JP2003214185A - Gas turbine combustor cooling structure and gas turbine - Google Patents
Gas turbine combustor cooling structure and gas turbineInfo
- Publication number
- JP2003214185A JP2003214185A JP2002012825A JP2002012825A JP2003214185A JP 2003214185 A JP2003214185 A JP 2003214185A JP 2002012825 A JP2002012825 A JP 2002012825A JP 2002012825 A JP2002012825 A JP 2002012825A JP 2003214185 A JP2003214185 A JP 2003214185A
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- Prior art keywords
- cooling
- gas turbine
- wall portion
- air
- turbine combustor
- Prior art date
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Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、ガスタービンの燃
焼器の内筒や尾筒等に採用される壁部材の冷却構造と、
それを有するガスタービンに関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a cooling structure for a wall member used for an inner cylinder or a transition cylinder of a gas turbine combustor,
It relates to a gas turbine having it.
【０００２】[0002]
【従来の技術】ガスタービン１００は一般に、図４にそ
の要部の縦断面を示すように、圧縮機部１とタービン部
２が同軸に設けられ、その間に中心軸Ｘ周りに複数の燃
焼器３が配設されている。2. Description of the Related Art Generally, a gas turbine 100 is provided with a compressor section 1 and a turbine section 2 coaxially with each other, and a plurality of combustors around a central axis X, as shown in FIG. 3 are provided.
【０００３】燃焼器３はパイロットノズル３２の周りに
複数のメインノズル３１が配設され、それらからの燃料
は燃焼室３３で燃焼し、燃焼ガスは尾筒３４を通ってタ
ービン部２へ駆動ガスとして吹き込まれる。In the combustor 3, a plurality of main nozzles 31 are arranged around a pilot nozzle 32, fuel from them burns in a combustion chamber 33, and combustion gas passes through a transition piece 34 to drive gas to the turbine section 2. Is blown in as.
【０００４】したがって、燃焼室３３の内壁部Ｙや尾筒
３４の壁部Ｚは高温のガスに曝されるため、何らかの冷
却構造を備える必要がある。Therefore, since the inner wall portion Y of the combustion chamber 33 and the wall portion Z of the transition piece 34 are exposed to the high temperature gas, it is necessary to have some kind of cooling structure.
【０００５】そのような燃焼室３３の内壁部Ｙや尾筒３
４の壁部Ｚに用いられる従来のガスタービン燃焼器冷却
構造の例の断面を、図５に示す。The inner wall portion Y of the combustion chamber 33 and the transition piece 3
A cross section of an example of a conventional gas turbine combustor cooling structure used for the wall portion Z of No. 4 is shown in FIG.
【０００６】燃焼室３３の内壁部Ｙや尾筒３４の壁部Ｚ
の壁部材０１０は、一方の面が高温ガス側３５に面し、
他方の面が燃焼用空気の一部を冷却用に用いる冷却空気
ａの供給される冷却空気側３６に面し、高温ガス側３５
と冷却空気側３６とを仕切っており、燃焼器３内の圧力
変動による燃焼振動を防止するために冷却空気側の壁面
の一部はカバー２０に覆われたキャビティー２１を有す
る二重壁部０１０ａを形成している。The inner wall portion Y of the combustion chamber 33 and the wall portion Z of the transition piece 34.
The wall member 010 of the one of which the one surface faces the hot gas side 35,
The other surface faces the cooling air side 36 to which the cooling air a used for cooling a part of the combustion air is supplied, and the high temperature gas side 35.
And a cooling air side 36 are separated from each other, and in order to prevent combustion oscillation due to pressure fluctuation in the combustor 3, a part of the cooling air side wall surface has a cavity 21 covered with a cover 20. 010a is formed.
【０００７】キャビティー２１は、壁部材０１０に穿孔
された吸音孔２２によって高温ガス側３５と連通し、高
温ガス側３５で発生した燃焼振動が吸音孔２２を介して
キャビティー２１により吸収減衰されるものとなってい
る。The cavity 21 communicates with the high temperature gas side 35 through a sound absorbing hole 22 formed in the wall member 010, and combustion vibration generated on the high temperature gas side 35 is absorbed and damped by the cavity 21 through the sound absorbing hole 22. It has become one.
【０００８】そして壁部材０１０の他の部分には、構造
上カバー２０で覆われていない一重壁部０１０ｂとなっ
ている部分もある。Another portion of the wall member 010 is a single wall portion 010b which is not covered by the cover 20 structurally.
【０００９】上記のような従来のガスタービン１００の
燃焼器３では、二重壁部０１０ａにおいては、カバーに
吸音孔２２と位置をずらして穿孔されたインピンジメン
ト冷却孔２３から吹き込まれた冷却空気ａが、キャビテ
ィー２１内の壁部材０１０に衝突してインピンジメント
冷却を行い、一重壁部０１０ｂにおいては冷却空気側３
６の冷却空気ａが壁部材０１０の壁面と接することによ
って冷却が行われていた。なお、吸音孔２２の径は通
常、インピンジメント冷却孔２３の径の１〜５倍であ
る。In the conventional combustor 3 of the gas turbine 100 as described above, in the double wall portion 010a, the cooling air blown from the impingement cooling hole 23 formed at the cover in a position shifted from the sound absorbing hole 22. a collides with the wall member 010 in the cavity 21 to perform impingement cooling, and in the single wall portion 010b, the cooling air side 3
Cooling was performed by the cooling air a of No. 6 coming into contact with the wall surface of the wall member 010. The diameter of the sound absorbing holes 22 is usually 1 to 5 times the diameter of the impingement cooling holes 23.
【００１０】[0010]
【発明が解決しようとする課題】上記のような従来のガ
スタービン１００の燃焼器３の冷却構造では、二重壁部
０１０ａにおいては、インピンジメント冷却により効果
的な壁部材０１０の冷却が行えるが、一重壁部０１０ｂ
は冷却空気側３６の冷却空気ａと接するだけなので、冷
却が十分に行われず高温化する問題があった。In the conventional cooling structure for the combustor 3 of the gas turbine 100 as described above, the double wall portion 010a can effectively cool the wall member 010 by impingement cooling. , Single wall 010b
Since it only contacts the cooling air a on the cooling air side 36, there is a problem that cooling is not performed sufficiently and the temperature rises.
