JPH08285284A - Combustor structure for gas turbine - Google Patents
Combustor structure for gas turbineInfo
- Publication number
- JPH08285284A JPH08285284A JP8380695A JP8380695A JPH08285284A JP H08285284 A JPH08285284 A JP H08285284A JP 8380695 A JP8380695 A JP 8380695A JP 8380695 A JP8380695 A JP 8380695A JP H08285284 A JPH08285284 A JP H08285284A
- Authority
- JP
- Japan
- Prior art keywords
- combustor liner
- combustor
- transition piece
- gas
- spring seal
- 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.)
- Pending
Links
- 239000007789 gas Substances 0.000 claims abstract description 78
- 238000001816 cooling Methods 0.000 claims abstract description 66
- 239000002184 metal Substances 0.000 claims abstract description 48
- 229910052751 metal Inorganic materials 0.000 claims abstract description 48
- 230000007704 transition Effects 0.000 claims abstract description 45
- 238000002485 combustion reaction Methods 0.000 claims abstract description 43
- 239000002737 fuel gas Substances 0.000 claims description 14
- 239000000567 combustion gas Substances 0.000 abstract description 5
- 230000003014 reinforcing effect Effects 0.000 abstract description 5
- 238000010276 construction Methods 0.000 abstract 1
- 230000002093 peripheral effect Effects 0.000 abstract 1
- 238000003466 welding Methods 0.000 description 9
- 238000010586 diagram Methods 0.000 description 8
- 230000000694 effects Effects 0.000 description 4
- 230000008646 thermal stress Effects 0.000 description 4
- 239000000446 fuel Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000000149 penetrating effect Effects 0.000 description 3
- 238000005336 cracking Methods 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000010790 dilution Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明はガスタービン用燃焼器構
造体に係わり、特に燃焼器ライナおよびトランジション
ピースを有するガスタービン用燃焼器構造体に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine combustor structure, and more particularly to a gas turbine combustor structure having a combustor liner and a transition piece.
【０００２】[0002]
【従来の技術】先ず、ガスタービンの燃焼器構造体にお
ける一般的な作動流体の流れについて説明する。圧縮機
より吐出された高圧空気は、燃焼器ライナとフロースリ
ーブ間の隙間に流れる。この空気の一部は燃焼器ライナ
頭部より燃料とともに燃焼器ライナ内に導かれ、また他
の一部は燃焼ガス希釈用および燃焼器ライナ本体のフイ
ルム冷却用として、燃焼器ライナのスロットより燃焼室
に入る。その後、燃焼ガスはトランジションピースを通
りタービンへ導かれ、燃焼ガスの熱エネルギが機械エネ
ルギとして有効な仕事に変換される。2. Description of the Related Art First, a general working fluid flow in a combustor structure of a gas turbine will be described. The high pressure air discharged from the compressor flows into the gap between the combustor liner and the flow sleeve. A part of this air is introduced into the combustor liner together with the fuel from the head of the combustor liner, and another part is burned from the slot of the combustor liner for dilution of the combustion gas and film cooling of the main body of the combustor liner. Enter the room. After that, the combustion gas is guided to the turbine through the transition piece, and the thermal energy of the combustion gas is converted into effective work as mechanical energy.
【０００３】そこで、従来の燃焼器構造体は燃焼器ライ
ナとトランジションピースの嵌合によって組立てられ一
体となっている。特に、燃焼器ライナのスプリングシー
ル部（ガス流れ出口部）は、トランジションピースと重
なり合っているため外表面からの冷却効果が小さく、か
つスプリングシール接合部は冷却空気が流れないため特
に高温になる。そのため燃焼器ライナのスプリングシー
ル部は、高温による材料の劣化が進行し、亀裂に対する
抵抗が著しく低下すると共に、燃焼ガス流の振動による
熱的応力ならびに機械的な燃焼振動が作用して亀裂発生
に至ることがある。Therefore, a conventional combustor structure is assembled and integrated by fitting a combustor liner and a transition piece. In particular, since the spring seal portion (gas flow outlet portion) of the combustor liner overlaps with the transition piece, the cooling effect from the outer surface is small, and the spring seal joint portion has a particularly high temperature because cooling air does not flow. Therefore, in the spring seal part of the combustor liner, deterioration of the material due to high temperature progresses, resistance to cracking is significantly reduced, and thermal stress due to vibration of the combustion gas flow and mechanical combustion vibration act to cause cracking. It may reach.
【０００４】[0004]
【発明が解決しようとする課題】従来の燃焼器構造体は
上記のような構造をしているため、熱的な応力および機
械的な燃焼振動の両方が加わり燃焼器ライナのガス流れ
出口部（スプリングシール部）に亀裂が発生することが
ある。そして、この亀裂発生の伝播により燃焼器ライナ
のスプリングシール部の役割が果たせなくなり、最後に
は燃焼器ライナ本体の破壊に繋がる恐れがある。Since the conventional combustor structure has the structure as described above, both the thermal stress and the mechanical combustion vibration are applied, and the gas flow outlet portion of the combustor liner ( Cracks may occur in the spring seal part). Then, due to the propagation of the crack generation, the role of the spring seal portion of the combustor liner cannot be fulfilled, and finally, the combustor liner main body may be broken.
【０００５】本発明は、上記事情に鑑みてなされたもの
で、その目的は、燃焼器ライナのスプリングシール部
（ガス流れ出口部）に発生し、伝播する亀裂を阻止する
ために燃焼器ライナのガス流れ出口部と重なり合う位置
で、燃焼器ライナ、トランジションピースまたはスプリ
ングシール部に冷却空気孔を有する燃焼器構造体を提供
することにある。The present invention has been made in view of the above circumstances, and an object thereof is to prevent cracks which are generated and propagate in a spring seal portion (gas flow outlet portion) of a combustor liner. It is an object of the present invention to provide a combustor structure having a cooling air hole in a combustor liner, a transition piece or a spring seal part at a position overlapping with a gas flow outlet part.
【０００６】[0006]
【課題を解決するための手段】上記目的を達成するため
に、本発明の請求項１は、燃焼器ライナとトランジショ
ンピースとをスプリングシール部を介して一体に構成さ
れたガスタービン用燃焼器構造体において、前記燃焼器
ライナの燃料ガス出口側近傍の前記トランジションピー
スに冷却空気孔を設け、スプリングシール部に発生する
亀裂を阻止するとともに、運転中に前記燃焼器ライナに
生じるガス火炎の燃焼温度によるメタル温度の上昇を抑
制するようにしたことを特徴とする。In order to achieve the above object, the first aspect of the present invention provides a combustor structure for a gas turbine in which a combustor liner and a transition piece are integrally formed via a spring seal portion. In the body, a cooling air hole is provided in the transition piece near the fuel gas outlet side of the combustor liner to prevent cracks occurring in the spring seal part, and the combustion temperature of the gas flame generated in the combustor liner during operation. It is characterized in that the increase in metal temperature due to is suppressed.
