JP2007224731A - Tail pipe seal structure of gas turbine combustor - Google Patents

Tail pipe seal structure of gas turbine combustor Download PDF

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JP2007224731A
JP2007224731A JP2006043530A JP2006043530A JP2007224731A JP 2007224731 A JP2007224731 A JP 2007224731A JP 2006043530 A JP2006043530 A JP 2006043530A JP 2006043530 A JP2006043530 A JP 2006043530A JP 2007224731 A JP2007224731 A JP 2007224731A
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gas turbine
seal member
tail
turbine combustor
seal
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JP4174615B2 (en
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Tomoko Hagari
智子 葉狩
Hidekazu Iwasaki
英和 岩崎
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Kawasaki Heavy Industries Ltd
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Kawasaki Heavy Industries Ltd
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Abstract

<P>PROBLEM TO BE SOLVED: To provide a tail pipe seal structure of a gas turbine combustor capable of preventing shortening of the service life of respective members, by restraining an increase in an amount of emission of NOx (nitrogen oxides), as a result of restraining reduction in output and engine performance, by preventing leakage of compressed air to the turbine side from a compressor. <P>SOLUTION: This tail pipe seal structure U of the gas turbine combustor is formed by arranging an annular seal member 3 having an opposed surface with an outlet end part peripheral surface of a tail pipe 1, in a connecting part between the tail pipe 1 and a turbine inlet part 2 of the gas turbine combustor formed by annularly arranging a plurality of combustors. A peripheral end part seal member 4 for preventing the inflow of air in the peripheral direction, is arranged in a clearance L2 between the opposed surface H of the annular seal member 3 and the outlet end part peripheral surface of the tail pipe 1. <P>COPYRIGHT: (C)2007,JPO&INPIT

Description

本発明は、ガスタービン燃焼器の尾筒シール構造に関する。さらに詳しくは、燃焼器の尾筒とタービンとの接続部におけるタービン側への圧縮空気の漏洩を防止するガスタービン燃焼器の尾筒シール構造に関する。   The present invention relates to a transition piece seal structure for a gas turbine combustor. More specifically, the present invention relates to a transition structure for a tail tube seal of a gas turbine combustor that prevents leakage of compressed air to the turbine side at a connection portion between the tail tube of the combustor and the turbine.

ガスタービンは、圧縮機と燃焼器とタービンとを備えて構成されており、カン型およびカンニュラ型の燃焼器構造の場合、複数の円筒状の燃焼器が同一円周上に並べられ、その燃焼器出口は尾筒を介して円環状のタービン入口と接続されている。   A gas turbine includes a compressor, a combustor, and a turbine. In the case of can-type and cannula-type combustor structures, a plurality of cylindrical combustors are arranged on the same circumference, and the combustion is performed. The vessel outlet is connected to an annular turbine inlet via a tail cylinder.

図９に、ガスタービン燃焼器とタービンとの接続部を断面図により示す。図９に示すように、同接続部は、全体は図示しない燃焼器にて発生する燃焼ガスをタービン側に送る通路としての尾筒１０１と、タービン入口部１０２と、尾筒１０１の出口端部周囲に設けられたフランジ１０３と、尾筒１０１およびタービン静翼１０４を支持するノズルサポート１０５と、タービン流路を形成する外径側および内径側流路形成部材１０６、１０７と、前記フランジ１０３と各流路形成部材１０６、１０７との間に介装された外径側および内径側の環状シール部材１０８、１０９とを備える。   In FIG. 9, the connection part of a gas turbine combustor and a turbine is shown with sectional drawing. As shown in FIG. 9, the connecting portion is generally composed of a tail cylinder 101 as a passage for sending combustion gas generated in a combustor (not shown) to the turbine side, a turbine inlet portion 102, and an outlet end portion of the tail cylinder 101. A flange 103 provided around, a nozzle support 105 that supports the transition piece 101 and the turbine vane 104, outer diameter side and inner diameter side flow path forming members 106 and 107 that form a turbine flow path, and the flange 103; Outer diameter side and inner diameter side annular seal members 108, 109 interposed between the flow path forming members 106, 107 are provided.

