WO2009087847A1 - ガスタービンの排気部の構造およびガスタービン - Google Patents
ガスタービンの排気部の構造およびガスタービン Download PDFInfo
- Publication number
- WO2009087847A1 WO2009087847A1 PCT/JP2008/072327 JP2008072327W WO2009087847A1 WO 2009087847 A1 WO2009087847 A1 WO 2009087847A1 JP 2008072327 W JP2008072327 W JP 2008072327W WO 2009087847 A1 WO2009087847 A1 WO 2009087847A1
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- WIPO (PCT)
- Prior art keywords
- strut
- gas
- turbine
- casing
- air
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/321—Application in turbines in gas turbines for a special turbine stage
- F05D2220/3215—Application in turbines in gas turbines for a special turbine stage the last stage of the turbine
Definitions
- the present invention relates to a structure of an exhaust part of a gas turbine and a gas turbine.
- an exhaust casing of a gas turbine is provided with a diffuser that efficiently recovers the pressure of high-temperature gas discharged from the turbine, a bearing that rotatably supports a rotor, a strut that supports the bearing with respect to a casing, and the like. It has been. Furthermore, in order to measure the vibration state during the operation of the gas turbine, an instrument such as a vibrometer is arranged around the bearing.
- the strut is cooled by supplying air extracted from the compressor section of the gas turbine to the strut.
- air is extracted from the compressor unit and used for cooling, there is a problem that the efficiency of the gas turbine is reduced by the amount of air extracted.
- the extracted air compressed and heated by the compressor section is further heated to be around the bearing. Will flow.
- the temperature of the extracted air is, for example, about 200 ° C., and may be heated to, for example, about 400 ° C. or more after the strut is cooled. is there.
- the instrumentation arranged around the bearing has low resistance to high heat, the instrumentation has a risk of being damaged by air heated to, for example, about 400 ° C. or more as described above.
- the present invention has been made in order to solve the above-described problem, and is capable of cooling the strut and reducing the temperature around the bearing without reducing the efficiency of the gas turbine. And to provide a gas turbine.
- a first aspect of the present invention includes a casing in which a gas path portion is formed, a bearing portion that rotatably supports a rotor blade of a turbine portion, a strut that extends inward from the casing and supports the bearing portion, An opening formed in the casing, and extends from the opening along the strut toward the bearing portion, guides air to the gas path portion, and on the downstream side of the final stage moving blade in the turbine portion, The structure of the exhaust part of the gas turbine provided with the cooling flow path opened in the gas path part is provided.
- the air outside the casing and the air having a temperature lower than that of the exhaust gas flowing through the gas path portion is cooled from the opening. It flows into the road and is led to the gas path.
- the air flowing through the cooling flow path flows along the strut, it takes heat of the strut and cools the strut.
- the downstream side of the last stage rotor blade in the turbine section is one of the regions where the pressure is lowest in the gas path section, the pressure difference between the open ends of the cooling flow path becomes large. Therefore, more low-temperature air flows through the cooling channel than in the case where the cooling channel is open to another region.
- a strut cover extending along the strut and forming a space with the strut is provided, and the space between the strut and the strut cover is the cooling channel. It is desirable to form a part of
- the inner diffuser extending along the rotation axis of the turbine portion and forming a space with the bearing portion, and extending from the casing to support the inner diffuser,
- a hollow strut that allows communication between the outside of the casing and the inside of the inner diffuser, and a lid that adjusts an opening area of the hollow strut with respect to the casing are provided, and a space between the bearing portion and the inner diffuser is provided. It is desirable to form the cooling flow path.
- the bearings can be cooled by air at a temperature lower than that of the exhaust gas flowing through the gas path flowing into the cooling flow path via the hollow strut.
- the air flow rate can be limited by the lid that adjusts the opening area, and a decrease in the air flow rate for cooling the struts is prevented.
- a compressor unit that compresses air
- a combustor that mixes and combusts air and fuel compressed by the compressor unit, and generates combustion gas, and is rotationally driven from the combustion gas.
- a gas turbine provided with a turbine section for extracting force and the exhaust section of the present invention into which exhaust gas exhausted from the turbine section flows.