【０００７】本発明の請求項２は、燃焼器ライナとトラ
ンジションピースとをスプリングシール部を介して一体
に構成されたガスタービン用燃焼器構造体において、前
記燃焼器ライナの燃料ガス出口側近傍の当該燃焼器ライ
ナにメタル冷却板を設け、運転中に燃焼器ライナに生じ
るガス火炎の燃焼温度によるメタル温度の上昇を抑制す
るようにしたことを特徴とする。According to a second aspect of the present invention, in a combustor structure for a gas turbine in which a combustor liner and a transition piece are integrally formed via a spring seal portion, the combustor liner is provided near a fuel gas outlet side. The combustor liner is provided with a metal cooling plate to suppress an increase in metal temperature due to a combustion temperature of a gas flame generated in the combustor liner during operation.
【０００８】本発明の請求項３は、燃焼器ライナとトラ
ンジションピースとをスプリングシール部を介して一体
に構成されたガスタービン用燃焼器構造体において、前
記燃焼器ライナの燃料ガス出口側近傍の当該燃焼器ライ
ナに冷却空気溝を設け、運転中に燃焼器ライナに生じる
ガス火炎の燃焼温度によるメタル温度の上昇を抑制する
ようにしたことを特徴とする。According to a third aspect of the present invention, in a combustor structure for a gas turbine in which a combustor liner and a transition piece are integrally formed via a spring seal portion, the combustor liner is provided near a fuel gas outlet side. A cooling air groove is provided in the combustor liner to suppress an increase in metal temperature due to a combustion temperature of a gas flame generated in the combustor liner during operation.
【０００９】本発明の請求項４は、燃焼器ライナとトラ
ンジションピースとをスプリングシール部を介して一体
に構成されたガスタービン用燃焼器構造体において、前
記燃焼器ライナの燃料ガス出口側近傍の当該燃焼器ライ
ナにスロット式冷却空気孔を設け、運転中に燃焼器ライ
ナに生じるガス火炎の燃焼温度によるメタル温度の上昇
を抑制するようにしたことを特徴とする。According to a fourth aspect of the present invention, in a combustor structure for a gas turbine in which a combustor liner and a transition piece are integrally formed via a spring seal portion, the combustor liner is provided near a fuel gas outlet side. The combustor liner is provided with slot type cooling air holes to suppress an increase in metal temperature due to a combustion temperature of a gas flame generated in the combustor liner during operation.
【００１０】本発明の請求項５は、燃焼器ライナとトラ
ンジションピースとをスプリングシール部を介して一体
に構成されたガスタービン用燃焼器構造体において、前
記燃焼器ライナの燃料ガス出口側近傍の当該燃焼器ライ
ナに複数のスロット式冷却空気孔を設け、運転中に燃焼
器ライナに生じるガス火炎の燃焼温度によるメタル温度
の上昇を抑制するようにしたことを特徴とする。According to a fifth aspect of the present invention, in a combustor structure for a gas turbine in which a combustor liner and a transition piece are integrally formed via a spring seal portion, the combustor liner is provided near a fuel gas outlet side. The combustor liner is provided with a plurality of slot-type cooling air holes to suppress an increase in metal temperature due to a combustion temperature of a gas flame generated in the combustor liner during operation.
【００１１】本発明の請求項６は、燃焼器ライナとトラ
ンジションピースとをスプリングシール部を介して一体
に構成されたガスタービン用燃焼器構造体において、前
記燃焼器ライナの燃料ガス出口側近傍の前記トランジシ
ョンピースの円周方向に複数の冷却空気孔を設け、運転
中に燃焼器ライナに生じるガス火炎の燃焼温度によるメ
タル温度の上昇を抑制するようにしたことを特徴とす
る。According to a sixth aspect of the present invention, in a combustor structure for a gas turbine in which a combustor liner and a transition piece are integrally formed via a spring seal portion, the combustor liner is provided near a fuel gas outlet side. A plurality of cooling air holes are provided in the circumferential direction of the transition piece to suppress an increase in metal temperature due to the combustion temperature of the gas flame generated in the combustor liner during operation.
【００１２】本発明の請求項７は、燃焼器ライナとトラ
ンジションピースとをスプリングシール部を介して一体
に構成されたガスタービン用燃焼器構造体において、前
記燃焼器ライナの燃料ガス出口側近傍の前記トランジシ
ョンピースの軸方向に複数の冷却空気孔を設け、運転中
に燃焼器ライナに生じるガス火炎の燃焼温度によるメタ
ル温度の上昇を抑制するようにしたことを特徴とする。According to a seventh aspect of the present invention, in a combustor structure for a gas turbine in which a combustor liner and a transition piece are integrally formed via a spring seal portion, the combustor liner is provided near a fuel gas outlet side. A plurality of cooling air holes are provided in the axial direction of the transition piece to suppress an increase in metal temperature due to the combustion temperature of the gas flame generated in the combustor liner during operation.
【００１３】本発明の請求項８は、燃焼器ライナとトラ
ンジションピースとをスプリングシール部を介して一体
に構成されたガスタービン用燃焼器構造体において、前
記スプリングシールのスリットに沿ってガス流れ出口端
部に至る冷却空気溝を設け、運転中に燃焼器ライナに生
じるガス火炎の燃焼温度によるメタル温度の上昇を抑制
するようにしたことを特徴とする。According to an eighth aspect of the present invention, in a combustor structure for a gas turbine in which a combustor liner and a transition piece are integrally formed via a spring seal portion, a gas flow outlet is provided along a slit of the spring seal. A cooling air groove reaching the end is provided to suppress an increase in metal temperature due to the combustion temperature of the gas flame generated in the combustor liner during operation.
【００１４】[0014]
【作用】上述したように、燃焼器構造体の燃焼器ライナ
に起こる熱応力や燃焼振動によって、燃焼器ライナのガ
ス流れ出口部に亀裂が発生し、その亀裂が燃焼器ライナ
の本体に伝播し、燃焼器ライナ本体へと伝播する。As described above, due to thermal stress and combustion vibration occurring in the combustor liner of the combustor structure, a crack is generated at the gas flow outlet of the combustor liner, and the crack propagates to the main body of the combustor liner. , Propagate to the combustor liner body.