ここで、ガスタービンの圧縮機からの圧縮空気は尾筒１０１の周囲に形成された高圧室（不図示である）に送られ、ここで尾筒１０１を冷却した後、燃焼器に送られるものとされるが、その一部は前記高圧室からシール部材１０８、１０９に設けられた細孔１０８ａ、１０９ａを介してタービン側に排出される。これにより、尾筒出口端部１０１ａが冷却されるとともに、前記尾筒１０１からタービン静翼１０４にかけての流路にて発生が懸念される燃焼ガスの巻き込みが防止される。   Here, the compressed air from the compressor of the gas turbine is sent to a high-pressure chamber (not shown) formed around the tail cylinder 101, where the tail cylinder 101 is cooled and then sent to the combustor. However, a part of the exhaust is discharged from the high-pressure chamber to the turbine side through the pores 108a and 109a provided in the seal members 108 and 109. Thus, the transition piece outlet end portion 101a is cooled, and combustion gas that is likely to be generated in the flow path from the transition piece 101 to the turbine stationary blade 104 is prevented.

ところが、前記燃焼器とタービンとの接続部においては、周方向に隣り合う各尾筒１０１の間隙および各尾筒１０１と環状シール部材１０８、１０９との間隙等から前記高圧室内の圧縮空気が燃焼や冷却に寄与することなくタービン側（タービン入口部１０２内）に漏れることがあり（下記特許文献１、２、３参照）、この結果、出力およびエンジン性能が低下するという問題が生じる。   However, in the connecting portion between the combustor and the turbine, the compressed air in the high-pressure chamber burns from the gaps between the tail cylinders 101 adjacent to each other in the circumferential direction, the gaps between the tail cylinders 101 and the annular seal members 108 and 109, and the like. Otherwise, it may leak to the turbine side (inside the turbine inlet portion 102) without contributing to cooling (see Patent Documents 1, 2, and 3 below). As a result, there arises a problem that output and engine performance are deteriorated.

これにより、所要の出力およびエンジン性能を維持するために、燃焼ガス温度を上昇させる必要が生じ、その結果、ＮＯｘ（窒素酸化物）の排出量の増大を招いたり、燃焼器や尾筒等の各部材が短寿命化するといった問題が生じる。
特開２００４−１５６５４３号公報 特開２００４−３０１１１５号公報 特開２０００−１３６７３１号公報 As a result, in order to maintain the required output and engine performance, it is necessary to raise the combustion gas temperature. As a result, the amount of NOx (nitrogen oxide) emission increases, the combustor, the tail cylinder, etc. There arises a problem that each member has a short life.
JP 2004-156543 A JP 2004-301115 A JP 2000-136731 A

本発明はかかる従来技術の課題に鑑みなされたものであって、圧縮機からの圧縮空気のタービン側への漏洩を防止して出力およびエンジン性能の低下を抑え、結果として、ＮＯｘ（窒素酸化物）の排出量の増大を抑え、各部材の短寿命化を防ぐことを可能とするガスタービン燃焼器の尾筒シール構造を提供することを目的としている。   The present invention has been made in view of the problems of the prior art, and prevents leakage of compressed air from the compressor to the turbine side to suppress a decrease in output and engine performance. As a result, NOx (nitrogen oxide) It is an object of the present invention to provide a tail tube seal structure for a gas turbine combustor that can suppress an increase in the discharge amount of the gas turbine combustor and prevent the life of each member from being shortened.