【００１１】また、二重壁部０１０ａにおいて、冷却孔
２２から高温の燃焼ガスがキャビティー２１内に流入す
ることを防止し、また冷却効果を上げるには、インピン
ジメント冷却用に吹き込まれる冷却空気ａの使用量を大
きくする必要があり、低ＮＯｘ燃焼に影響を与えるとい
う問題があった。Further, in the double wall portion 010a, in order to prevent high temperature combustion gas from flowing into the cavity 21 from the cooling hole 22 and to enhance the cooling effect, cooling air blown for impingement cooling is used. There is a problem that it is necessary to increase the amount of a used, which affects low NOx combustion.
【００１２】本発明は、かかる従来のガスタービン燃焼
器冷却構造の問題を解消し、燃焼器内の圧力変動を減衰
できるとともに、冷却空気の使用を減じ、燃焼器の壁部
材を効率よく冷却できるガスタービン燃焼器冷却構造と
それを用いたガスタービンを提供することを目的とする
ものである。The present invention solves the problems of the conventional cooling structure of a gas turbine combustor, can reduce the pressure fluctuation in the combustor, reduce the use of cooling air, and efficiently cool the wall member of the combustor. An object of the present invention is to provide a gas turbine combustor cooling structure and a gas turbine using the same.
【００１３】[0013]
【課題を解決するための手段】（１）本発明は、上記の
課題を解決するためになされたものであって、その第１
の手段として、ガスタービン燃焼器において冷却空気側
と高温ガス側とを仕切る壁部材の冷却空気側をカバーで
覆いキャビティーを形成した二重壁部を有し、前記カバ
ーにインピンジメント冷却孔を備え、前記二重壁部の前
記壁部材に前記高温ガス側と前記キャビティーとを連通
する吸音孔を備えたガスタービン燃焼器冷却構造であっ
て、前記壁部材内に冷却蒸気を通す蒸気冷却通路を前記
吸音孔をかわして設けてなることを特徴とするガスター
ビン燃焼器冷却構造を提供する。(1) The present invention has been made in order to solve the above-mentioned problems.
As a means of having a double wall portion which forms a cavity by covering the cooling air side of the wall member that separates the cooling air side and the high temperature gas side in the gas turbine combustor with a cover, and has an impingement cooling hole in the cover. A gas turbine combustor cooling structure, comprising: a sound absorbing hole for communicating the high temperature gas side and the cavity in the wall member of the double wall portion, wherein steam cooling is provided for passing cooling steam into the wall member. There is provided a gas turbine combustor cooling structure characterized in that a passage is provided so as to avoid the sound absorbing hole.
【００１４】以上のように構成された第１の手段によれ
ば、キャビティーによる燃焼振動減衰を奏しつつ、壁部
材は二重壁部においてインピンジメント冷却孔による冷
却と蒸気冷却通路により効果的に冷却が行われるため、
従来のインピンジメント冷却孔のみによる冷却において
吸音孔から高温ガス側へ流入する冷却空気の量より流入
空気量を少なく設定することができ、また、二重壁部以
外の一重壁部においては、従来の壁面の冷却空気との接
触のみによる冷却に比べ十分な冷却が行われる。According to the first means constructed as described above, while the combustion vibration is attenuated by the cavity, the wall member is effectively cooled by the impingement cooling holes and the steam cooling passage in the double wall portion. Because cooling is done,
In the conventional cooling with only impingement cooling holes, the amount of inflow air can be set smaller than the amount of cooling air flowing from the sound absorbing holes to the high temperature gas side. Sufficient cooling is performed as compared with the cooling by only contacting the wall surface with the cooling air.
【００１５】（２）第２の手段としては、第１の手段の
ガスタービン燃焼器冷却構造において、前記二重壁部以
外の壁部材における複数の前記蒸気冷却通路の設置密度
を、前記二重壁部の壁部材における複数の前記蒸気冷却
通路の設置密度より高くしてなることを特徴とするガス
タービン燃焼器冷却構造を提供する。(2) As a second means, in the gas turbine combustor cooling structure of the first means, the installation density of the plurality of steam cooling passages in the wall member other than the double wall portion is set to the double There is provided a gas turbine combustor cooling structure having a density higher than the installation density of a plurality of the steam cooling passages in a wall member of a wall portion.
【００１６】第２の手段によれば、第１の手段の作用に
加え、インピンジメント冷却孔による冷却が行われない
二重壁部以外の一重壁部での壁部材の冷却用蒸気による
冷却が強化される。According to the second means, in addition to the function of the first means, the cooling of the wall member by the cooling steam at the single wall portion other than the double wall portion where the cooling by the impingement cooling holes is not performed. To be strengthened.
【００１７】（３）また、第３の手段として、ガスター
ビン燃焼器において冷却空気側と高温ガス側とを仕切る
壁部材の冷却空気側をカバーで覆いキャビティーを形成
した二重壁部を有し、前記カバーにインピンジメント冷
却孔を備え、前記二重壁部の前記壁部材に前記高温ガス
側と前記キャビティーとを連通する吸音孔を備えたガス
タービン燃焼器冷却構造であって、前記壁部材内に冷却
空気を通す空気冷却通路を前記吸音孔をかわして設け、
同空気冷却通路は前記二重壁部以外において前記冷却空
気側と連通する冷却空気入口を備え且つ前記二重壁部に
おいて前記高温ガス側と連通する冷却空気出口を備えて
なることを特徴とするガスタービン燃焼器冷却構造を提
供する。(3) As a third means, the gas turbine combustor has a double wall portion having a cavity formed by covering the cooling air side of the wall member for partitioning the cooling air side and the high temperature gas side with a cover. And a cover having an impingement cooling hole, the wall member of the double wall portion is a gas turbine combustor cooling structure having a sound absorbing hole communicating the high temperature gas side and the cavity, An air cooling passage for passing cooling air is provided in the wall member, bypassing the sound absorbing hole,
The air cooling passage has a cooling air inlet communicating with the cooling air side other than the double wall portion and a cooling air outlet communicating with the hot gas side in the double wall portion. A gas turbine combustor cooling structure is provided.
【００１８】第３の手段によれば、別途蒸気冷却のため
の冷却蒸気供給と排出の装置を加える必要がなく、キャ
ビティーによる燃焼振動減衰を奏しつつ、壁部材は二重
壁部においてインピンジメント冷却孔による冷却と空気
冷却通路により効果的に冷却が行われるため、従来のイ
ンピンジメント冷却孔のみによる冷却において吸音孔か
ら高温ガス側へ流入する冷却空気の量より流入空気量を
少なく設定することができ、また、二重壁部以外の一重
壁部においては、従来の壁面の冷却空気の接触のみによ
る冷却に比べ十分な冷却が行われる。According to the third means, it is not necessary to separately add a cooling steam supply and discharge device for cooling the steam, and the wall vibration is damped by the combustion vibration, and the wall member is impinged in the double wall portion. Since the cooling by the cooling holes and the cooling by the air cooling passage are performed effectively, the inflow air amount should be set smaller than the amount of cooling air flowing from the sound absorbing holes to the high temperature gas side in the conventional cooling by only the impingement cooling holes. In addition, in the single wall portion other than the double wall portion, sufficient cooling is performed as compared with the conventional cooling by only contacting cooling air on the wall surface.
