上記燃焼ガスの流れ方向にほぼ直交
する面内で上記尾筒の上半体および下半体の各全周にわ
たり外方へ突出するひさし取付段部を一体形成する工程
と、上記ひさし取付段部に連なって上記燃焼ガスの流れ
方向にほぼ直交する面内で上記尾筒の上半体および下半
体の各全周にわたり外方へ突出する空気導入段部を一体
形成する工程と、この空気導入段部に複数の空気孔を形
成する工程と、上記プレス成形した尾筒の上半体および
下半体のつば部を上記曲線状の接合面に沿って切断して
上記燃焼器の内筒と上記タービンとの間にまたがる連続
した尾筒の上半体と下半体とをそれぞれ形成する工程
と、帯状板材をプレス加工して上記尾筒の上半体および
下半体の各ひさし取付段部の内周面に接合されるひさし
の上半部および下半部をそれぞれ成形する工程と、この
尾筒の上半体および下半体の各取付段部にそれぞれ対応
する上記ひさしの上半部と下半部とを接合する工程と、
上記ひさしの上半部および下半部を接合した尾筒の上半
体と下半体とを燃焼ガスの流れ方向に沿った接合面で接
合させる工程とを具備したことを特徴とするガスタービ
ン用燃焼器の尾筒の製造方法。1. A method of manufacturing a transition piece which is connected to an inner cylinder of a combustor and guides combustion gas to a turbine, wherein a flat plate-shaped member is put in a mold which is divided into upper and lower halves along a flow direction of the combustion gas. An upper half body and a lower half body of the transition piece having a continuous curved joint surface extending between the inner cylinder of the combustor and the turbine and having different transverse cross sections in the flow direction of the combustion gas are pressed respectively. During the process of working and pressing the upper and lower halves of the transition piece, the outer circumference of each of the upper and lower halves of the transition piece is outside in a plane substantially orthogonal to the flow direction of the combustion gas. The step of integrally forming the eaves mounting step portion projecting toward one side, and all of the upper half body and the lower half body of the transition piece in a plane that is continuous with the eaves mounting step portion and is substantially orthogonal to the flow direction of the combustion gas. A step of integrally forming an air introduction step portion projecting outward over the circumference, A step of forming a plurality of air holes in the air introduction step of the, and the upper half and lower half of the press-molded transition piece is cut along the curved joint surface of the combustor. Each step of forming a continuous upper half body and a lower half body of the transition piece extending between the inner cylinder and the turbine, and pressing the strip plate material to form the upper half body and the lower half body of the transition piece, respectively. Forming the upper half and lower half of the eaves to be joined to the inner peripheral surface of the eaves mounting step, and the eaves corresponding to the respective mounting steps of the upper half and lower half of the transition piece. A step of joining the upper half and the lower half of
And a step of joining an upper half body and a lower half body of the transition piece, which joins the upper half portion and the lower half portion of the eaves, at a joint surface along a flow direction of combustion gas. Of manufacturing tail cylinder of combustor for automobile.
プレス成形後に機械加工により、尾筒の空気導入段部に
空気孔を形成する特許請求の範囲第１項に記載のガスタ
ービン用燃焼器の尾筒の製造方法。2. Simultaneously with press-molding the transition piece, or
The method for manufacturing a transition piece of a combustor for a gas turbine according to claim 1, wherein air holes are formed in the air introduction step portion of the transition piece by press working after press forming.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60071056A JPH0637976B2 (en) | 1985-04-05 | 1985-04-05 | Method of manufacturing transition piece of combustor for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60071056A JPH0637976B2 (en) | 1985-04-05 | 1985-04-05 | Method of manufacturing transition piece of combustor for gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS61231332A JPS61231332A (en) | 1986-10-15 |
| JPH0637976B2 true JPH0637976B2 (en) | 1994-05-18 |
Family
ID=13449478
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP60071056A Expired - Lifetime JPH0637976B2 (en) | 1985-04-05 | 1985-04-05 | Method of manufacturing transition piece of combustor for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0637976B2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8015818B2 (en) * | 2005-02-22 | 2011-09-13 | Siemens Energy, Inc. | Cooled transition duct for a gas turbine engine |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3826082A (en) * | 1973-03-30 | 1974-07-30 | Gen Electric | Combustion liner cooling slot stabilizing dimple |
| US4292801A (en) * | 1979-07-11 | 1981-10-06 | General Electric Company | Dual stage-dual mode low nox combustor |
| JPS5689570U (en) * | 1979-12-07 | 1981-07-17 | ||
| JPS58154367U (en) * | 1982-04-08 | 1983-10-15 | 三菱重工業株式会社 | Cooling structure for gas turbines, etc. |
-
1985
- 1985-04-05 JP JP60071056A patent/JPH0637976B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPS61231332A (en) | 1986-10-15 |
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