本発明のガスタービン燃焼器の尾筒シール構造は、複数の燃焼器を環状に配設してなるガスタービン燃焼器の尾筒とタービン入口部との接続部に、前記尾筒出口端部周面との対向面を有する環状シール部材を設けてなるガスタービン燃焼器の尾筒シール構造であって、前記環状シール部材の前記対向面と前記尾筒出口端部の外径側および内径側の面、つまり周面との間隙に、周方向の空気流入を防止する周端部シール部材を配設してなることを特徴とする。   In the gas turbine combustor tail pipe seal structure according to the present invention, the periphery of the tail pipe outlet end portion is provided at a connection portion between the tail cylinder and the turbine inlet portion of the gas turbine combustor formed by annularly arranging a plurality of combustors. A gas turbine combustor tail tube seal structure provided with an annular seal member having a surface facing the surface, the outer surface of the annular seal member and the outer diameter side and the inner diameter side of the tail tube outlet end portion A peripheral end seal member for preventing air inflow in the circumferential direction is provided in a gap between the surface and the peripheral surface.

本発明のガスタービン燃焼器の尾筒シール構造においては、周端部シール部材は、環状シール部材に沿うように湾曲形成されたシール辺と、該シール辺の一端から半径方向に折り曲げ形成された係止爪とを含むＬ字状部材とされ、 前記係止爪が、環状シール部材の尾筒出口端部周面との対向面に形成された嵌合溝に嵌合されていたり、環状シール部材に沿うように湾曲形成されたシール辺と、該シール辺の一側端から半径方向に突出形成された係止爪とを含む変形Ｔ字状部材とされ、前記係止爪が、環状シール部材の尾筒出口端部周面との対向面に形成された嵌合溝に嵌合されていたりするのが好ましい。   In the transition tube seal structure of the gas turbine combustor according to the present invention, the peripheral end seal member is formed to be bent along the annular seal member and to be bent in the radial direction from one end of the seal side. An L-shaped member including a locking claw, and the locking claw is fitted in a fitting groove formed on a surface of the annular seal member facing the peripheral surface of the tail tube outlet end, or an annular seal A deformed T-shaped member including a seal side curved so as to follow the member and a locking claw protruding from one side end of the seal side in the radial direction, the locking claw being an annular seal It is preferable that the member is fitted in a fitting groove formed on a surface facing the peripheral surface of the end portion of the transition piece outlet of the member.

また、本発明のガスタービン燃焼器の尾筒シール構造においては、同一形状とされた周端部シール部材が、尾筒の四隅に配設されてなるのが好ましい。   Moreover, in the transition piece seal structure of the gas turbine combustor according to the present invention, it is preferable that circumferential end seal members having the same shape are disposed at the four corners of the transition piece.

本発明のガスタービン燃焼器の尾筒シール構造は、前記の如く構成されているので、尾筒とタービンとの接続部におけるタービン側への圧縮空気の漏洩を防止でき、出力およびエンジン性能が向上するという優れた効果が得られる。   Since the transition structure of the transition of the gas turbine combustor according to the present invention is configured as described above, leakage of compressed air to the turbine side at the connection between the transition and the turbine can be prevented, and output and engine performance are improved. An excellent effect is obtained.

また、漏洩空気によるタービン入口温度の低下がないので、燃焼ガス温度の上昇を抑えることができ、ＮＯｘ（窒素酸化物）の低減が図られるとともに、尾筒などの部品の長寿命化が図られるという優れた効果が得られる。   Further, since there is no decrease in the turbine inlet temperature due to leaked air, an increase in the combustion gas temperature can be suppressed, NOx (nitrogen oxide) can be reduced, and the life of parts such as the tail tube can be extended. An excellent effect is obtained.

以下、添付図面を参照しながら本発明を実施形態に基づいて説明するが、本発明はかかる実施形態のみに限定されるものではない。   Hereinafter, although the present invention is explained based on an embodiment, referring to an accompanying drawing, the present invention is not limited only to this embodiment.

実施形態１
図１に、本発明の実施形態１に係るガスタービン燃焼器の尾筒シール構造を概略図により示す。図２に、その斜視図を示す。 Embodiment 1
FIG. 1 is a schematic view showing a transition structure of a transition piece of a gas turbine combustor according to Embodiment 1 of the present invention. FIG. 2 shows a perspective view thereof.