【００１５】そこで、本発明では、燃焼器ライナのガス
流れ出口部の亀裂の発生および伝播を阻止し、燃焼器ラ
イナ本体の飛散を未然に防止するとともに、燃焼器ライ
ナ本体の運転中に生じるガス火炎の燃焼温度を抑制する
ために、燃焼器ライナのガス流れ出口部と重なり合う位
置で、燃焼器ライナ、トランジションピースまたはスプ
リングシール部に冷却空気孔を設けているので、この冷
却空気孔によって燃焼器ライナのガス流れ出口部のメタ
ルを直接空気冷却し、メタル温度を降下させることによ
り材料強度を増し、損傷を防止できる。従って、燃焼器
ライナ本体の使用寿命を長くするとともに、燃焼器構造
体の信頼性を高めることができる。Therefore, in the present invention, the generation and propagation of cracks at the gas flow outlet of the combustor liner is prevented, scattering of the combustor liner body is prevented, and gas generated during operation of the combustor liner body is prevented. In order to suppress the combustion temperature of the flame, cooling air holes are provided in the combustor liner, transition piece or spring seal at the position where they overlap the gas flow outlet of the combustor liner. By directly air-cooling the metal at the gas flow outlet of the liner and lowering the metal temperature, the material strength can be increased and damage can be prevented. Therefore, it is possible to extend the service life of the main body of the combustor and increase the reliability of the combustor structure.
【００１６】[0016]
【実施例】以下、本発明の実施例を図を参照して説明す
る。図１は本発明の第１実施例（請求項１対応）の構成
図である。同図に示すように、燃焼器ライナ１およびト
ランジションピース２は、空気圧縮機吐出ケーシング３
の円周の回りに配列された燃焼器ケーシング４および燃
焼器ラッパ５で覆われている。Embodiments of the present invention will now be described with reference to the drawings. FIG. 1 is a configuration diagram of a first embodiment (corresponding to claim 1) of the present invention. As shown in the figure, the combustor liner 1 and the transition piece 2 include an air compressor discharge casing 3
It is covered with a combustor casing 4 and a combustor wrapper 5 arranged around the circumference of.
【００１７】燃焼器ライナ１は、燃焼噴射ノズル６や図
示しない点火器及び火炎検出機並びに火炎伝播管７を有
している。高温ガスは燃焼器ライナ１内で燃料が燃焼す
ることにより発生し、ガスタービンを作動するのに使用
される。The combustor liner 1 has a combustion injection nozzle 6, an igniter and a flame detector (not shown), and a flame propagation tube 7. Hot gas is generated by the combustion of fuel in the combustor liner 1 and is used to operate the gas turbine.
【００１８】空気圧縮機吐出ケーシング３からの高圧空
気は、トランジションピース２の回りに導かれ、燃焼器
ライナ１の各々の回りの環状の空間へ入る。この空気は
燃焼用空気口（混合空気口）８および燃焼器ライナ１を
冷却するスロット９を通り燃焼域に入る。トランジショ
ンピース２は燃焼器ライナ１からの高温ガスをガスター
ビン第１段ノズルに直接導くものである。High pressure air from the air compressor discharge casing 3 is directed around the transition pieces 2 and enters an annular space around each of the combustor liners 1. This air enters the combustion zone through the combustion air port (mixed air port) 8 and the slot 9 for cooling the combustor liner 1. The transition piece 2 directly guides the hot gas from the combustor liner 1 to the gas turbine first stage nozzle.
【００１９】燃焼構造体の燃焼器ライナ１とトランジシ
ョンピース２の嵌合状態を図２に示し、図３は図２のＡ
−Ａ方向からみた断面図である。同図に示すように、燃
焼器ライナ１のスプリングシール部１０と重なり合うト
ランジションピース２の補強リブ１１から本体を貫通さ
せた冷却空気孔１２ａ，１２ｂを円周方向に複数個設け
る。これによって補強リブ１１より流入した冷却空気
は、燃焼器ライナ１のスプリングシール部１０に当たり
メタルを円周状に均等に冷却する。なお補強リブ１１は
溶接金属１３ａ，１３ｂで固定されている。The fitting state of the combustor liner 1 and the transition piece 2 of the combustion structure is shown in FIG. 2, and FIG. 3 is A in FIG.
It is sectional drawing seen from the -A direction. As shown in the figure, a plurality of cooling air holes 12a, 12b are provided in the circumferential direction through the main body from the reinforcing ribs 11 of the transition piece 2 overlapping the spring seal portion 10 of the combustor liner 1. As a result, the cooling air flowing in from the reinforcing ribs 11 hits the spring seal portion 10 of the combustor liner 1 to cool the metal evenly in the circumferential direction. The reinforcing rib 11 is fixed with weld metals 13a and 13b.
【００２０】図４は本発明による燃焼構造体のメタル温
度分布を示す。特に、燃焼器ライナ１のスプリングシー
ル部１０のメタル温度１４は、約５００℃と従来のメタ
ル温度（約６５０℃）より１５０℃程度降下させること
ができる。したがって、本発明によると、燃焼器ライナ
１のスプリングシール部１０は材料強度が維持され、亀
裂発生抵抗が増大している。FIG. 4 shows the metal temperature distribution of the combustion structure according to the present invention. In particular, the metal temperature 14 of the spring seal portion 10 of the combustor liner 1 can be lowered to about 500 ° C, which is about 150 ° C lower than the conventional metal temperature (about 650 ° C). Therefore, according to the present invention, the material strength of the spring seal portion 10 of the combustor liner 1 is maintained and the crack initiation resistance is increased.
【００２１】図５は本発明の第２の実施例（請求項２対
応）に係る燃焼構造体の燃焼器ライナの断面図、図６は
図５のＢ−Ｂ断面図である。同図に示すように、燃焼器
ライナ１にはメタルを冷却するスロット９が全周に穿設
してあり、このスロット９の内側にメタル冷却板１５を
設け、スロット９より入る冷却空気をメタル冷却板１５
を介してスプリングシール部（ガス流れ出口部）１０ま
で導き、燃焼器ライナ１のメタルを冷却する構造とす
る。メタル冷却板１５はガス流れ上流側を全周溶接１６
ａ、中央部を部分溶接１６ｂ、下流側を部分溶接１６ｃ
で固定している。FIG. 5 is a sectional view of a combustor liner of a combustion structure according to a second embodiment (corresponding to claim 2) of the present invention, and FIG. 6 is a sectional view taken along line BB of FIG. As shown in the figure, the combustor liner 1 is provided with a slot 9 for cooling the metal all around, and a metal cooling plate 15 is provided inside the slot 9 to cool the cooling air entering from the slot 9 to the metal. Cooling plate 15
The metal of the combustor liner 1 is cooled by introducing it to the spring seal portion (gas flow outlet portion) 10 via the. The metal cooling plate 15 is welded all around the upstream side of the gas flow 16
a, partial welding 16b at the center, partial welding 16c at the downstream side
It is fixed with.