【００１９】（４）第４の手段として、第３の手段のガ
スタービン燃焼器冷却構造において、前記冷却空気出口
に代えて前記空気冷却通路は前記二重壁部において前記
キャビティーと連通する連通孔を備えてなることを特徴
とするガスタービン燃焼器冷却構造を提供する。(4) As a fourth means, in the gas turbine combustor cooling structure according to the third means, the air cooling passage, instead of the cooling air outlet, communicates with the cavity at the double wall portion. Provided is a gas turbine combustor cooling structure comprising holes.
【００２０】第４の手段によれば、第３の手段の作用に
加え、空気冷却通路の冷却空気が一旦キャビティーに入
り吸音孔から高温ガス側に流出するので、キャビティー
に高温燃焼ガスが流入することが防止される。According to the fourth means, in addition to the function of the third means, since the cooling air in the air cooling passage once enters the cavity and flows out from the sound absorbing hole to the high temperature gas side, the high temperature combustion gas is introduced into the cavity. Inflow is prevented.
【００２１】（５）第５の手段として、第１の手段ない
し第４の手段のいずれかのガスタービン燃焼器冷却構造
を有してなることを特徴とするガスタービンを提供す
る。(5) As a fifth means, there is provided a gas turbine comprising the gas turbine combustor cooling structure according to any one of the first means to the fourth means.
【００２２】第５の手段によれば、第１の手段ないし第
４の手段の作用を奏することによりガスタービンは、燃
焼器の冷却の効率化と空気混合の適切化によって燃焼効
率が向上し、より低ＮＯｘな燃焼が可能となる。According to the fifth means, the gas turbine has the effects of the first means to the fourth means, so that the combustion efficiency of the gas turbine is improved by improving the efficiency of cooling the combustor and optimizing the air mixing. Combustion with lower NOx becomes possible.
【００２３】[0023]
【発明の実施の形態】図１に基づき、本発明の実施の第
１形態に係るガスタービン燃焼器冷却構造を説明する。
図１（ａ）は、図４に示した燃焼室３３の内壁部Ｙや尾
筒３４の壁部Ｚに用いられる本実施の形態のガスタービ
ン燃焼器冷却構造の断面図、（ｂ）は（ａ）中Ａ−Ａ矢
視断面図、（ｃ）は（ａ）中Ｂ−Ｂ矢視断面図、（ｄ）
は（ａ）中Ｃ−Ｃ矢視断面図である。なお図１（ａ）
は、（ｂ）中Ｄ−Ｄ矢視断面図となる。DESCRIPTION OF THE PREFERRED EMBODIMENTS A gas turbine combustor cooling structure according to a first embodiment of the present invention will be described with reference to FIG.
1A is a cross-sectional view of the gas turbine combustor cooling structure of the present embodiment used for the inner wall portion Y of the combustion chamber 33 and the wall portion Z of the transition piece 34 shown in FIG. 4, and FIG. a) a sectional view taken along the arrow AA in the middle, (c) a sectional view taken along the arrow BB in the middle of (a), (d)
FIG. 8A is a sectional view taken along the line CC in FIG. Note that FIG. 1 (a)
Is a sectional view taken along the line DD in (b).
【００２４】本実施の形態においても、図５に示した従
来例のように、壁部材１０の二重壁部１０ａにおいて
は、カバー２０に吸音孔２２と位置をずらして穿孔され
たインピンジメント冷却孔２３が設けられ、インピンジ
メント冷却孔２３から吹き込まれた冷却空気ａが、キャ
ビティー２１内の壁部材１０に衝突してインピンジメン
ト冷却を行い、一重壁部１０ｂにおいては壁部材１０の
壁面が冷却空気側３６の冷却空気ａと接することによっ
て冷却が行われるが、本実施の形態においては、インピ
ンジメント冷却孔２３は吸音孔２２と交互に並んだ列を
なして配置されており、壁部材１０内にはその列の間に
平行に複数の蒸気冷却通路１１が吸音孔２２をかわして
設けられていることに特徴がある。Also in this embodiment, as in the conventional example shown in FIG. 5, in the double wall portion 10a of the wall member 10, the impingement cooling is formed in the cover 20 at a position displaced from the sound absorbing hole 22. The hole 23 is provided, and the cooling air a blown from the impingement cooling hole 23 collides with the wall member 10 in the cavity 21 to perform impingement cooling, and the wall surface of the wall member 10 in the single wall portion 10b is Cooling is performed by contacting the cooling air a on the cooling air side 36, but in the present embodiment, the impingement cooling holes 23 are arranged in rows alternately arranged with the sound absorbing holes 22, and the wall member It is characterized in that a plurality of steam cooling passages 11 are provided in parallel with each other in the column 10 so as to avoid the sound absorbing holes 22.
【００２５】蒸気冷却通路１１には図示しない冷却蒸気
供給部から冷却用蒸気が供給され、図示しない冷却蒸気
排出部から冷却用蒸気が排出される。Cooling steam is supplied to the steam cooling passage 11 from a cooling steam supply section (not shown), and cooling steam is discharged from a cooling steam discharge section (not shown).
【００２６】また、一重壁部１０ｂはインピンジメント
冷却孔２３による冷却が行われないので、冷却用蒸気に
よる冷却を強化することが望ましく、一重壁部１０ｂの
複数の蒸気冷却通路１１’の配置密度は、二重壁部１０
ａの複数の蒸気冷却通路１１の配置密度より高く設けら
れる。Further, since the single wall portion 10b is not cooled by the impingement cooling holes 23, it is desirable to enhance the cooling by the cooling steam, and the arrangement density of the plurality of steam cooling passages 11 'of the single wall portion 10b is desired. Is the double wall 10
It is provided at a higher density than the arrangement density of the plurality of steam cooling passages 11a.
