US3652181A - Cooling sleeve for gas turbine combustor transition member - Google Patents
Cooling sleeve for gas turbine combustor transition member Download PDFInfo
- Publication number
- US3652181A US3652181A US91659A US3652181DA US3652181A US 3652181 A US3652181 A US 3652181A US 91659 A US91659 A US 91659A US 3652181D A US3652181D A US 3652181DA US 3652181 A US3652181 A US 3652181A
- Authority
- US
- United States
- Prior art keywords
- transition member
- sleeve
- turbine
- walls
- wall
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Classifications
-
- 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
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
Definitions
- This invention relates generally to gas turbine power plants and more particularly to an improved construction for cooling of the transition member supplying hot combustion gases from the combustion chamber to the turbine, as well as an improved construction for improving the temperature distribution of the hot gas to the turbine blades.
- Industrial gas turbines generally supply compressor air to a jacket surrounding a combustion liner within which combustion takes place for supplying hot gases to the turbine located some distance away from the combustion chamber outlet.
- a transition member which is oftentimes partially cooled by the compressor air on its way to the combustion chamber. Some parts of the transition member are relatively difficult to cool in this manner because they are in locations which are relatively inaccessible to the cooling air flow.
- One such region is the radially outer portion of the transition member closest to the turbine.
- one object of the present invention is to provide an improved construction for cooling the inaccessible wall portions of the transition member in a gas turbine.
- Another object of the invention is to provide an improved construction for introducing compressor air into the hot gas path to profile" the radial temperature gradient in a gas turbine.
- FIG. 1 is a partial horizontal cross section of a gas turbine power plant illustrating the location of the transition member
- FIG. 2 is an enlarged view of the end of the transition member illustrating the cooling sleeve of the present invention
- FIG. 3 is a cross section of the transition member and cooling sleeve taken along the lines IIIIII of FIG. 2.
- the invention is practiced by providing a cooling sleeve which surrounds and encloses the end of the transition member adjacent the turbine inlet, Inlet holes into the sleeve provide cooling by impingement against the transition member in addition to some connection cooling. Holes through the transition member into the hot gas path are located diametrically opposite the inlet holes so that cooling air flows around the transition member to cool it before entering the hot gas path to cool the blade root region.
- FIG. 1 of the drawing the illustrated portion of a gas turbine power plant shows a section of the compressor l, the combustion chamber 2, and the turbine 3.
- the compressor 1 has an outlet 4 which discharges into a closed chamber 5 containing a curved transition member 6.
- the transition member 6 connects the open circular end of a combustion liner 7 with an arc of radially extending stationary nozzle partitions 8 and is suitably curved to provide the flow transition from a circular inlet to an arcuate outlet.
- a number of such transition members 6 and combustion liners 7 are circumferentially spaced around the gas turbine, only one being shown here for simplicity.
- the turbine portion includes additional rotating turbine buckets 9 and stationary nozzle partitions 8 in the first turbine stage.
- the foregoing construction is well known in the art.
- the present invention comprises an improvement by the addition of a cooling sleeve 11 surrounding the end of the transition member 6.
- FIG. 2 of the drawing and the cross section of F IG. 3 shows that the end of transition member 6 adjacent the inlet to turbine nozzle partitions 8 includes a sheet metal sleeve 11 confirming in shape to the transition member curvature but spaced therefrom by means of a crimped edge 12 which is spot welded or otherwise tightly attached to transition member 6.
- the sleeve 11 is so proportioned as indicated in the drawings to leave a passage 13 surrounding the transition member 6 for the flow of cooling air between the transition member and the sleeve walls.
- the transition member has a top wall 14 and a bottom wall 15.
- the sleeve has a top wall 16 and bottom wall 17.
- Reference in the description and claims to top walls means radially outer walls with respect to the gas turbine axis.
- bottom walls means radially inner walls with respect to the axis.
- the top wall 16 of the sleeve is perforated with a large number of small inlet holes 18 distributed for impingement cooling of transition member top wall 14, while the bottom wall 17 of the sleeve 1 l is imperforate.
- the bottom wall 15 of the transition member is perforated with a smaller number of fairly large air outlet holes 19 for temperature profiling, while the top wall 14 of the transition sleeve is imperforate. Air therefore must enter at inlet holes 18 and flow in both directions around the sides of the transition member to exit through holes 19.
- Inlet holes 18 are distributed with respect to the surface of the upper transition wall 14 and are selected and sized to provide air impingement cooling by relatively small jets of air striking against the surface of wall 14. For example, in the illustrated construction, around holes of one-eighth inch diameter have been found suitable for gas turbines in the 15 to 75 mw. output range.