【００２２】メタル冷却板１５は強度及び冷却効果の増
加が得られる構造が好ましく、このため液状模様および
ジグザク模様も適用できる。これによって燃焼器ライナ
１のメタルを効果的に冷却することができる。The metal cooling plate 15 preferably has a structure capable of increasing the strength and the cooling effect, and therefore, a liquid pattern and a zigzag pattern can also be applied. This allows the metal of the combustor liner 1 to be effectively cooled.
【００２３】図７は本発明の第３の実施例（請求項３対
応）に係る燃焼構造体の燃焼器ライナの構成図、図８は
図７のＣ−Ｃ断面図である。同図に示すように、燃焼器
ライナ１のガス流れ出口部付近にはトランジションピー
ス２との嵌合いをシールするためのスプリングシール１
０が、スポット溶接１７により固定されている。このス
プリングシール１０にはスリット１０ａがあり、このス
リット１０ａより冷却空気が入る。この冷却空気を利用
して燃焼器ライナ１のガス流れ出口端部のメタルを冷却
するために、ガス流れ方向に沿って冷却空気溝１８を設
ける。この冷却空気溝１８は燃焼器ライナ１の円周方向
に複数箇所配置される。FIG. 7 is a configuration diagram of a combustor liner of a combustion structure according to a third embodiment (corresponding to claim 3) of the present invention, and FIG. 8 is a sectional view taken along line CC of FIG. As shown in the figure, a spring seal 1 for sealing the fitting with the transition piece 2 is provided near the gas flow outlet of the combustor liner 1.
0 is fixed by spot welding 17. The spring seal 10 has a slit 10a, and cooling air enters through the slit 10a. In order to cool the metal at the gas flow outlet end of the combustor liner 1 using this cooling air, cooling air grooves 18 are provided along the gas flow direction. The cooling air grooves 18 are arranged at a plurality of positions in the circumferential direction of the combustor liner 1.
【００２４】またスプリングシール１０のスリット１０
ａを通って入ってくる冷却空気を燃焼器ライナ１に設け
た冷却空気溝１８を通過させ燃焼器ライナ１のメタルを
冷却することができる。The slit 10 of the spring seal 10
It is possible to cool the metal of the combustor liner 1 by passing the cooling air coming in through a through the cooling air groove 18 provided in the combustor liner 1.
【００２５】図９は本発明の第４実施例（請求項４対
応）に係る燃焼構造体の燃焼器ライナの断面図、図１０
は図９のＤ−Ｄ断面図である。同図に示すように、燃焼
器ライナ１にはスロット式による冷却空気孔１９を円周
方向に複数穿設してあり、この冷却空気孔１９より入っ
てくる空気により燃焼器ライナ１のガス流れ出口端部を
直接冷却する構造とする。スロット式による冷却空気孔
１９を有するプレート２０は、一端を燃焼器ライナ１に
スポット溶接２１ａで固定し、他端をスプリングシール
１０に円周方向にスポット溶接２１ｂで固定する。この
ように燃焼器ラテナ１のスロット式による冷却空気孔１
９を通って入ってくる空気によってガス流れ出口端部の
メタルを直接冷却することができる。FIG. 9 is a sectional view of a combustor liner of a combustion structure according to a fourth embodiment (corresponding to claim 4) of the present invention, and FIG.
FIG. 10 is a sectional view taken along the line D-D in FIG. 9. As shown in the figure, the combustor liner 1 is provided with a plurality of slot-type cooling air holes 19 in the circumferential direction. The air flowing through the cooling air holes 19 causes the gas flow of the combustor liner 1 to flow. The structure is such that the outlet end is directly cooled. A plate 20 having slotted cooling air holes 19 has one end fixed to the combustor liner 1 by spot welding 21a and the other end fixed to the spring seal 10 in the circumferential direction by spot welding 21b. In this way, the slotted cooling air holes 1 of the combustor lathe 1
The air entering through 9 allows the metal at the gas flow outlet end to be cooled directly.
【００２６】図１１は本発明の第５実施例（請求項５対
応）に係る燃焼構造体の燃焼器ライナの断面図、図１２
は図１１のＥ−Ｅ断面図である。同図に示すように、燃
焼器ライナ１にはスロット式による冷却空気孔２２ａ，
２２ｂを軸方向に複数穿設し、この冷却空気孔２２ａ，
２２ｂより入ってくる空気をインピンジ板２３ａ，２３
ｂに当てガス流れ方向に導き、燃焼器ライナ１のガス流
れ出口部を直接冷却する。スロット式による冷却空気孔
２２ａ，２２ｂを有するプレート２４はスプリングシー
ル１０と円周方向に複数のスポット溶接２５で固定し、
インピンジ板２３ａ，２３ｂは燃焼器ライナ１に溶接２
６ａ，２６ｂで固定する。このように燃焼器ライナ１の
スロット式による冷却空気孔２２ａ，２２ｂより流入す
る空気によって、ガス流れ出口部のメタルを直接冷却す
ることができる。FIG. 11 is a sectional view of a combustor liner of a combustion structure according to a fifth embodiment (corresponding to claim 5) of the present invention, and FIG.
FIG. 12 is a sectional view taken along line EE of FIG. 11. As shown in the figure, the combustor liner 1 has a slot-type cooling air hole 22a,
22b are provided in the axial direction, and the cooling air holes 22a,
The air coming in from 22b is fed to the impingement plates 23a, 23
It is applied to b and guided in the gas flow direction to directly cool the gas flow outlet of the combustor liner 1. The plate 24 having the slot-type cooling air holes 22a and 22b is fixed to the spring seal 10 by a plurality of spot welds 25 in the circumferential direction,
The impingement plates 23a, 23b are welded to the combustor liner 1 2
Fix with 6a, 26b. As described above, the air flowing in from the slot-type cooling air holes 22a and 22b of the combustor liner 1 can directly cool the metal at the gas flow outlet.