【００２７】したがってピッチが異なる二重壁部１０ａ
の蒸気冷却通路１１と、一重壁部１０ｂの蒸気冷却通路
１１’とを連通するためには、壁部材１０内に蒸気冷却
通路１１、１１’と直角に交わって連通し、蓋１３で塞
がれた溝１２が連絡通路として設けられる。Therefore, the double wall portions 10a having different pitches
In order to connect the steam cooling passage 11 of FIG. 1 and the steam cooling passage 11 ′ of the single wall portion 10b to each other, the wall cooling member 10 communicates with the steam cooling passages 11 and 11 ′ at right angles, and is closed by the lid 13. The groove 12 is provided as a communication passage.
【００２８】以上のように構成された本実施の形態のガ
スタービン燃焼器冷却構造によれば、キャビティー２１
によって燃焼振動の圧力変動を減衰しつつ、壁部材１０
は二重壁部１０ａにおいてインピンジメント冷却孔２３
による冷却と蒸気冷却通路１１により効果的に冷却が行
われるため、従来のインピンジメント冷却孔２３のみに
よる冷却においてインピンジメント冷却孔２３から吹き
込まれ吸音孔２２から高温ガス側へ流入する冷却空気ａ
の量より流入空気量を少なく設定することができ、燃焼
器３の燃焼状態にあたえる影響が少なくなり、低ＮＯｘ
燃焼への障害を低減できるものとなる。According to the gas turbine combustor cooling structure of the present embodiment configured as described above, the cavity 21
While attenuating the pressure fluctuation of the combustion vibration by the wall member 10
Is the impingement cooling hole 23 in the double wall portion 10a.
And the steam cooling passage 11 effectively cools the cooling air a that is blown from the impingement cooling holes 23 and flows into the high temperature gas side from the sound absorbing holes 22 in the conventional cooling using only the impingement cooling holes 23.
The amount of inflowing air can be set to be smaller than the amount of NOx.
The obstacle to combustion can be reduced.
【００２９】また、一重壁部１０ｂにおいては、蒸気冷
却通路１１’による冷却が加わり、従来の冷却空気ａの
接触のみによる冷却に比べ十分な冷却が行われ、一重壁
部１０ｂの高温化の問題が解消される。Further, in the single wall portion 10b, the cooling by the steam cooling passage 11 'is added, so that the single wall portion 10b is sufficiently cooled as compared with the conventional cooling only by the contact of the cooling air a, and the problem of the high temperature of the single wall portion 10b. Is eliminated.
【００３０】なお、壁部材１０に蒸気冷却通路１１、１
１’を設ける方法は適宜でよいが、例えば、板状部材の
一面に蒸気冷却通路１１、１１’となるべき溝を形成し
たのちその面を別の板状部材で塞いで一体化することに
より蒸気冷却通路１１、１１’を有する壁部材１０は容
易に形成できる。The wall member 10 has steam cooling passages 11, 1
The method of providing 1'may be arbitrary, for example, by forming a groove to be the steam cooling passages 11 and 11 'on one surface of the plate-shaped member and then closing the surface with another plate-shaped member for integration. The wall member 10 having the steam cooling passages 11 and 11 'can be easily formed.
【００３１】図２に基づき、本発明の実施の第２形態に
係るガスタービン燃焼器冷却構造を説明する。図２
（ａ）は、図４に示した燃焼室３３の内壁部Ｙや尾筒３
４の壁部Ｚに用いられる本実施の形態のガスタービン燃
焼器冷却構造の断面図、（ｂ）は（ａ）中Ｅ−Ｅ矢視断
面図、（ｃ）は（ａ）中Ｆ−Ｆ矢視断面図、（ｄ）は
（ａ）中Ｇ−Ｇ矢視断面図である。なお、図２（ａ）
は、（ｂ）中Ｈ−Ｈ矢視断面図となる。A gas turbine combustor cooling structure according to a second embodiment of the present invention will be described with reference to FIG. Figure 2
4A shows the inner wall portion Y of the combustion chamber 33 and the transition piece 3 shown in FIG.
4 is a cross-sectional view of the gas turbine combustor cooling structure of the present embodiment used for the wall portion Z of FIG. 4, (b) is a cross-sectional view taken along line EE in (a), and (c) is F-F in (a). Sectional view taken in the direction of the arrow, (d) is a sectional view taken along the line GG in FIG. 2 (a)
Is a sectional view taken along line H-H in FIG.
【００３２】本実施の形態においては、前述の実施の第
１形態に対して、蒸気冷却通路に代えて、壁部材４０内
に空気冷却通路４１を設けたことに特徴がある。The present embodiment is characterized in that an air cooling passage 41 is provided in the wall member 40 in place of the steam cooling passage, unlike the first embodiment described above.
【００３３】すなわち、本実施の形態においても、二重
壁部４０ａにおいては、カバー２０に吸音孔２２と位置
をずらして穿孔されたインピンジメント冷却孔２３が設
けられ、インピンジメント冷却孔２３から吹き込まれた
冷却空気ａが、キャビティー２１内の壁部材４０に衝突
してインピンジメント冷却を行い、一重壁部４０ｂにお
いては冷却空気側３６の冷却空気ａと接することによっ
て冷却が行われるが、インピンジメント冷却孔２３は吸
音孔２２と交互に並んだ列をなして配置されており、壁
部材４０内にはその列の間に平行に複数の空気冷却通路
４１が吸音孔２２をかわして設けられている。That is, also in the present embodiment, in the double wall portion 40a, the cover 20 is provided with the impingement cooling hole 23 which is perforated at a position different from the sound absorbing hole 22, and is blown from the impingement cooling hole 23. The cooled cooling air a collides with the wall member 40 in the cavity 21 to perform impingement cooling, and the single wall portion 40 b contacts the cooling air a on the cooling air side 36 to perform cooling. The ment cooling holes 23 are arranged in rows alternately arranged with the sound absorbing holes 22, and in the wall member 40, a plurality of air cooling passages 41 are provided in parallel between the rows so as to avoid the sound absorbing holes 22. ing.
【００３４】そして、一重壁部４０ｂにおいて空気冷却
通路４１は冷却空気側３６と連通する冷却空気入口４２
が設けられ、二重壁部４０ｂにおいて空気冷却通路４１
は高温ガス側３５と連通する冷却空気出口４３が設けら
れており、冷却空気ａは冷却空気側３６から冷却空気入
口４２を通り空気冷却通路４１に入り、壁部材４０を冷
却したのち冷却空気出口４３を通り高温ガス側３５に流
出する。In the single wall portion 40b, the air cooling passage 41 communicates with the cooling air side 36 and the cooling air inlet 42.
And the air cooling passage 41 is provided in the double wall portion 40b.