- the outlet holes 19 are arranged and proportioned for a different purpose, i.e., for injection of air to provide radial temperature profiling of the hot gas flowing through transition member 6. Therefore, they are arranged along one or two rows and are larger in diameter to minimize radial velocity and keep air near the root of nozzle portion 8. In the construction illustrated, two rows of around 10 holes each of three-eighths inch diameter have been found suitable.
- air from the compressor outlet 4 partially cools transition member 6 en route to the combustion chamber.
- a portion of the compressor air flows toward the relatively inaccessible radially outer or top" portion of the transition member and into the air inlet holes 18 because of the existing pressure difference.
- the tiny jets of air from the numerous small inlet holes 18 serve to effectively cool the arcuate surface of the top transition wall 14 by impingement thereon.
- the air then flows around the sides of the transition wall serving to further cool the same by convection.
- the partially heated air now flows through the outlet holes 19 into the radially inner portion of the hot gases flowing through the transition member 6.
- a gas turbine having a transition member arranged to conduct hot combustion gases from a combustion chamber to a turbine inlet passage, said transition member being disposed in a chamber connected to a source of pressurized cooling fluid, the improvement comprising:
- transition member portion having a substantially imperforate top wall topand an opposed bottom wall
- a sleeve member surrounding and spaced from said transition member portion and having top and bottom opposed walls spaced from said respective top and bottom transition member opposed walls to form an unobstructed flow space there between,
- top wall of the sleeve member being perforated and communicating with a supply of compressed air and arranged to admit jets of cooling fiuid for impingement 1 cooling of the transition member top wall
- said bottom wall of the transitionmember portion having openings arranged to admit cooling fluid from the sleeve into the transition member interior for profiling the hot combustion gases entering the turbine.
- top and bottom walls are arcuate surfaces, and wherein said top walls have greater surface areas than said bottom walls and wherein the perforations in the top wall are smaller in sizeand greater in number than the openings in said bottom wall.
- said sleeve member comprises a sheet metal jacket surrounding said transition member portion and substantially uniformly spaced therefrom and sealingly attached thereto by crimped edges on said jacket.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US9165970A | 1970-11-23 | 1970-11-23 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3652181A true US3652181A (en) | 1972-03-28 |
Family
ID=22228970
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US91659A Expired - Lifetime US3652181A (en) | 1970-11-23 | 1970-11-23 | Cooling sleeve for gas turbine combustor transition member |
Country Status (8)
Country | Link |
---|---|
US (1) | US3652181A (fr) |
JP (1) | JPS5411443B1 (fr) |
CH (1) | CH538602A (fr) |
DE (1) | DE2155107A1 (fr) |
FR (1) | FR2115343B1 (fr) |
GB (1) | GB1311630A (fr) |
IT (1) | IT941241B (fr) |
NL (1) | NL7112400A (fr) |
Cited By (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3844116A (en) * | 1972-09-06 | 1974-10-29 | Avco Corp | Duct wall and reverse flow combustor incorporating same |
US4195474A (en) * | 1977-10-17 | 1980-04-01 | General Electric Company | Liquid-cooled transition member to turbine inlet |
US4211069A (en) * | 1977-06-24 | 1980-07-08 | Bbc Brown Boveri & Company Limited | Combustion chamber for a gas turbine |
EP0203431A1 (fr) * | 1985-05-14 | 1986-12-03 | General Electric Company | Canal de transition refroidi par impact |
EP0239020A2 (fr) * | 1986-03-20 | 1987-09-30 | Hitachi, Ltd. | Chambre de combustion pour une turbine à gaz |
US4719748A (en) * | 1985-05-14 | 1988-01-19 | General Electric Company | Impingement cooled transition duct |