【００２７】図１３は本発明の第６実施例（請求項６対
応）に係る燃焼構造体の燃焼器ライナの断面図、図１４
は図１３のＦ−Ｆ断面図である。同図は、燃焼器ライナ
１とトランジションピース２の嵌合状態を示す図であ
り、燃焼器ライナ１のガス流れ出口部（スプリングシー
ル部）１０と重なり合うトランジションピース２に貫通
した冷却空気孔２７を円周方向に複数箇所設ける。トラ
ンジションピース２より流入した冷却空気は燃焼器ライ
ナ１のガス流れ出口部（スプリングシール部）１０に当
たりメタルを冷却する。これによって、燃焼器ライナ１
のガス流れ出口部（スプリングシール部）１０のメタル
が円周状に均等に冷却される。FIG. 13 is a sectional view of a combustor liner of a combustion structure according to a sixth embodiment of the present invention (corresponding to claim 6), and FIG.
FIG. 14 is a sectional view taken along line F-F in FIG. 13. This figure is a view showing a fitted state of the combustor liner 1 and the transition piece 2, and shows cooling air holes 27 penetrating the transition piece 2 overlapping the gas flow outlet portion (spring seal portion) 10 of the combustor liner 1. Provide at multiple locations in the circumferential direction. The cooling air flowing in from the transition piece 2 hits the gas flow outlet portion (spring seal portion) 10 of the combustor liner 1 to cool the metal. This allows the combustor liner 1
The metal of the gas flow outlet portion (spring seal portion) 10 is uniformly cooled circumferentially.
【００２８】図１５は本発明の第７実施例（請求項７対
応）に係る燃焼構造体の燃焼器ライナの断面図、図１６
は図１５のＧ−Ｇ断面図である。同図は、燃焼器ライナ
１とトランジションピース２の嵌合状態を示す図であ
り、燃焼器ライナ１のガス流れ出口部（スプリングシー
ル部）１０と重なり合うトランジションピース２の軸方
向に貫通した冷却空気孔２８ａ，２８ｂを複数箇所設け
る。トランジションピース２の軸方向に貫通した冷却空
気孔２８ａ，２８ｂより流入した冷却空気は、燃焼器ラ
イナ１のスプリングシール部１０に当たりメタルを冷却
する。これによって、燃焼器ライナ１のスプリングシー
ル部１０のメタルが円周状に均等に冷却される。FIG. 15 is a sectional view of a combustor liner of a combustion structure according to a seventh embodiment (corresponding to claim 7) of the present invention, and FIG.
FIG. 16 is a sectional view taken along line GG of FIG. 15. This figure is a view showing a fitted state of the combustor liner 1 and the transition piece 2, and cooling air penetrating in the axial direction of the transition piece 2 overlapping the gas flow outlet (spring seal part) 10 of the combustor liner 1. A plurality of holes 28a and 28b are provided. The cooling air flowing in from the cooling air holes 28a and 28b penetrating the transition piece 2 in the axial direction hits the spring seal portion 10 of the combustor liner 1 to cool the metal. As a result, the metal of the spring seal portion 10 of the combustor liner 1 is evenly circumferentially cooled.
【００２９】図１７は本発明の第８実施例（請求項８対
応）に係る燃焼構造体の燃焼器ライナの構成図、図１８
は図１７のＨ−Ｈ断面図である。同図に示すように、燃
焼器ライナ１のガス流れ出口部付近にはトランジション
ピース２との嵌合をシールするためのスプリングシール
１０がスポット溶接１７により固定されている。このス
プリングシール１０にはスリット１０ａがあり、このス
リット１０ａより冷却空気が入る。この冷却空気を利用
して燃焼器ライナ１のガス流れ出口端部のメタルを冷却
するために、燃焼器ライナ１の円周方向にスリット１０
ａに沿って冷却空気溝２９を設ける。これによって冷却
空気溝２９を通過した冷却空気は燃焼器ライナ１のメタ
ルを直接冷却することができる。FIG. 17 is a structural diagram of a combustor liner of a combustion structure according to an eighth embodiment (corresponding to claim 8) of the present invention, and FIG.
FIG. 18 is a sectional view taken along line HH of FIG. 17. As shown in the figure, a spring seal 10 for sealing the fitting with the transition piece 2 is fixed by spot welding 17 near the gas flow outlet of the combustor liner 1. The spring seal 10 has a slit 10a, and cooling air enters through the slit 10a. In order to cool the metal at the end of the gas flow outlet of the combustor liner 1 using this cooling air, the slit 10 is formed in the circumferential direction of the combustor liner 1.
A cooling air groove 29 is provided along a. As a result, the cooling air that has passed through the cooling air groove 29 can directly cool the metal of the combustor liner 1.
【００３０】[0030]
【発明の効果】以上説明したように、本発明によれば、
燃焼器構造体で起こる熱応力や燃焼振動及び燃焼温度の
影響により、燃焼器ライナのガス流れ出口部に発生する
亀裂を阻止し、これにより燃焼器ライナ本体の飛散を未
然に防止し、燃焼器構造体の使用寿命を長くするととも
に燃焼器構造体の信頼性を高めることができる、という
すぐれた効果を奏する。As described above, according to the present invention,
Cracks that occur at the gas flow outlet of the combustor liner due to the effects of thermal stress, combustion vibration, and combustion temperature that occur in the combustor structure are prevented, which prevents scattering of the combustor liner body. This has the excellent effect that the service life of the structure can be extended and the reliability of the combustor structure can be improved.
【図１】本発明の第１実施例の構成図。FIG. 1 is a configuration diagram of a first embodiment of the present invention.
【図２】図１の燃焼器構造体の燃焼器ライナとトランジ
ションピースの嵌合状態図。FIG. 2 is a fitting state diagram of a combustor liner and a transition piece of the combustor structure shown in FIG.
【図３】図２のＡ−Ａ断面図。FIG. 3 is a sectional view taken along line AA of FIG. 2;
【図４】本発明による燃焼器構造体のメタル温度分布
図。FIG. 4 is a metal temperature distribution diagram of a combustor structure according to the present invention.
【図５】本発明の第２実施例の断面図。FIG. 5 is a sectional view of a second embodiment of the present invention.
【図６】図５のＢ−Ｂ断面図。6 is a sectional view taken along line BB of FIG.
【図７】本発明の第３実施例の構成図。FIG. 7 is a configuration diagram of a third embodiment of the present invention.