- the exhaust part according to the first aspect of the present invention, the strut, the bearing part, the instrumentation and the like arranged around the bearing part, It is cooled by the air flowing through.
- the strut is used to evacuate the air outside the casing by the pressure difference between the outside of the casing and the inside of the gas path part.
- the strut can be cooled, and the strut and the periphery of the bearing can be cooled without being affected by load fluctuations without reducing the efficiency of the gas turbine.
- FIG. 3 is a cross-sectional view taken along the line AA for explaining the configuration of the exhaust section of FIG. 2. It is a perspective view explaining the structure of the seal ring holding
- FIG. 1 is a schematic diagram illustrating the configuration of a gas turbine according to the present embodiment.
- the gas turbine 1 of the present embodiment includes a compressor unit 2 that compresses air, a combustor 3 that mixes and combusts the compressed air and fuel, and generates combustion gas.
- a turbine unit 4 that extracts rotational driving force from the combustion gas, and an exhaust unit 5 into which exhaust gas exhausted from the turbine unit 4 flows are provided.
- the compressor unit 2 compresses the sucked air and supplies it to the combustor 3.
- the compressor unit 2 is provided on the rotary shaft 6 together with the turbine unit 4, and is driven to rotate by the turbine unit 4.
- the combustor 3 mixes the compressed air supplied from the compressor unit 2 and fuel, and burns the air-fuel mixture. High-temperature flue gas generated by combustion is supplied to the turbine unit 4.
- the turbine unit 4 extracts the rotational driving force from the combustion gas supplied from the combustor 3 and supplies the rotational driving force to the compressor unit 2 and other devices. Exhaust gas discharged from the turbine section 4 flows into the exhaust section 5.
- FIG. 2 is a partially enlarged view for explaining the configuration of the exhaust section of FIG. 3 is a cross-sectional view taken along the line AA for explaining the configuration of the exhaust section of FIG.
- the exhaust part 5 has a gas path part 7 into which exhaust gas discharged from the turbine part 4 flows.
- the exhaust portion 5 includes a casing 11 that forms the outer shape of the exhaust portion 5, a bearing portion 12 that rotatably supports the rotary shaft 6, and an inner side that covers the periphery of the bearing portion 12.
- a diffuser 13, a strut 14 that supports the bearing portion 12, a strut cover 15 that covers the periphery of the strut 14, and a hollow strut 16 that supports the inner diffuser 13 are provided.
- the exhaust part 5 is provided with a cooling flow path 17 that guides air for cooling the struts 14 from the outside of the casing 11.
- the casing 11 forms the gas path portion 7 between the casing 11 and the inner diffuser 13, and forms a diffuser in which the cross-sectional area of the gas path portion 7 gradually increases toward the downstream side (right side in FIG. 2).
- a strut 14 is arranged on the turbine section 4 side on the inner peripheral surface of the casing 11 so as to extend toward the rotating shaft 6, and a cooling flow path 17 is arranged in an annular shape at a mounting portion on the radially outer side of the strut 14.
- the casing 11 is provided with an opening 18 that allows the cooling flow path 17 and the outside of the casing 11 to communicate with each other.
- the bearing portion 12 is supported by the six struts 14 and is described as being applied to an example in which the opening 18 is provided between the six struts 14, but the number of struts 14 and The position where the opening 18 is provided is not particularly limited to the above-described embodiment.
- a strut cover 15 extending in the radial direction along the strut 14 is disposed around the strut 14 while forming a space with the strut 14.
- a space between the strut 14 and the strut cover 15 constitutes a part of the cooling flow path 17 and communicates with the cooling flow path 17 disposed on the inner peripheral surface of the casing 11.
- the bearing portion 12 supports the rotary shaft 6 in a rotatable manner, and is supported by a strut 14 extending from the casing 11.
- a seal ring holding part 20 is arranged at the end of the bearing part 12 on the turbine part 4 side.
- FIG. 4 is a perspective view illustrating the configuration of the seal ring holding portion of FIG. As shown in FIGS. 2 and 4, the seal ring holding part 20 is a ring plate-like member.
- a flow hole 21 through which air passes from the inner diffuser 13 side to the turbine part 4 side is formed in the seal ring holding part 20.
- the flow hole 21 forms a part of the cooling flow path 17.