シール構造Ｕは、図１および図２に示すように、図示しないガスタービン燃焼器からタービンに燃焼ガスを送る通路である尾筒１と、タービン側の燃焼ガスの流入路であるタービン入口部２との接続部をシールするものとされる。   As shown in FIGS. 1 and 2, the seal structure U includes a tail tube 1 that is a passage for sending combustion gas from a gas turbine combustor (not shown) to the turbine, and a turbine inlet 2 that is an inflow passage for combustion gas on the turbine side. It is assumed that the connection part is sealed.

すなわち、シール構造Ｕは、尾筒１の燃焼ガスの出口開口１ａとタービン入口部２の入口開口２ａとの接続部をシールするように尾筒１の出口端部周面との対向面を有する環状シール部材３１、３２をそれぞれ配設するとともに、周方向に隣接する各尾筒１の出口端部の間隙（図３参照。以下、周方向間隙という）Ｌ１から尾筒１の出口端部周面と環状シール部材３１、３２の対向面との間隙Ｌ２（図３参照。以下、径方向間隙という）に回り込む圧縮機からの圧縮空気の流れを遮断するように、前記径方向間隙Ｌ２の所定箇所に板状シール部材４、４を配設してなるものとされる。なお、本明細書では円環状のタービン入口部２の形状に基づいて周方向および径方向を規定している。 That is, the seal structure U has a surface facing the peripheral surface of the outlet end portion of the tail cylinder 1 so as to seal the connection portion between the combustion gas outlet opening 1 a of the tail cylinder 1 and the inlet opening 2 a of the turbine inlet portion 2. The annular seal members 3 1 , 3 2 are respectively disposed, and the outlet end of the tail tube 1 from the gap (see FIG. 3; hereinafter referred to as the circumferential gap) L1 between the outlet ends of the tail tubes 1 adjacent in the circumferential direction. The radial direction so as to block the flow of compressed air from the compressor that wraps around a gap L2 (see FIG. 3; hereinafter referred to as a radial gap) between the circumferential surface of the portion and the opposed surfaces of the annular seal members 3 1 , 3 2 . The plate-like seal members 4 and 4 are arranged at predetermined positions of the gap L2. In the present specification, the circumferential direction and the radial direction are defined based on the shape of the annular turbine inlet 2.

つまり、図３に示すように、各尾筒１の出口開口１ａは概略方形とされて、円環状のタービン入口部２の入口開口２ａと対向するよう同一円周上に並べられている。ここで、尾筒１の出口開口１ａの周方向両側縁には嵌合部１ｂ（図２参照）が設けられており、周方向に並ぶ各尾筒１の嵌合部１ｂを嵌め合わせて各尾筒１の出口端部の隙間をシールするものとされている。しかしながら、嵌合部１ｂ以外の箇所では周方向に並ぶ各尾筒１の間に若干の間隙Ｌ１が存在し、図２に示すように、この周方向間隙Ｌ１と前記径方向間隙Ｌ２とが通じているために圧縮機からの圧縮空気が周方向間隙Ｌ１から径方向間隙Ｌ２を介してタービン側に漏れる。なお、径方向間隙Ｌ２は、背景技術にて示したように、尾筒１の出口端部を冷却するための空気流路を確保するよう設けられるものとされる。   That is, as shown in FIG. 3, the outlet openings 1 a of the tail cylinders 1 are substantially square and are arranged on the same circumference so as to face the inlet openings 2 a of the annular turbine inlet 2. Here, the fitting part 1b (refer FIG. 2) is provided in the circumferential direction both-sides edge of the exit opening 1a of the transition piece 1, The fitting part 1b of each transition piece 1 arranged in the circumferential direction is fitted, and each is fitted. The gap at the exit end of the transition piece 1 is sealed. However, there is a slight gap L1 between the tail cylinders 1 arranged in the circumferential direction at locations other than the fitting portion 1b. As shown in FIG. 2, the circumferential gap L1 and the radial gap L2 communicate with each other. Therefore, the compressed air from the compressor leaks from the circumferential gap L1 to the turbine side via the radial gap L2. The radial gap L2 is provided so as to secure an air flow path for cooling the outlet end portion of the transition piece 1 as shown in the background art.