Is provided with a cooling air outlet 43 communicating with the hot gas side 35, and the cooling air a passes from the cooling air side 36 through the cooling air inlet 42 into the air cooling passage 41 to cool the wall member 40 and then the cooling air outlet. It flows through 43 to the hot gas side 35.
【００３５】以上のように構成された本実施の形態のガ
スタービン燃焼器冷却構造によれば、実施の第１形態の
ように別途蒸気冷却のための冷却蒸気供給と排出の装置
を加える必要がなく、キャビティー２１によって燃焼振
動の圧力変動を減衰しつつ、壁部材４０は二重壁部４０
ａにおいてインピンジメント冷却孔２３による冷却と空
気冷却通路４１により効果的に冷却が行われるため、従
来のインピンジメント冷却孔２３のみによる冷却におい
てインピンジメント冷却孔２３から吹き込まれ吸音孔２
２から高温ガス側へ流入する冷却空気ａの量より流入空
気量を少なく設定することができ、燃焼器の燃焼状態に
あたえる影響が少なくなり、低ＮＯｘ燃焼への障害を低
減できるものとなる。According to the gas turbine combustor cooling structure of the present embodiment configured as described above, it is necessary to separately add a cooling steam supply and discharge device for steam cooling as in the first embodiment. Instead, the cavity 21 damps the pressure fluctuation of the combustion vibration, and the wall member 40 has the double wall portion 40.
In a, the cooling by the impingement cooling holes 23 and the cooling by the air cooling passages 41 are effectively performed. Therefore, in the conventional cooling by only the impingement cooling holes 23, the sound absorption holes 2 are blown from the impingement cooling holes 23.
The amount of inflowing air can be set to be smaller than the amount of cooling air a flowing from 2 to the high temperature gas side, the influence given to the combustion state of the combustor is reduced, and the obstacle to low NOx combustion can be reduced.
【００３６】また、一重壁部４０ｂにおいては、空気冷
却通路４１による冷却が加わり、従来の冷却空気ａの接
触のみによる冷却に比べ十分な冷却が行われ、一重壁部
４０ｂの高温化の問題が解消される。Further, in the single wall portion 40b, the cooling by the air cooling passage 41 is added, and the single wall portion 40b is sufficiently cooled as compared with the conventional cooling only by the contact of the cooling air a, which causes a problem that the single wall portion 40b is heated. Will be resolved.
【００３７】なお、壁部材４０に空気冷却通路４１を設
ける方法は適宜でよいが、例えば、板状部材の一面に空
気冷却通路４１となるべき溝を形成したのちその面を別
の板状部材で塞いで一体化することにより空気冷却通路
４１を有する壁部材４０は容易に形成できる。The method of providing the air cooling passage 41 in the wall member 40 may be appropriately selected. For example, after forming a groove to be the air cooling passage 41 on one surface of the plate-shaped member, the surface is formed on another plate-shaped member. The wall member 40 having the air cooling passage 41 can be easily formed by closing with and integrating.
【００３８】図３に基づき、本発明の実施の第３形態に
係るガスタービン燃焼器冷却構造を説明する。図３は、
図４に示した燃焼室３３の内壁部Ｙや尾筒３４の壁部Ｚ
に用いられる本実施の形態のガスタービン燃焼器冷却構
造の断面図である。A gas turbine combustor cooling structure according to a third embodiment of the present invention will be described with reference to FIG. Figure 3
The inner wall portion Y of the combustion chamber 33 and the wall portion Z of the transition piece 34 shown in FIG.
FIG. 3 is a cross-sectional view of a gas turbine combustor cooling structure of the present embodiment used for
【００３９】本実施の形態においては、前述の実施の第
２形態に対して、空気冷却通路４１’から冷却空気ａが
一旦キャビティー２１に入ったのち吸音孔２２を通って
高温ガス側３５に流出するようにしたことに特徴があ
る。In the present embodiment, unlike the above-described second embodiment, the cooling air a once enters the cavity 21 from the air cooling passage 41 'and then passes through the sound absorbing holes 22 to reach the high temperature gas side 35. The feature is that it was made to leak.
【００４０】すなわち、本実施の形態においても、前述
の実施の第２形態と同様に二重壁部４０ａ’において
は、カバー２０にインピンジメント冷却孔２３が設けら
れ、インピンジメント冷却孔２３から吹き込まれた冷却
空気ａが、キャビティー２１内の壁部材４０’に衝突し
てインピンジメント冷却を行い、一重壁部４０ｂ’にお
いては冷却空気側３６の冷却空気ａと接することによっ
て冷却が行われ、インピンジメント冷却孔２３は吸音孔
２２と交互に列をなして配置されており、壁部材４０’
内にはその列の間に平行に複数の空気冷却通路４１’が
吸音孔２２をかわして設けられている。That is, also in the present embodiment, as in the second embodiment described above, in the double wall portion 40a ', the impingement cooling hole 23 is provided in the cover 20, and the impingement cooling hole 23 blows in. The cooled cooling air a collides with the wall member 40 ′ in the cavity 21 to perform impingement cooling, and the single wall portion 40 b ′ is cooled by contacting the cooling air a on the cooling air side 36, The impingement cooling holes 23 are arranged alternately in rows with the sound absorbing holes 22, and the wall members 40 'are arranged.
A plurality of air cooling passages 41 ′ are provided in parallel with each other in the row, bypassing the sound absorbing holes 22.
【００４１】そして、一重壁部４０ｂ’において空気冷
却通路４１’は冷却空気側３６と連通する冷却空気入口
４２’が設けられ、二重壁部４０ａ’において空気冷却
通路４１’はキャビティー２１と連通する連通孔４４が
設けられている。そのため、冷却空気ａは冷却空気側３
６から冷却空気入口４２’を通り空気冷却通路４１’に
入り、壁部材４０’を冷却したのち連通孔４４を通りキ
ャビティー２１に入り、インピンジメント冷却孔２３か
らの冷却空気ａと混ざって吸音孔２２から高温ガス側３
５に流出する。In the single wall portion 40b ', the air cooling passage 41' is provided with a cooling air inlet 42 'which communicates with the cooling air side 36, and in the double wall portion 40a', the air cooling passage 41 'is connected to the cavity 21. A communication hole 44 that communicates is provided. Therefore, the cooling air a is the cooling air side 3
6 through the cooling air inlet 42 'into the air cooling passage 41', cools the wall member 40 ', then through the communication hole 44 into the cavity 21, and mixes with the cooling air a from the impingement cooling hole 23 to absorb noise. Hole 22 to hot gas side 3
Outflow to 5.