US4903477A (en) * | 1987-04-01 | 1990-02-27 | Westinghouse Electric Corp. | Gas turbine combustor transition duct forced convection cooling |
US5394687A (en) * | 1993-12-03 | 1995-03-07 | The United States Of America As Represented By The Department Of Energy | Gas turbine vane cooling system |
WO1998057044A1 (fr) * | 1997-06-13 | 1998-12-17 | Siemens Westinghouse Power Corporation | Plaque de refroidissement pour turbine a gaz |
WO2000077348A1 (fr) * | 1999-06-10 | 2000-12-21 | Pratt & Whitney Canada Corp. | Appareil servant a reduire le refroidissement de la gaine de sortie du dispositif combustor |
EP1160512A2 (fr) * | 2000-06-02 | 2001-12-05 | General Electric Company | Structure de support résistant à la fracture pour garniture du type "hula" dans une turbine à gaz et procédé correspondant |
US20020112483A1 (en) * | 2001-02-16 | 2002-08-22 | Mitsubishi Heavy Industries Ltd. | Transition piece outlet structure enabling to reduce the temperature, and a transition piece, a combustor and a gas turbine providing the above output structure |
EP1270874A1 (fr) * | 2001-06-18 | 2003-01-02 | Siemens Aktiengesellschaft | Turbine à gaz avec un compresseur d'air |
US20050241314A1 (en) * | 2003-07-14 | 2005-11-03 | Hiroya Takaya | Cooling structure of gas turbine tail pipe |
US20060101801A1 (en) * | 2004-11-18 | 2006-05-18 | Siemens Westinghouse Power Corporation | Combustor flow sleeve with optimized cooling and airflow distribution |
US20070175220A1 (en) * | 2006-02-02 | 2007-08-02 | Siemens Power Generation, Inc. | Gas turbine engine curved diffuser with partial impingement cooling apparatus for transitions |
US20070180827A1 (en) * | 2006-02-09 | 2007-08-09 | Siemens Power Generation, Inc. | Gas turbine engine transitions comprising closed cooled transition cooling channels |
US20080276619A1 (en) * | 2007-05-09 | 2008-11-13 | Siemens Power Generation, Inc. | Impingement jets coupled to cooling channels for transition cooling |
EP2028344A1 (fr) * | 2007-08-21 | 2009-02-25 | Siemens Aktiengesellschaft | Conduit de transition |
WO2009103671A1 (fr) * | 2008-02-20 | 2009-08-27 | Alstom Technology Ltd | Turbine à gaz à architecture de refroidissement améliorée |
US20100005804A1 (en) * | 2008-07-11 | 2010-01-14 | General Electric Company | Combustor structure |
US20100037622A1 (en) * | 2008-08-18 | 2010-02-18 | General Electric Company | Contoured Impingement Sleeve Holes |
US20100071382A1 (en) * | 2008-09-25 | 2010-03-25 | Siemens Energy, Inc. | Gas Turbine Transition Duct |
US20100242487A1 (en) * | 2009-03-30 | 2010-09-30 | General Electric Company | Thermally decoupled can-annular transition piece |
US20100242485A1 (en) * | 2009-03-30 | 2010-09-30 | General Electric Company | Combustor liner |
US20120079828A1 (en) * | 2010-10-05 | 2012-04-05 | Hitachi, Ltd. | Gas Turbine Combustor |
US20120324898A1 (en) * | 2011-06-21 | 2012-12-27 | Mcmahan Kevin Weston | Combustor assembly for use in a turbine engine and methods of assembling same |
CN103375262A (zh) * | 2012-04-30 | 2013-10-30 | 通用电气公司 | 涡轮机系统中具有延迟喷射的过渡管道 |
US8647053B2 (en) | 2010-08-09 | 2014-02-11 | Siemens Energy, Inc. | Cooling arrangement for a turbine component |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SE426982B (sv) * | 1980-03-19 | 1983-02-21 | Fagersta Ab | Sett och anordning for atervinning av verme fran rokgaser |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2479573A (en) * | 1943-10-20 | 1949-08-23 | Gen Electric | Gas turbine power plant |
US2806355A (en) * | 1950-05-09 | 1957-09-17 | Maschf Augsburg Nuernberg Ag | Axial flow turbine with means for admixing low temperature gas into the high temperature driving gas stream |
US2958194A (en) * | 1951-09-24 | 1960-11-01 | Power Jets Res & Dev Ltd | Cooled flame tube |
US3135496A (en) * | 1962-03-02 | 1964-06-02 | Gen Electric | Axial flow turbine with radial temperature gradient |
US3433015A (en) * | 1965-06-23 | 1969-03-18 | Nasa | Gas turbine combustion apparatus |
US3490747A (en) * | 1967-11-29 | 1970-01-20 | Westinghouse Electric Corp | Temperature profiling means for turbine inlet |
US3570241A (en) * | 1968-08-02 | 1971-03-16 | Rolls Royce | Flame tube for combustion chamber of a gas turbine engine |
-
1970