また、後掲のように、環状シール部材３は所定長さ（実施形態では尾筒１の出口端部の周方向長さと対応する長さ）に分割された分割体から構成されているために（図４および図５参照）、各分割体の対向端面の間隙からも径方向間隙Ｌ２に圧縮空気が漏れる。   Further, as described later, the annular seal member 3 is constituted by a divided body divided into a predetermined length (in the embodiment, a length corresponding to the circumferential length of the outlet end portion of the tail tube 1). (Refer to FIG. 4 and FIG. 5), compressed air leaks from the gap between the opposed end faces of each divided body into the radial gap L2.

これらの事情から、圧縮空気のタービン側への漏洩を防止するために、実施形態では板状シール部材４、４を前記径方向間隙Ｌ２の所定箇所に設けるものとしている。   From these circumstances, in order to prevent leakage of compressed air to the turbine side, in the embodiment, the plate-like seal members 4 and 4 are provided at predetermined positions of the radial gap L2.

図４〜図６に、環状シール部材３の詳細を示す。図４は外径側の環状シール部材３１の二面図であり、図５は内径側の環状シール部材３２の二面図である。図６は環状シール部材を模式化した斜視図である。 4 to 6 show the details of the annular seal member 3. Figure 4 is a two-sided view of an annular sealing member 3 1 of the outer diameter side, Fig 5 is a two-sided view of an annular sealing member 3 2 on the inner diameter side. FIG. 6 is a perspective view schematically showing the annular seal member.

環状シール部材３は、図１に示すように、尾筒１の出口開口１ａの外径側および内径側端面から入口に向けて所定距離後退させて尾筒１の出口端部の外径側および内径側に設けられたフランジ状部（以下、尾筒フランジという）５と、ノズルサポート６の一部分を構成し、第１段のタービン静翼（以下、単に静翼という）７を外径側および内径側から支持するタービン流路形成部材８、９の開口端部８ａ、９ａとの間に介装されている。   As shown in FIG. 1, the annular seal member 3 is retracted by a predetermined distance from the outer diameter side and inner diameter side end surfaces of the outlet opening 1 a of the tail tube 1 toward the inlet, and the outer diameter side of the outlet end portion of the tail tube 1 and A flange-like portion (hereinafter referred to as a transition piece flange) 5 provided on the inner diameter side and a part of the nozzle support 6 are configured, and a first stage turbine stationary blade (hereinafter simply referred to as a stationary blade) 7 is connected to the outer diameter side and It is interposed between the open ends 8a, 9a of the turbine flow path forming members 8, 9 supported from the inner diameter side.

ここで、環状シール部材３は、図４および図５に示すように、所定長さに切断された各分割体から構成されており、コの字断面の本体３ａ（図６参照）と、本体３ａの尾筒対向面Ｈと垂直な一方外面に形成された、尾筒フランジ５の根元部分の出口側に周方向に延びるように設けられた断面方形の溝５ａと嵌合する突条３ｂと、本体３ａの他方外面に形成された、タービン流路形成部材８、９の端部８ａ、９ａと嵌合する溝３ｃとを有してなる。   Here, as shown in FIG. 4 and FIG. 5, the annular seal member 3 is composed of each divided body cut into a predetermined length, and a main body 3 a (see FIG. 6) having a U-shaped cross section, and a main body A ridge 3b fitted on a groove 5a having a square cross section provided on one outer surface perpendicular to the tail tube facing surface H of 3a and extending in the circumferential direction on the outlet side of the root portion of the tail tube flange 5; The groove 3c is formed on the other outer surface of the main body 3a and is fitted to the end portions 8a, 9a of the turbine flow path forming members 8, 9.