【００４２】以上のように構成された本実施の形態のガ
スタービン燃焼器冷却構造によれば、実施の第１形態の
ように別途蒸気冷却のための冷却蒸気供給と排出の装置
を加える必要がなく、キャビティー２１によって燃焼振
動の圧力変動を減衰しつつ、壁部材４０’は二重壁部４
０ａ’においてインピンジメント冷却孔２３による冷却
と空気冷却通路４１’により効果的に冷却が行われるた
め、従来のインピンジメント冷却孔２３のみによる冷却
においてインピンジメント冷却孔２３から吹き込まれ吸
音孔２２から高温ガス側へ流入する冷却空気ａの量より
流入空気量を少なく設定することができ、燃焼器の燃焼
状態にあたえる影響が少なくなり、低ＮＯｘ燃焼への障
害を低減できるものとなる。According to the gas turbine combustor cooling structure of the present embodiment configured as described above, it is necessary to separately add a cooling steam supply and discharge device for steam cooling as in the first embodiment. Instead, the cavity 21 damps the pressure fluctuation of the combustion vibration, and the wall member 40 ′ has the double wall portion 4
At 0a ', the cooling by the impingement cooling holes 23 and the cooling by the air cooling passages 41' are effectively performed. Therefore, in the conventional cooling by only the impingement cooling holes 23, a high temperature is blown from the impingement cooling holes 23 through the sound absorbing holes 22. The amount of inflowing air can be set to be smaller than the amount of cooling air a flowing into the gas side, the influence given to the combustion state of the combustor is reduced, and the obstacle to low NOx combustion can be reduced.
【００４３】しかも空気冷却通路４１’の冷却空気ａは
一旦キャビティー２１に入りインピンジメント冷却孔２
３から吹き込まれた冷却空気ａとともに吸音孔２２から
高温ガス側３５に流出するので、吸音孔２２から排出す
る空気量が増え、キャビティー２１に高温燃焼ガスが流
入することを防止することが出来る。Moreover, the cooling air a in the air cooling passage 41 'once enters the cavity 21 and the impingement cooling hole 2
Since the cooling air a blown from 3 flows out from the sound absorbing hole 22 to the high temperature gas side 35, the amount of air discharged from the sound absorbing hole 22 increases and it is possible to prevent the high temperature combustion gas from flowing into the cavity 21. .
【００４４】また、一重壁部４０ｂ’においては、空気
冷却通路４１’による冷却が加わり従来の冷却空気ａの
接触のみによる冷却に比べ十分な冷却が行われ、一重壁
部４０ｂ’の高温化の問題が解消される。Further, the single wall portion 40b 'is cooled by the air cooling passage 41', and is cooled more sufficiently than the conventional cooling by only contact with the cooling air a, so that the temperature of the single wall portion 40b 'is raised. The problem goes away.
【００４５】以上、何れの実施の形態のガスタービン燃
焼器冷却構造においても、それを用いたガスタービン
は、燃焼器の冷却の効率化と空気混合の適切化によって
燃焼効率が向上し、より低ＮＯｘな燃焼を可能とするガ
スタービンとなる。As described above, in any of the gas turbine combustor cooling structures of any of the embodiments, the gas turbine using the same has improved combustion efficiency due to improved cooling efficiency of the combustor and proper air mixing, resulting in lower combustion efficiency. It becomes a gas turbine that enables NOx combustion.
【００４６】以上、本発明の実施の形態を説明したが、
本発明は上記実施の形態に限定されるものではなく、本
発明の範囲内でその具体的構造に種々の変更を加えてよ
いことはいうまでもない。The embodiment of the present invention has been described above.
Needless to say, the present invention is not limited to the above-described embodiments, and various modifications may be made to the specific structure within the scope of the present invention.
【００４７】[0047]
【発明の効果】（１）請求項１の発明によれば、ガスタ
ービン燃焼器冷却構造を、ガスタービン燃焼器において
冷却空気側と高温ガス側とを仕切る壁部材の冷却空気側
をカバーで覆いキャビティーを形成した二重壁部を有
し、前記カバーにインピンジメント冷却孔を備え、前記
二重壁部の前記壁部材に前記高温ガス側と前記キャビテ
ィーとを連通する吸音孔を備えたガスタービン燃焼器冷
却構造であって、前記壁部材内に冷却蒸気を通す蒸気冷
却通路を前記吸音孔をかわして設けてなるように構成し
たので、キャビティーによる燃焼振動減衰を奏しつつ、
壁部材は二重壁部においてインピンジメント冷却孔によ
る冷却と蒸気冷却通路により効果的に冷却が行われるた
め、従来のインピンジメント冷却孔のみによる冷却にお
いて吸音孔から高温ガス側へ流入する冷却空気の量より
流入空気量を少なく設定することができ、燃焼器の燃焼
状態にあたえる影響が少なくなり、低ＮＯｘ燃焼への障
害を低減できるものとなる。また、二重壁部以外の一重
壁部においては、従来の壁面の冷却空気との接触のみに
よる冷却に比べ十分な冷却が行われ、高温化の問題が解
消される。(1) According to the invention of claim 1, the cooling structure of the gas turbine combustor is such that the cooling air side of the wall member for partitioning the cooling air side and the high temperature gas side in the gas turbine combustor is covered with a cover. The cover has an impingement cooling hole, and the wall member of the double wall has a sound absorbing hole for communicating the high temperature gas side with the cavity. In the gas turbine combustor cooling structure, since the steam cooling passage for passing the cooling steam in the wall member is provided so as to avoid the sound absorbing hole, while suppressing the combustion vibration by the cavity,
Since the wall member is effectively cooled by the impingement cooling hole and the steam cooling passage in the double wall portion, the cooling air flowing from the sound absorbing hole to the high temperature gas side is cooled by the conventional impingement cooling hole alone. The amount of inflowing air can be set to be smaller than the amount, the influence given to the combustion state of the combustor is reduced, and obstacles to low NOx combustion can be reduced. Further, in the single wall portion other than the double wall portion, sufficient cooling is performed as compared with the conventional cooling by only contacting the wall surface with the cooling air, and the problem of high temperature is solved.