【図８】図７のＣ−Ｃ断面図。8 is a cross-sectional view taken along line CC of FIG.
【図９】本発明の第４実施例の断面図。FIG. 9 is a sectional view of a fourth embodiment of the present invention.
【図１０】図９のＤ−Ｄ断面図。FIG. 10 is a sectional view taken along line DD of FIG. 9;
【図１１】本発明の第５実施例の断面図。FIG. 11 is a sectional view of a fifth embodiment of the present invention.
【図１２】図１１のＥ−Ｅ断面図。12 is a sectional view taken along line EE of FIG.
【図１３】本発明の第６実施例の断面図。FIG. 13 is a sectional view of a sixth embodiment of the present invention.
【図１４】図１３のＦ−Ｆ断面図。14 is a sectional view taken along line FF of FIG.
【図１５】本発明の第７実施例の断面図。FIG. 15 is a sectional view of a seventh embodiment of the present invention.
【図１６】図１５のＧ−Ｇ断面図。16 is a sectional view taken along line GG of FIG.
【図１７】本発明の第８実施例の構成図。FIG. 17 is a configuration diagram of an eighth embodiment of the present invention.
【図１８】図１７のＨ−Ｈ断面図。18 is a cross-sectional view taken along line HH of FIG.
１…燃焼ライナ、２…トランジションピース、３…空気
圧縮吐出ケーシング、４…燃焼器ケーシング、５…燃焼
器ラッパ、６…燃料噴射ノズル、７…火炎伝播管、８…
燃焼用空気口（混合空気口）、９…プレート、１０…ス
プリングシール部、１０ａ…スリット、１１…補強リ
ブ、１２ａ，１２ｂ…冷却空気孔、１３ａ，１３ｂ…溶
接金属、１４…メタル温度及び測定点、１５…メタル冷
却板、１６ａ，１６ｂ，１６ｃ…溶接部、１７…スポッ
ト溶接、１８…冷却空気溝、１９…冷却空気孔、２０…
プレート、２１ａ，２１ｂ…スポット溶接、２２ａ，２
２ｂ…冷却空気孔、２３ａ，２３ｂ…インピンジ板、２
４…プレート、２５…スポット溶接、２６ａ，２６ｂ…
溶接部、２７…冷却空気孔、２８ａ，２８ｂ…冷却空気
孔、２９…冷却空気溝。DESCRIPTION OF SYMBOLS 1 ... Combustion liner, 2 ... Transition piece, 3 ... Air compression discharge casing, 4 ... Combustor casing, 5 ... Combustor wrapper, 6 ... Fuel injection nozzle, 7 ... Flame propagation tube, 8 ...
Combustion air port (mixed air port), 9 ... Plate, 10 ... Spring seal part, 10a ... Slit, 11 ... Reinforcing rib, 12a, 12b ... Cooling air hole, 13a, 13b ... Weld metal, 14 ... Metal temperature and measurement Points, 15 ... Metal cooling plate, 16a, 16b, 16c ... Welded portion, 17 ... Spot welding, 18 ... Cooling air groove, 19 ... Cooling air hole, 20 ...
Plates, 21a, 21b ... Spot welding, 22a, 2
2b ... Cooling air holes, 23a, 23b ... Impingement plate, 2
4 ... Plate, 25 ... Spot welding, 26a, 26b ...
Welded portion, 27 ... Cooling air hole, 28a, 28b ... Cooling air hole, 29 ... Cooling air groove.
───────────────────────────────────────────────────── フロントページの続き (72)発明者 吉岡 洋明 神奈川県横浜市鶴見区末広町２丁目４番地 株式会社東芝京浜事業所内 (72)発明者 石井 潤治 神奈川県横浜市鶴見区末広町２丁目４番地 株式会社東芝京浜事業所内 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Hiroaki Yoshioka 2-4 Suehiro-cho, Tsurumi-ku, Yokohama-shi, Kanagawa Toshiba Keihin Plant (72) Inventor Junji Ishii 2-cue, Suehiro-cho, Tsurumi-ku, Yokohama-shi, Kanagawa Address inside Toshiba Keihin office
Claims (8)
をスプリングシール部を介して一体に構成されたガスタ
ービン用燃焼器構造体において、前記燃焼器ライナの燃
料ガス出口側近傍の前記トランジションピースに冷却空
気孔を設け、スプリングシール部に発生する亀裂を阻止
するとともに、運転中に前記燃焼器ライナに生じるガス
火炎の燃焼温度によるメタル温度の上昇を抑制するよう
にしたことを特徴とするガスタービン用燃焼器構造体。1. A combustor structure for a gas turbine in which a combustor liner and a transition piece are integrally formed via a spring seal portion, wherein cooling air is provided to the transition piece near the fuel gas outlet side of the combustor liner. Combustion for gas turbines, characterized in that holes are provided to prevent cracks occurring in the spring seal portion and to suppress an increase in metal temperature due to the combustion temperature of the gas flame generated in the combustor liner during operation. Vessel structure.
をスプリングシール部を介して一体に構成されたガスタ
ービン用燃焼器構造体において、前記燃焼器ライナの燃
料ガス出口側近傍の当該燃焼器ライナにメタル冷却板を
設け、運転中に燃焼器ライナに生じるガス火炎の燃焼温
度によるメタル温度の上昇を抑制するようにしたことを
特徴とするガスタービン用燃焼器構造体。2. A gas turbine combustor structure in which a combustor liner and a transition piece are integrally formed via a spring seal portion, wherein a metal is provided on the combustor liner near the fuel gas outlet side of the combustor liner. A combustor structure for a gas turbine, wherein a cooling plate is provided to suppress an increase in metal temperature due to a combustion temperature of a gas flame generated in a combustor liner during operation.
をスプリングシール部を介して一体に構成されたガスタ
ービン用燃焼器構造体において、前記燃焼器ライナの燃
料ガス出口側近傍の当該燃焼器ライナに冷却空気溝を設
け、運転中に燃焼器ライナに生じるガス火炎の燃焼温度
によるメタル温度の上昇を抑制するようにしたことを特
徴とするガスタービン用燃焼器構造体。3. In a combustor structure for a gas turbine, wherein a combustor liner and a transition piece are integrally formed via a spring seal portion, the combustor liner is cooled near the fuel gas outlet side of the combustor liner. A combustor structure for a gas turbine, wherein an air groove is provided to suppress an increase in metal temperature due to a combustion temperature of a gas flame generated in a combustor liner during operation.