さらに、環状シール部材３は、図６に示すように、後掲の板状シール部材４の係止爪部４ｂと嵌合する係止溝３ｄが本体３ａの尾筒１出口端部周面との対向面Ｈに設けられてなるものとされる。また、図４および図５にて符号３ｅが付された部位は環状シール部材３を尾筒１に固定するためのフランジであり、符号３ｆが付された部位は環状シール部材３と尾筒１との位置関係を決めるためのフランジである。   Further, as shown in FIG. 6, the annular seal member 3 has a locking groove 3 d that fits with a locking claw portion 4 b of the plate-like sealing member 4 described later, and a peripheral surface of the outlet end portion of the transition piece 1 of the main body 3 a. It is supposed that it is provided on the opposite surface H of the. 4 and 5, a portion denoted by reference numeral 3 e is a flange for fixing the annular seal member 3 to the tail tube 1, and a portion denoted by reference numeral 3 f is the annular seal member 3 and the tail tube 1. It is a flange for deciding the positional relationship.

次に、板状シール部材４を説明する。   Next, the plate-like seal member 4 will be described.

図７に、板状シール部材４の詳細を示す。板状シール部材４は耐熱性素材からなり、本体４ａと、この本体４ａの一側端を垂直に折り曲げるようにして設けられた、環状シール部材３の係止溝３ｄと嵌合して板状シール部材４を固定する係止爪部４ｂとを有する断面湾曲Ｌ字形の部材とされている。ここで、板状シール部材４は、異種部品点数の削減および組間違い等の防止のために全て同じ寸法、形状とするのが好ましい。   FIG. 7 shows details of the plate-like seal member 4. The plate-like seal member 4 is made of a heat-resistant material, and is fitted into a plate-like shape by fitting with a main body 4a and a locking groove 3d of the annular seal member 3 provided so that one end of the main body 4a is bent vertically. The member has an L-shaped cross section having a locking claw portion 4b for fixing the seal member 4. Here, it is preferable that the plate-like seal members 4 have the same size and shape in order to reduce the number of different parts and prevent assembly errors.

しかして、このような板状シール部材４は、図２および図３に示すとおり、周方向間隙Ｌ１および環状シール部材３の各分割体の対向端面の間隙（以下、周方向間隙Ｌ１等という）から径方向間隙Ｌ２への圧縮空気の流入を防止するように、外径側および内径側の径方向間隙Ｌ２の尾筒１の出口端部の周方向両端部に配設されるものとされており、これによって、周方向間隙Ｌ１等から径方向間隙Ｌ２を通ってタービン入口部２内に流入する圧縮空気の漏洩を防止することが可能となる。   Thus, as shown in FIGS. 2 and 3, such a plate-shaped sealing member 4 includes a circumferential gap L1 and a gap between the opposed end faces of each divided body of the annular sealing member 3 (hereinafter referred to as a circumferential gap L1 and the like). In order to prevent inflow of compressed air from the outer diameter side to the radial gap L2, the outer diameter side and the inner diameter side radial gap L2 are arranged at both ends in the circumferential direction of the outlet end portion of the transition piece 1. Accordingly, it is possible to prevent leakage of compressed air flowing into the turbine inlet 2 from the circumferential gap L1 and the like through the radial gap L2.

したがって、圧縮空気のタービン側への漏洩による出力およびエンジン性能の低下が防止されて、所望の出力レベルを維持するために燃焼ガス温度を上昇させる必要がなくなり、燃焼ガス中のＮＯｘ（窒素酸化物）排出量を低減することができるとともに、ガスタービン燃焼器および尾筒等の各部材を長寿命化することが可能となる。   Accordingly, a decrease in output and engine performance due to leakage of compressed air to the turbine side is prevented, and there is no need to increase the combustion gas temperature in order to maintain a desired output level. NOx (nitrogen oxides) in the combustion gas ) Emissions can be reduced, and the life of each member such as the gas turbine combustor and the tail tube can be extended.