【００４８】（２）請求項２の発明によれば、請求項１
に記載のガスタービン燃焼器冷却構造において、前記二
重壁部以外の壁部材における複数の前記蒸気冷却通路の
設置密度を、前記二重壁部の壁部材における複数の前記
蒸気冷却通路の設置密度より高くしてなるように構成し
たので、請求項１の発明の効果に加え、インピンジメン
ト冷却孔による冷却が行われない二重壁部以外の一重壁
部での壁部材の冷却用蒸気による冷却が強化される。(2) According to the invention of claim 2, claim 1
In the gas turbine combustor cooling structure according to, the installation density of the plurality of steam cooling passages in the wall member other than the double wall portion, the installation density of the plurality of steam cooling passages in the wall member of the double wall portion. Since it is configured to be higher, in addition to the effect of the invention of claim 1, cooling by the cooling steam of the wall member at the single wall portion other than the double wall portion where cooling by the impingement cooling holes is not performed Will be strengthened.
【００４９】（３）請求項３の発明によれば、ガスター
ビン燃焼器冷却構造を、ガスタービン燃焼器において冷
却空気側と高温ガス側とを仕切る壁部材の冷却空気側を
カバーで覆いキャビティーを形成した二重壁部を有し、
前記カバーにインピンジメント冷却孔を備え、前記二重
壁部の前記壁部材に前記高温ガス側と前記キャビティー
とを連通する吸音孔を備えたガスタービン燃焼器冷却構
造であって、前記壁部材内に冷却空気を通す空気冷却通
路を前記吸音孔をかわして設け、同空気冷却通路は前記
二重壁部以外において前記冷却空気側と連通する冷却空
気入口を備え且つ前記二重壁部において前記高温ガス側
と連通する冷却空気出口を備えてなるように構成したの
で、別途蒸気冷却のための冷却蒸気供給と排出の装置を
加える必要がなく簡潔な装置構成が可能であり、キャビ
ティーによる燃焼振動減衰を奏しつつ、壁部材は二重壁
部においてインピンジメント冷却孔による冷却と空気冷
却通路により効果的に冷却が行われるため、従来のイン
ピンジメント冷却孔のみによる冷却において吸音孔から
高温ガス側へ流入する冷却空気の量より流入空気量を少
なく設定することができ、燃焼器の燃焼状態にあたえる
影響が少なくなり、低ＮＯｘ燃焼への障害を低減できる
ものとなる。また、二重壁部以外の一重壁部において
は、従来の壁面の冷却空気との接触のみによる冷却に比
べ十分な冷却が行われ、高温化の問題が解消される。(3) According to the third aspect of the invention, the cooling structure of the gas turbine combustor has a cavity in which the cooling air side of the wall member for partitioning the cooling air side and the high temperature gas side of the gas turbine combustor is covered with a cover. Has a double wall formed
A gas turbine combustor cooling structure comprising: an impingement cooling hole in the cover; and a sound absorbing hole for communicating the high temperature gas side and the cavity in the wall member of the double wall portion, wherein the wall member An air cooling passage through which cooling air is passed is provided inside the sound absorbing hole, the air cooling passage having a cooling air inlet communicating with the cooling air side other than the double wall portion, and the double wall portion including the cooling air inlet. Since it is configured to have a cooling air outlet that communicates with the high temperature gas side, a simple device configuration is possible without the need to add a separate cooling vapor supply and discharge device for cooling the vapor, and combustion by the cavity is possible. While damping the vibration, the wall member is effectively cooled by the impingement cooling holes and the air cooling passage in the double wall portion, so that the conventional impingement cooling is performed. In the case of cooling by only the amount of inflow air can be set smaller than the amount of cooling air flowing into the high temperature gas side from the sound absorbing hole, the influence given to the combustion state of the combustor is reduced, and the obstacle to low NOx combustion can be reduced. Will be things. Further, in the single wall portion other than the double wall portion, sufficient cooling is performed as compared with the conventional cooling by only contacting the wall surface with the cooling air, and the problem of high temperature is solved.
【００５０】（４）請求項４の発明によれば、請求項３
に記載のガスタービン燃焼器冷却構造において、前記冷
却空気出口に代えて前記空気冷却通路は前記二重壁部に
おいて前記キャビティーと連通する連通孔を備えてなる
ように構成したので、請求項３の発明の効果に加え、空
気冷却通路の冷却空気が一旦キャビティーに入り吸音孔
から高温ガス側に流出するため、キャビティーに高温燃
焼ガスが流入することが防止される。(4) According to the invention of claim 4, claim 3
4. The gas turbine combustor cooling structure according to claim 3, wherein the air cooling passage is provided with a communication hole communicating with the cavity in the double wall portion instead of the cooling air outlet. In addition to the effect of the present invention, since the cooling air in the air cooling passage once enters the cavity and flows out from the sound absorbing hole to the high temperature gas side, the high temperature combustion gas is prevented from flowing into the cavity.
【００５１】（５）請求項５の発明によれば、ガスター
ビンを、請求項１ないし請求項４のいずれかに記載のガ
スタービン燃焼器冷却構造を有してなるように構成した
ので、請求項１ないし請求項４の発明の効果を奏するこ
とにより、ガスタービンは、燃焼器の冷却の効率化と空
気混合の適切化によって燃焼効率が向上し、より低ＮＯ
ｘな燃焼を可能とするガスタービンとなる。(5) According to the invention of claim 5, since the gas turbine is constituted to have the gas turbine combustor cooling structure according to any one of claims 1 to 4, According to the effects of the inventions of claim 1 to claim 4, the gas turbine has improved combustion efficiency by improving the efficiency of cooling the combustor and optimizing the air mixing, and has a lower NO
It becomes a gas turbine that enables x-ray combustion.
【図１】本発明の実施の第１形態に係るガスタービン燃
焼器冷却構造の説明図であり、（ａ）はガスタービン燃
焼器冷却構造の断面図、（ｂ）は（ａ）中Ａ−Ａ矢視断
面図、（ｃ）は（ａ）中Ｂ−Ｂ矢視断面図、（ｄ）は
（ａ）中Ｃ−Ｃ矢視断面図である。FIG. 1 is an explanatory diagram of a gas turbine combustor cooling structure according to a first embodiment of the present invention, (a) is a cross-sectional view of the gas turbine combustor cooling structure, and (b) is A- in (a). A sectional view taken along arrow A, (c) is a sectional view taken along line BB in (a), and (d) is a sectional view taken along line CC of (a).
【図２】本発明の実施の第２形態に係るガスタービン燃
焼器冷却構造の説明図であり、（ａ）は、ガスタービン
燃焼器冷却構造の断面図、（ｂ）は（ａ）中Ｅ−Ｅ矢視
断面図、（ｃ）は（ａ）中Ｆ−Ｆ矢視断面図、（ｄ）は
（ａ）中Ｇ−Ｇ矢視断面図である。FIG. 2 is an explanatory view of a gas turbine combustor cooling structure according to a second embodiment of the present invention, (a) is a cross-sectional view of the gas turbine combustor cooling structure, and (b) is an inside E of (a). -E arrow sectional view, (c) is a FF arrow sectional view in (a), (d) is a GG arrow sectional view in (a).