をスプリングシール部を介して一体に構成されたガスタ
ービン用燃焼器構造体において、前記燃焼器ライナの燃
料ガス出口側近傍の当該燃焼器ライナにスロット式冷却
空気孔を設け、運転中に燃焼器ライナに生じるガス火炎
の燃焼温度によるメタル温度の上昇を抑制するようにし
たことを特徴とするガスタービン用燃焼器構造体。4. A gas turbine combustor structure in which a combustor liner and a transition piece are integrally formed via a spring seal portion, wherein a slot is formed in the combustor liner near the fuel gas outlet side of the combustor liner. A combustor structure for a gas turbine, wherein a cooling air hole is provided to suppress an increase in metal temperature due to a combustion temperature of a gas flame generated in a combustor liner during operation.
をスプリングシール部を介して一体に構成されたガスタ
ービン用燃焼器構造体において、前記燃焼器ライナの燃
料ガス出口側近傍の当該燃焼器ライナに複数のスロット
式冷却空気孔を設け、運転中に燃焼器ライナに生じるガ
ス火炎の燃焼温度によるメタル温度の上昇を抑制するよ
うにしたことを特徴とするガスタービン用燃焼器構造
体。5. A gas turbine combustor structure in which a combustor liner and a transition piece are integrally formed via a spring seal portion, and a plurality of combustor liners are provided near the fuel gas outlet side of the combustor liner. A slot-type cooling air hole is provided to suppress an increase in metal temperature due to a combustion temperature of a gas flame generated in a combustor liner during operation, and a combustor structure for a gas turbine.
をスプリングシール部を介して一体に構成されたガスタ
ービン用燃焼器構造体において、前記燃焼器ライナの燃
料ガス出口側近傍の前記トランジションピースの円周方
向に複数の冷却空気孔を設け、運転中に燃焼器ライナに
生じるガス火炎の燃焼温度によるメタル温度の上昇を抑
制するようにしたことを特徴とするガスタービン用燃焼
器構造体。6. A combustor liner and a transition piece are integrally formed via a spring seal portion in a combustor structure for a gas turbine, wherein the circumference of the transition piece is near the fuel gas outlet side of the combustor liner. A combustor structure for a gas turbine, wherein a plurality of cooling air holes are provided in a direction to suppress an increase in metal temperature due to a combustion temperature of a gas flame generated in a combustor liner during operation.
をスプリングシール部を介して一体に構成されたガスタ
ービン用燃焼器構造体において、前記燃焼器ライナの燃
料ガス出口側近傍の前記トランジションピースの軸方向
に複数の冷却空気孔を設け、運転中に燃焼器ライナに生
じるガス火炎の燃焼温度によるメタル温度の上昇を抑制
するようにしたことを特徴とするガスタービン用燃焼器
構造体。7. A combustor structure for a gas turbine in which a combustor liner and a transition piece are integrally formed via a spring seal portion, wherein in the axial direction of the transition piece near the fuel gas outlet side of the combustor liner. A combustor structure for a gas turbine, characterized in that a plurality of cooling air holes are provided in said structure to suppress an increase in metal temperature due to a combustion temperature of a gas flame generated in a combustor liner during operation.
をスプリングシール部を介して一体に構成されたガスタ
ービン用燃焼器構造体において、前記スプリングシール
のスリットに沿ってガス流れ出口端部に至る冷却空気溝
を設け、運転中に燃焼器ライナに生じるガス火炎の燃焼
温度によるメタル温度の上昇を抑制するようにしたこと
を特徴とするガスタービン用燃焼器構造体。8. A combustor structure for a gas turbine in which a combustor liner and a transition piece are integrally formed via a spring seal portion, wherein cooling air reaching a gas flow outlet end portion along a slit of the spring seal. A combustor structure for a gas turbine, wherein a groove is provided to suppress an increase in metal temperature due to a combustion temperature of a gas flame generated in a combustor liner during operation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8380695A JPH08285284A (en) | 1995-04-10 | 1995-04-10 | Combustor structure for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8380695A JPH08285284A (en) | 1995-04-10 | 1995-04-10 | Combustor structure for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH08285284A true JPH08285284A (en) | 1996-11-01 |
Family
ID=13812917
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP8380695A Pending JPH08285284A (en) | 1995-04-10 | 1995-04-10 | Combustor structure for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH08285284A (en) |
Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09196378A (en) * | 1996-01-12 | 1997-07-29 | Mitsubishi Heavy Ind Ltd | Tail pipe of gas turbine combustor |
| JPH10238777A (en) * | 1997-02-28 | 1998-09-08 | Hitachi Ltd | Gas turbine combustor |
| US5983641A (en) * | 1997-04-30 | 1999-11-16 | Mitsubishi Heavy Industries, Ltd. | Tail pipe of gas turbine combustor and gas turbine combustor having the same tail pipe |
| JP2002071136A (en) * | 2000-08-28 | 2002-03-08 | Hitachi Ltd | Combustor liner |
| WO2003002913A1 (en) * | 2001-06-27 | 2003-01-09 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
| JP2003013747A (en) * | 2001-06-29 | 2003-01-15 | Mitsubishi Heavy Ind Ltd | Gas turbine combustor |
| US6658853B2 (en) | 2001-09-12 | 2003-12-09 | Kawasaki Jukogyo Kabushiki Kaisha | Seal structure for combustor liner |
| EP1391582A2 (en) | 2002-08-22 | 2004-02-25 | Kawasaki Jukogyo Kabushiki Kaisha | Sealing structure for combustor liner |
| JP2005345093A (en) * | 2004-06-01 | 2005-12-15 | General Electric Co <Ge> | Method and apparatus for cooling a combustor liner and transition component of a gas turbine |
| US7096668B2 (en) * | 2003-12-22 | 2006-08-29 | Martling Vincent C | Cooling and sealing design for a gas turbine combustion system |
| US7246995B2 (en) | 2004-12-10 | 2007-07-24 | Siemens Power Generation, Inc. | Seal usable between a transition and a turbine vane assembly in a turbine engine |
| US7269957B2 (en) * | 2004-05-28 | 2007-09-18 | Martling Vincent C | Combustion liner having improved cooling and sealing |
| JP2009250242A (en) * | 2008-04-10 | 2009-10-29 | General Electric Co <Ge> | Combustor seal having multiple cooling fluid pathways |
| JP2009275701A (en) * | 2008-05-13 | 2009-11-26 | General Electric Co <Ge> | Method and device for cooling and dilution-adjusting gas turbine combustor liner and transition piece joint part |