実施形態２
次に、図８を参照して本発明の実施形態２を説明する。実施形態２は実施形態１を改変してなるものであり、板状シール部材４を改変してなるものとされる。実施形態２のその余の構成は実施形態１と同様であるため、その詳細説明は省略する。 Embodiment 2
Next, Embodiment 2 of the present invention will be described with reference to FIG. The second embodiment is obtained by modifying the first embodiment, and is obtained by modifying the plate-like seal member 4. Since the remaining configuration of the second embodiment is the same as that of the first embodiment, detailed description thereof is omitted.

すなわち、図８に示すように、実施形態２の板状シール部材４Ａは、係止爪部４ｂが本体４ａの一側端寄りに設けられた断面変形Ｔ字形の部材とされている。このように、板状シール部材４Ａを断面変形Ｔ字形とすることによって、係止爪部４ｂの強度を高めることが可能であり、シール構造をより堅牢なものとすることが可能となる。   That is, as shown in FIG. 8, the plate-shaped sealing member 4A according to the second embodiment is a T-shaped member having a deformed cross section in which the locking claw portion 4b is provided near one end of the main body 4a. Thus, by making the plate-shaped seal member 4A into a T-shaped cross-sectional deformation, the strength of the locking claw portion 4b can be increased, and the seal structure can be made more robust.

以上、本発明を各実施形態により説明したが、本発明はこれに限られるものではなく、例えば、板状シール部材の係止爪部と嵌合する係止溝を環状シール部材に設ける代わりに、尾筒の出口端部の外径側および内径側の環状シール部材対向面、つまり出口端部周面に設けることも可能であり、この場合にも、前記各実施形態と同様の作用効果を達成することが可能である。   As mentioned above, although this invention was demonstrated by each embodiment, this invention is not restricted to this, For example, instead of providing the latching groove | channel which fits the latching claw part of a plate-shaped seal member in an annular seal member In addition, it is also possible to provide the annular seal member facing surface on the outer diameter side and inner diameter side of the outlet end portion of the tail tube, that is, the peripheral surface of the outlet end portion. It is possible to achieve.

本発明は、ガスタービン燃焼器とタービンとの接続部分に適用できる。   The present invention can be applied to a connecting portion between a gas turbine combustor and a turbine.

本発明の実施形態１に係るガスタービン燃焼器の尾筒シール構造の概略図である。It is the schematic of the tail-tube seal structure of the gas turbine combustor which concerns on Embodiment 1 of this invention. 同シール構造の概略斜視図である。It is a schematic perspective view of the seal structure. 同シール構造の要部詳細を示す模式図である。It is a schematic diagram which shows the principal part detail of the seal structure. 外径側の環状シール部材の詳細を示す２面図であり、同（ａ）は正面図、同（ｂ）は側面図である。It is a 2nd page figure which shows the detail of the annular seal member by the side of an outer diameter, The same (a) is a front view, The same (b) is a side view. 内径側の環状シール部材の詳細を示す２面図であり、同（ａ）は正面図、同（ｂ）は側面図である。It is a 2nd page figure which shows the detail of the annular seal member of an internal diameter side, The same (a) is a front view, The same (b) is a side view. 環状シール部材を模式化した斜視図である。It is the perspective view which modeled the annular seal member. 実施形態１の板状シール部材の詳細を示す２面図であり、同（ａ）は正面図、同（ｂ）は側面図である。It is a 2nd page figure which shows the detail of the plate-shaped sealing member of Embodiment 1, (a) is a front view, (b) is a side view. 実施形態２の板状シール部材の詳細を示す２面図であり、同（ａ）は正面図、同（ｂ）は側面図である。It is a 2nd page figure which shows the detail of the plate-shaped sealing member of Embodiment 2, (a) is a front view, (b) is a side view. 従来のガスタービン燃焼器の尾筒のシール構造の概略構成を示す部分断面図である。It is a fragmentary sectional view which shows schematic structure of the seal structure of the tail cylinder of the conventional gas turbine combustor.