【図３】本発明の実施の第３形態に係るガスタービン燃
焼器冷却構造の説明図であり、ガスタービン燃焼器冷却
構造の断面図である。FIG. 3 is an explanatory diagram of a gas turbine combustor cooling structure according to a third embodiment of the present invention, and is a cross-sectional view of the gas turbine combustor cooling structure.
【図４】一般的なガスタービンの要部の縦断面図であ
る。FIG. 4 is a vertical cross-sectional view of a main part of a general gas turbine.
【図５】従来のガスタービン燃焼器冷却構造の例の断面
図である。FIG. 5 is a cross-sectional view of an example of a conventional gas turbine combustor cooling structure.
１ 圧縮機部 ２ タービン部 ３ 燃焼器 １０ 壁部材 １０ａ 二重壁部 １０ｂ 一重壁部 １１、１１’ 蒸気冷却通路 １２ 溝 １３ 蓋 ２０ カバー ２１ キャビティー ２２ 吸音孔 ２３ インピンジメント冷却孔 ３５ 高温ガス側 ３６ 冷却空気側 ４０、４０’ 壁部材 ４０ａ、４０ａ’ 二重壁部 ４０ｂ、４０ｂ’ 一重壁部 ４１、４１’ 空気冷却通路 ４２、４２’ 冷却空気入口 ４３ 冷却空気出口 ４４ 連通孔 １００ ガスタービン 1 Compressor section 2 turbine section 3 combustor 10 wall members 10a double wall 10b Single wall part 11, 11 'Steam cooling passage 12 grooves 13 lid 20 cover 21 cavity 22 Sound absorption hole 23 Impingement cooling holes 35 High temperature gas side 36 Cooling air side 40, 40 'wall member 40a, 40a 'double wall 40b, 40b 'single wall 41, 41 'Air cooling passage 42, 42 'Cooling air inlet 43 Cooling air outlet 44 communication hole 100 gas turbine
Claims (5)
と高温ガス側とを仕切る壁部材の冷却空気側をカバーで
覆いキャビティーを形成した二重壁部を有し、前記カバ
ーにインピンジメント冷却孔を備え、前記二重壁部の前
記壁部材に前記高温ガス側と前記キャビティーとを連通
する吸音孔を備えたガスタービン燃焼器冷却構造であっ
て、前記壁部材内に冷却蒸気を通す蒸気冷却通路を前記
吸音孔をかわして設けてなることを特徴とするガスター
ビン燃焼器冷却構造。1. A gas turbine combustor has a double wall portion which forms a cavity by covering a cooling air side of a wall member for partitioning the cooling air side and the high temperature gas side with a cover, and has an impingement cooling hole in the cover. A gas turbine combustor cooling structure comprising: a sound absorbing hole communicating between the high temperature gas side and the cavity in the wall member of the double wall portion, the steam passing cooling steam into the wall member. A gas turbine combustor cooling structure, wherein a cooling passage is provided so as to avoid the sound absorbing hole.
却構造において、前記二重壁部以外の壁部材における複
数の前記蒸気冷却通路の設置密度を、前記二重壁部の壁
部材における複数の前記蒸気冷却通路の設置密度より高
くしてなることを特徴とするガスタービン燃焼器冷却構
造。2. The gas turbine combustor cooling structure according to claim 1, wherein the installation density of the plurality of steam cooling passages in a wall member other than the double wall portion is set to a plurality in the wall member of the double wall portion. The gas turbine combustor cooling structure is characterized in that the installation density of the steam cooling passages is higher than the installation density.
と高温ガス側とを仕切る壁部材の冷却空気側をカバーで
覆いキャビティーを形成した二重壁部を有し、前記カバ
ーにインピンジメント冷却孔を備え、前記二重壁部の前
記壁部材に前記高温ガス側と前記キャビティーとを連通
する吸音孔を備えたガスタービン燃焼器冷却構造であっ
て、前記壁部材内に冷却空気を通す空気冷却通路を前記
吸音孔をかわして設け、同空気冷却通路は前記二重壁部
以外において前記冷却空気側と連通する冷却空気入口を
備え且つ前記二重壁部において前記高温ガス側と連通す
る冷却空気出口を備えてなることを特徴とするガスター
ビン燃焼器冷却構造。3. A gas turbine combustor having a double wall portion having a cavity formed by covering a cooling air side of a wall member for partitioning the cooling air side and the high temperature gas side with a cover, and having an impingement cooling hole in the cover. A gas turbine combustor cooling structure comprising a sound absorbing hole for communicating the high temperature gas side with the cavity in the wall member of the double wall portion, wherein air for passing cooling air into the wall member is provided. A cooling passage is provided so as to avoid the sound absorbing hole, and the air cooling passage has a cooling air inlet communicating with the cooling air side other than the double wall portion, and cooling communicating with the high temperature gas side in the double wall portion. A gas turbine combustor cooling structure comprising an air outlet.
却構造において、前記冷却空気出口に代えて前記空気冷
却通路は前記二重壁部において前記キャビティーと連通
する連通孔を備えてなることを特徴とするガスタービン
燃焼器冷却構造。4. The gas turbine combustor cooling structure according to claim 3, wherein instead of the cooling air outlet, the air cooling passage includes a communication hole that communicates with the cavity in the double wall portion. Gas turbine combustor cooling structure characterized by.
のガスタービン燃焼器冷却構造を有してなることを特徴
とするガスタービン。5. A gas turbine comprising the gas turbine combustor cooling structure according to any one of claims 1 to 4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2002012825A JP2003214185A (en) | 2002-01-22 | 2002-01-22 | Gas turbine combustor cooling structure and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2002012825A JP2003214185A (en) | 2002-01-22 | 2002-01-22 | Gas turbine combustor cooling structure and gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2003214185A true JP2003214185A (en) | 2003-07-30 |
Family
ID=27649927
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2002012825A Withdrawn JP2003214185A (en) | 2002-01-22 | 2002-01-22 | Gas turbine combustor cooling structure and gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2003214185A (en) |
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| US7089741B2 (en) | 2003-08-29 | 2006-08-15 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
| JP2008274774A (en) * | 2007-04-25 | 2008-11-13 | Mitsubishi Heavy Ind Ltd | Gas turbine combustor and gas turbine |
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