- description will be made by applying to an example in which eight flow holes 21 are formed in the seal ring holding portion 20, but the number of flow holes 21 formed is limited to eight. However, it may be more or less than eight and is not particularly limited.
- the cooling channel 17 is formed from the opening 18 of the casing 11 to the inner peripheral surface of the casing 11, the space between the strut 14 and the strut cover 15, the bearing 12 and the inner diffuser 13. And a through hole 21. Further, the cooling flow path 17 is open between the turbine section 4 and the gas path section 7, in other words, on the downstream side of the final stage moving blade of the turbine section 4 and on the radially inner wall surface.
- the hollow struts 16 are arranged on the inner peripheral surface of the casing 11 downstream of the struts 14 (on the right side in FIG. 2) so as to extend radially inward.
- the hollow strut 16 is a member formed in a cylindrical shape, and its radially outer end is connected to the casing 11 and its radially inner end is connected to the inner diffuser 13. Further, the space inside the hollow strut 16 communicates with the outside space of the casing 11 and the inside space of the inner diffuser 13 to form a cooling passage 25.
- FIG. 5 is a diagram for explaining the configuration of the lid of FIG. As shown in FIGS. 2 and 5, a lid 22 is disposed in the opening of the hollow strut 16 on the casing 11 side.
- the lid 22 restricts the flow rate of air flowing into the inner space of the inner diffuser 13 via the hollow strut 16.
- the lid portion 22 is formed with a through hole 24 through which a plurality of pipes 23 connected to the bearing portion 12 through hollow struts 16 are inserted.
- the through hole 24 is formed larger than the pipe 23, and a gap through which air passes is formed between the through hole 24 and the pipe 23.
- the air flow flowing in the cooling flow path 17 flows between the strut 14 and the strut cover 15, takes heat from the strut 14, and flows into the inner diffuser 13.
- the air that has flowed into the inner diffuser 13 passes through the circulation hole 21.
- the air that has passed through the flow hole 21 flows into the gas path unit 7 from an opening formed between the turbine unit 4 and the gas path unit 7.
- air also flows into the hollow strut 16 from the through hole 24 of the lid portion 22 disposed in the opening of the hollow strut 16.
- the air is air having a temperature lower than that of the exhaust gas flowing through the gas path unit 7.
- the air that has flowed into the hollow strut 16 flows into the cooling passage 25 and cools around the bearing, and then merges with the air that has passed between the strut 14 and the strut cover 15 described above.
- the amount of air flowing in through the clearance of the through hole 24 of the lid portion 22 is smaller than the amount of air flowing in from the opening 18. In other words, the area of the gap between the through holes 24 is smaller than the area of the opening 18.
- the air outside the casing 11 flows into the cooling flow path 17 from the opening 18 and is guided around the bearing.
- the air flowing through the cooling flow path 17 cools the strut 14 as it flows along the strut 14. Therefore, the strut 14 does not decrease the efficiency of the gas turbine 1 as in the case of extracting compressed air from the compressor unit 2. Can be cooled.
- the pressure difference between both opening ends of the cooling flow path 17 and the cooling flow path 25 is increased. Therefore, more air can be supplied around the struts 14 and the bearings via the cooling flow path 17 than when the cooling flow path 17 and the cooling flow path 25 are open to other regions. Can be cooled more effectively.
- the cooling channel 17 By forming the cooling channel 17 around the strut 14, the contact area between the strut 14 and the air flowing through the cooling channel 17 is widened. Therefore, the cooling effect of the strut 14 by the air flowing through the cooling channel 17 can be enhanced. Further, since the cooling flow path 17 is formed between the strut 14 and the gas path portion 7, the heat of the exhaust gas flowing through the gas path portion 7 can be made difficult to be transmitted to the strut 14.