符号の説明Explanation of symbols

Ｕ シール構造
Ｌ１ 周方向間隙
Ｌ２ 径方向間隙
１ 尾筒
２ タービン入口部
３ 環状シール部材
４ 板状シール部材
U seal structure L1 circumferential gap L2 radial gap 1 tail cylinder 2 turbine inlet 3 annular seal member 4 plate seal member

Claims (4)

複数の燃焼器を環状に配設してなるガスタービン燃焼器の尾筒とタービン入口部との接続部に、前記尾筒出口端部周面との対向面を有する環状シール部材を設けてなるガスタービン燃焼器の尾筒シール構造であって、
前記環状シール部材の前記対向面と前記尾筒出口端部周面との間隙に、周方向の空気流入を防止する周端部シール部材を配設してなることを特徴とするガスタービン燃焼器の尾筒シール構造。 An annular seal member having a surface opposed to the peripheral surface of the end portion of the tail tube outlet is provided at a connection portion between the tail tube of the gas turbine combustor formed by arranging a plurality of combustors in a ring shape and the turbine inlet portion. A gas turbine combustor tail tube seal structure,
A gas turbine combustor comprising a circumferential end seal member for preventing air inflow in a circumferential direction in a gap between the facing surface of the annular seal member and the peripheral surface of the end portion of the transition piece outlet. Tail tube seal structure. 周端部シール部材は、環状シール部材に沿うように湾曲形成されたシール辺と、該シール辺の一端から半径方向に折り曲げ形成された係止爪とを含むＬ字状部材とされ、
前記係止爪が、環状シール部材の尾筒出口端部周面との対向面に形成された嵌合溝に嵌合されて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の尾筒シール構造。 The peripheral end seal member is an L-shaped member including a seal side that is curved so as to follow the annular seal member, and a locking claw that is bent in a radial direction from one end of the seal side,
The tail of the gas turbine combustor according to claim 1, wherein the engaging claw is fitted in a fitting groove formed on a surface of the annular seal member facing the peripheral surface of the end portion of the tail tube outlet. Tube seal structure. 周端部シール部材は、環状シール部材に沿うように湾曲形成されたシール辺と、該シール辺の一側端から半径方向に突出形成された係止爪とを含む変形Ｔ字状部材とされ、
前記係止爪が、環状シール部材の尾筒出口端部周面との対向面に形成された嵌合溝に嵌合されて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の尾筒シール構造。 The peripheral end seal member is a deformed T-shaped member including a seal side that is curved so as to follow the annular seal member, and a locking claw that is formed to project from one side end of the seal side in the radial direction. ,
The tail of the gas turbine combustor according to claim 1, wherein the engaging claw is fitted in a fitting groove formed on a surface of the annular seal member facing the peripheral surface of the end portion of the tail tube outlet. Tube seal structure. 同一形状とされた周端部シール部材が、尾筒の四隅に配設されて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の尾筒シール構造。   The tail end seal structure for a gas turbine combustor according to claim 1, wherein the peripheral end seal members having the same shape are disposed at four corners of the end case.
JP2006043530A 2006-02-21 2006-02-21 Gas turbine combustor tail tube seal structure Active JP4174615B2 (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170276002A1 (en) * 2016-03-24 2017-09-28 General Electric Company Transition duct assembly
CN108291721A (en) * 2015-11-26 2018-07-17 川崎重工业株式会社 Intermediate structure

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP7348784B2 (en) 2019-09-13 2023-09-21 三菱重工業株式会社 Outlet seals, outlet seal sets, and gas turbines

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108291721A (en) * 2015-11-26 2018-07-17 川崎重工业株式会社 Intermediate structure
US20170276002A1 (en) * 2016-03-24 2017-09-28 General Electric Company Transition duct assembly
US10260360B2 (en) * 2016-03-24 2019-04-16 General Electric Company Transition duct assembly

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