| JP2010196702A (en) * | 2009-02-26 | 2010-09-09 | General Electric Co <Ge> | Gas turbine combustion system cooling arrangement |
| JP2010281568A (en) * | 2004-06-04 | 2010-12-16 | General Electric Co <Ge> | Method and apparatus for low emission gas turbine power generation |
| FR2959795A1 (en) * | 2010-05-05 | 2011-11-11 | Snecma | Combustion chamber for turbomachine, has case flanges that are cooperated with terminal flanges to ensure maintenance of chamber in position, where one terminal flange is arranged to cooperate with one case flange through sliding contact |
| EP2058475A3 (en) * | 2007-11-09 | 2012-04-04 | United Technologies Corporation | Cooled transition piece of a gas turbine engine and corresponding gas turbine engine |
| WO2012132898A1 (en) * | 2011-03-30 | 2012-10-04 | 三菱重工業株式会社 | Combustor and gas turbine provided with same |
| US8713945B2 (en) | 2010-06-29 | 2014-05-06 | Nuovo Pignone S.P.A. | Liner aft end support mechanisms and spring loaded liner stop mechanisms |
| JP2014178076A (en) * | 2013-03-15 | 2014-09-25 | Mitsubishi Heavy Ind Ltd | Elastic ring, and combustor and gas turbine with the same |
| KR101662121B1 (en) * | 2015-07-06 | 2016-10-04 | 두산중공업 주식회사 | The invention of liner and transition piece connection |
| JP2018071801A (en) * | 2016-10-24 | 2018-05-10 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
-
1995
- 1995-04-10 JP JP8380695A patent/JPH08285284A/en active Pending
Cited By (30)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09196378A (en) * | 1996-01-12 | 1997-07-29 | Mitsubishi Heavy Ind Ltd | Tail pipe of gas turbine combustor |
| JPH10238777A (en) * | 1997-02-28 | 1998-09-08 | Hitachi Ltd | Gas turbine combustor |
| US5983641A (en) * | 1997-04-30 | 1999-11-16 | Mitsubishi Heavy Industries, Ltd. | Tail pipe of gas turbine combustor and gas turbine combustor having the same tail pipe |
| JP2002071136A (en) * | 2000-08-28 | 2002-03-08 | Hitachi Ltd | Combustor liner |
| US7032386B2 (en) | 2001-06-27 | 2006-04-25 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
| WO2003002913A1 (en) * | 2001-06-27 | 2003-01-09 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
| JP2003013747A (en) * | 2001-06-29 | 2003-01-15 | Mitsubishi Heavy Ind Ltd | Gas turbine combustor |
| US6658853B2 (en) | 2001-09-12 | 2003-12-09 | Kawasaki Jukogyo Kabushiki Kaisha | Seal structure for combustor liner |
| US6854738B2 (en) | 2002-08-22 | 2005-02-15 | Kawasaki Jukogyo Kabushiki Kaisha | Sealing structure for combustor liner |
| EP1391582A2 (en) | 2002-08-22 | 2004-02-25 | Kawasaki Jukogyo Kabushiki Kaisha | Sealing structure for combustor liner |
| US7096668B2 (en) * | 2003-12-22 | 2006-08-29 | Martling Vincent C | Cooling and sealing design for a gas turbine combustion system |
| US7269957B2 (en) * | 2004-05-28 | 2007-09-18 | Martling Vincent C | Combustion liner having improved cooling and sealing |
| JP2005345093A (en) * | 2004-06-01 | 2005-12-15 | General Electric Co <Ge> | Method and apparatus for cooling a combustor liner and transition component of a gas turbine |
| JP2010281568A (en) * | 2004-06-04 | 2010-12-16 | General Electric Co <Ge> | Method and apparatus for low emission gas turbine power generation |
| US7246995B2 (en) | 2004-12-10 | 2007-07-24 | Siemens Power Generation, Inc. | Seal usable between a transition and a turbine vane assembly in a turbine engine |
| US8307656B2 (en) | 2007-11-09 | 2012-11-13 | United Technologies Corp. | Gas turbine engine systems involving cooling of combustion section liners |
| EP2058475A3 (en) * | 2007-11-09 | 2012-04-04 | United Technologies Corporation | Cooled transition piece of a gas turbine engine and corresponding gas turbine engine |
| JP2009250242A (en) * | 2008-04-10 | 2009-10-29 | General Electric Co <Ge> | Combustor seal having multiple cooling fluid pathways |
| JP2009275701A (en) * | 2008-05-13 | 2009-11-26 | General Electric Co <Ge> | Method and device for cooling and dilution-adjusting gas turbine combustor liner and transition piece joint part |
| JP2010196702A (en) * | 2009-02-26 | 2010-09-09 | General Electric Co <Ge> | Gas turbine combustion system cooling arrangement |
| FR2959795A1 (en) * | 2010-05-05 | 2011-11-11 | Snecma | Combustion chamber for turbomachine, has case flanges that are cooperated with terminal flanges to ensure maintenance of chamber in position, where one terminal flange is arranged to cooperate with one case flange through sliding contact |
| US8713945B2 (en) | 2010-06-29 | 2014-05-06 | Nuovo Pignone S.P.A. | Liner aft end support mechanisms and spring loaded liner stop mechanisms |
| CN103443421A (en) * | 2011-03-30 | 2013-12-11 | 三菱重工业株式会社 | Combustor and gas turbine provided with same |
| WO2012132898A1 (en) * | 2011-03-30 | 2012-10-04 | 三菱重工業株式会社 | Combustor and gas turbine provided with same |
| JPWO2012132898A1 (en) * | 2011-03-30 | 2014-07-28 | 三菱重工業株式会社 | Combustor and gas turbine provided with the same |
| KR101531124B1 (en) * | 2011-03-30 | 2015-06-23 | 미츠비시 히타치 파워 시스템즈 가부시키가이샤 | Combustor and gas turbine provided with same |
| US9957893B2 (en) | 2011-03-30 | 2018-05-01 | Mitsubishi Hitachi Power Systems, Ltd. | Combustor and gas turbine provided with same |
| JP2014178076A (en) * | 2013-03-15 | 2014-09-25 | Mitsubishi Heavy Ind Ltd | Elastic ring, and combustor and gas turbine with the same |
| KR101662121B1 (en) * | 2015-07-06 | 2016-10-04 | 두산중공업 주식회사 | The invention of liner and transition piece connection |
| JP2018071801A (en) * | 2016-10-24 | 2018-05-10 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
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