- the air around the bearing can be cooled by flowing air having a temperature lower than that of the exhaust gas flowing through the gas path portion 7 into the cooling flow path 25 via the hollow struts 16. Further, by providing the lid portion 22, it is possible to prevent a decrease in the flow rate of the air that cools the struts 14 by adjusting the flow rate of the air flowing into the cooling flow path 25 via the hollow struts 16.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
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Abstract
Description
さらに、ガスタービンの運転中における振動状態を計測するため、軸受の周辺には振動計などの計装品が配置されている。
そのため、運転中のガスタービンにおいて、ストラットや計装品を冷却する様々な技術が提案されている(例えば、特許文献1および2参照。)。
しかしながら、空気をコンプレッサ部から抽気して冷却に用いるため、空気を抽気した分だけガスタービンの効率が低下するという問題があった。
一般に、軸受まわりに配置された計装品は高熱に対して耐性が低いため、計装品は、上述の様に例えば約400℃以上に加熱された空気によって損傷する危険があった。
本発明の第1の態様は、内側にガスパス部が形成されるケーシングと、タービン部の動翼を回転可能に支持する軸受部と、前記ケーシングから内側に延び、前記軸受部を支持するストラットと、前記ケーシングに形成された開口部と、該開口部から前記ストラットに沿って前記軸受部に向かって延び、空気を前記ガスパス部に導くとともに、前記タービン部における最終段動翼の下流側において、前記ガスパス部に開口している冷却流路と、が設けられているガスタービンの排気部の構造を提供する。
一方、ストラットとガスパス部との間に冷却流路が形成されるため、ガスパス部を流れる排気ガスの熱がストラットに伝わりにくくなる。
2 コンプレッサ部
3 燃焼部
4 タービン部
5 排気部
7 ガスパス部
11 ケーシング
12 軸受部
13 内側ディフューザ
14 ストラット
15 ストラットカバー
16 ホローストラット
17 冷却流路
18 開口部
20 シールリング保持部
21 流通孔
22 蓋部
23 配管
24 貫通孔
25 冷却流路
図1は、本実施形態に係るガスタービンの構成を説明する模式図である。
本実施形態のガスタービン1には、図1に示すように、空気を圧縮するコンプレッサ部2と、圧縮された空気と燃料とを混合して燃焼させ、燃焼ガスを生成する燃焼器3と、燃焼ガスから回転駆動力を取り出すタービン部4と、タービン部4から排気された排気ガスが流入する排気部5と、が設けられている。
コンプレッサ部2はタービン部4とともに回転軸6に設けられ、タービン部4により回転駆動されるものである。
排気部5は、タービン部4から排出された排気ガスが流入するガスパス部7が内部に形成されたものである。
さらに、排気部5には、ケーシング11の外からストラット14を冷却する空気を導く冷却流路17が設けられている。
ケーシング11の内周面におけるタービン部4側には、ストラット14が回転軸6に向かって延びるように配置され、ストラット14の径方向外側の取り付け部には、冷却流路17が円環状に配置されている。ケーシング11には、冷却流路17とケーシング11の外側とを連通させる開口部18が配置されている。
シールリング保持部20は、図2および図4に示すように、リング板状の部材である。
なお、本実施形態では、8個の流通孔21がシールリング保持部20に形成されている例に適用して説明するが、流通孔21が形成される個数は、8個に限定されるものではなく、8個よりも多くても少なくてもよく、特に限定するものではない。
さらに、冷却流路17は、タービン部4とガスパス部7との間、言い換えると、タービン部4の最終段動翼の下流側であって、径方向内側の壁面に開口している。
ホローストラット16におけるケーシング11側の開口部には、図2および図5に示すように、蓋部22が配置されている。
蓋部22には、ホローストラット16を介して軸受部12と連結された複数の配管23が挿通される貫通孔24が形成されている。貫通孔24は、配管23よりも大きく形成され、配管23との間に空気が通過する隙間が形成されている。
ガスタービン1の運転が開始されると、図2に示すように、タービン部4から排気ガスが排気部5のガスパス部7に流入する。タービン部4の最終段動翼の下流側であって、径方向内側の領域では、圧力が大気圧よりも低い圧力となる。
言い換えると、冷却流路17の両端部における圧力に差が生じ、冷却流路17には、ケーシング11の外側からガスパス部7に向かう空気流れが発生する。
蓋部22の貫通孔24の隙間から流入する空気の量は、開口部18から流入する空気の量よりも少ない。言い換えると、貫通孔24の隙間の面積は、開口部18の面積よりも狭い。
さらに、ストラット14とガスパス部7との間に冷却流路17が形成されるため、ガスパス部7を流れる排気ガスの熱をストラット14に伝わりにくくすることができる。
さらに蓋部22を設けることにより、ホローストラット16を介して冷却流路25に流入する空気の流量を調整することにより、ストラット14を冷却する空気の流量低下を防止することができる。
Claims (4)
- 内側にガスパス部が形成されるケーシングと、
タービン部を回転可能に支持する軸受部と、
前記ケーシングから内側に延び、前記軸受部を支持するストラットと、
前記ケーシングに形成された開口部と、
該開口部から前記ストラットに沿って前記軸受部に向かって延び、空気を前記ガスパス部に導くとともに、前記タービン部における最終段動翼の下流側において、前記ガスパス部に開口している冷却流路と、
が設けられているガスタービンの排気部の構造。 - 前記ストラットに沿って延び、前記ストラットとの間に空間を形成するストラットカバーが設けられ、
前記ストラットと前記ストラットカバーとの間の空間が、前記冷却流路の一部を形成する請求項1記載のガスタービンの排気部の構造。 - 前記タービン部の回転軸線に沿って延び、前記軸受部との間に空間を形成する内側ディフューザと、
前記ケーシングから延び、前記内側ディフューザを支持するとともに、前記ケーシングの外部と前記内側ディフューザの内部とを連通させるホローストラットと、
前記ホローストラットにおける前記ケーシングに対する開口面積を調節する蓋部と、
が設けられ、
前記軸受部と前記内側ディフューザとの間の空間が、前記冷却流路を形成する請求項1または2に記載のガスタービンの排気部の構造。 - 空気を圧縮するコンプレッサ部と、
前記コンプレッサ部によって圧縮された空気と燃料とを混合して燃焼させ、燃焼ガスを生成する燃焼器と、
前記燃焼ガスから回転駆動力を取り出すタービン部と、
該タービン部から排気された排気ガスが流入する請求項1から請求項3のいずれかに記載の排気部と、
が設けられているガスタービン。
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
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KR1020107000828A KR101192620B1 (ko) | 2008-01-10 | 2008-12-09 | 가스 터빈의 배기부의 구조 및 가스 터빈 |
US12/666,211 US8740550B2 (en) | 2008-01-10 | 2008-12-09 | Structure of exhaust section of gas turbine and gas turbine |
EP08870113.1A EP2187019B2 (en) | 2008-01-10 | 2008-12-09 | Gas turbine with exhaust section structure |
CN200880024719.1A CN101743391B (zh) | 2008-01-10 | 2008-12-09 | 燃气轮机的排气部的结构及燃气轮机 |
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JP2008003368A JP5118496B2 (ja) | 2008-01-10 | 2008-01-10 | ガスタービンの排気部の構造およびガスタービン |
JP2008-003368 | 2008-01-10 |
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WO2009087847A1 true WO2009087847A1 (ja) | 2009-07-16 |
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PCT/JP2008/072327 WO2009087847A1 (ja) | 2008-01-10 | 2008-12-09 | ガスタービンの排気部の構造およびガスタービン |
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US (1) | US8740550B2 (ja) |
EP (1) | EP2187019B2 (ja) |
JP (1) | JP5118496B2 (ja) |
KR (1) | KR101192620B1 (ja) |
CN (1) | CN101743391B (ja) |
WO (1) | WO2009087847A1 (ja) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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EP2336524A3 (en) * | 2009-12-15 | 2011-10-05 | Kawasaki Jukogyo Kabushiki Kaisha | Gas turbine engine with cooling arrangement |
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Also Published As
Publication number | Publication date |
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JP5118496B2 (ja) | 2013-01-16 |
JP2009167800A (ja) | 2009-07-30 |
EP2187019B2 (en) | 2019-03-06 |
CN101743391A (zh) | 2010-06-16 |
KR101192620B1 (ko) | 2012-10-18 |
EP2187019B1 (en) | 2016-03-23 |
EP2187019A1 (en) | 2010-05-19 |
US20100322759A1 (en) | 2010-12-23 |
KR20100021522A (ko) | 2010-02-24 |
US8740550B2 (en) | 2014-06-03 |
EP2187019A4 (en) | 2015-02-25 |
CN101743391B (zh) | 2015-01-28 |
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