- 1970-11-23 US US91659A patent/US3652181A/en not_active Expired - Lifetime
-
1971
- 1971-08-20 GB GB3910871A patent/GB1311630A/en not_active Expired
- 1971-09-09 NL NL7112400A patent/NL7112400A/xx not_active Application Discontinuation
- 1971-11-05 DE DE19712155107 patent/DE2155107A1/de active Pending
- 1971-11-18 CH CH1681571A patent/CH538602A/de not_active IP Right Cessation
- 1971-11-22 IT IT31473/71A patent/IT941241B/it active
- 1971-11-23 FR FR7141839A patent/FR2115343B1/fr not_active Expired
- 1971-11-24 JP JP9372671A patent/JPS5411443B1/ja active Pending
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2479573A (en) * | 1943-10-20 | 1949-08-23 | Gen Electric | Gas turbine power plant |
US2806355A (en) * | 1950-05-09 | 1957-09-17 | Maschf Augsburg Nuernberg Ag | Axial flow turbine with means for admixing low temperature gas into the high temperature driving gas stream |
US2958194A (en) * | 1951-09-24 | 1960-11-01 | Power Jets Res & Dev Ltd | Cooled flame tube |
US3135496A (en) * | 1962-03-02 | 1964-06-02 | Gen Electric | Axial flow turbine with radial temperature gradient |
US3433015A (en) * | 1965-06-23 | 1969-03-18 | Nasa | Gas turbine combustion apparatus |
US3490747A (en) * | 1967-11-29 | 1970-01-20 | Westinghouse Electric Corp | Temperature profiling means for turbine inlet |
US3570241A (en) * | 1968-08-02 | 1971-03-16 | Rolls Royce | Flame tube for combustion chamber of a gas turbine engine |
Cited By (55)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3844116A (en) * | 1972-09-06 | 1974-10-29 | Avco Corp | Duct wall and reverse flow combustor incorporating same |
US4211069A (en) * | 1977-06-24 | 1980-07-08 | Bbc Brown Boveri & Company Limited | Combustion chamber for a gas turbine |
US4195474A (en) * | 1977-10-17 | 1980-04-01 | General Electric Company | Liquid-cooled transition member to turbine inlet |
EP0203431A1 (fr) * | 1985-05-14 | 1986-12-03 | General Electric Company | Canal de transition refroidi par impact |
AU593551B2 (en) * | 1985-05-14 | 1990-02-15 | General Electric Company | An improved apparatus |
US4719748A (en) * | 1985-05-14 | 1988-01-19 | General Electric Company | Impingement cooled transition duct |
EP0239020A3 (en) * | 1986-03-20 | 1989-01-18 | Hitachi, Ltd. | Gas turbine combustion apparatus |
EP0239020A2 (fr) * | 1986-03-20 | 1987-09-30 | Hitachi, Ltd. | Chambre de combustion pour une turbine à gaz |
US4903477A (en) * | 1987-04-01 | 1990-02-27 | Westinghouse Electric Corp. | Gas turbine combustor transition duct forced convection cooling |
US5394687A (en) * | 1993-12-03 | 1995-03-07 | The United States Of America As Represented By The Department Of Energy | Gas turbine vane cooling system |
WO1998057044A1 (fr) * | 1997-06-13 | 1998-12-17 | Siemens Westinghouse Power Corporation | Plaque de refroidissement pour turbine a gaz |
US6018950A (en) * | 1997-06-13 | 2000-02-01 | Siemens Westinghouse Power Corporation | Combustion turbine modular cooling panel |
WO2000077348A1 (fr) * | 1999-06-10 | 2000-12-21 | Pratt & Whitney Canada Corp. | Appareil servant a reduire le refroidissement de la gaine de sortie du dispositif combustor |
US6269628B1 (en) | 1999-06-10 | 2001-08-07 | Pratt & Whitney Canada Corp. | Apparatus for reducing combustor exit duct cooling |
EP1160512A2 (fr) * | 2000-06-02 | 2001-12-05 | General Electric Company | Structure de support résistant à la fracture pour garniture du type "hula" dans une turbine à gaz et procédé correspondant |
EP1160512A3 (fr) * | 2000-06-02 | 2002-06-19 | General Electric Company | Structure de support résistant à la fracture pour garniture du type "hula" dans une turbine à gaz et procédé correspondant |
US20020112483A1 (en) * | 2001-02-16 | 2002-08-22 | Mitsubishi Heavy Industries Ltd. | Transition piece outlet structure enabling to reduce the temperature, and a transition piece, a combustor and a gas turbine providing the above output structure |
US6769257B2 (en) * | 2001-02-16 | 2004-08-03 | Mitsubishi Heavy Industries, Ltd. | Transition piece outlet structure enabling to reduce the temperature, and a transition piece, a combustor and a gas turbine providing the above output structure |
EP1270874A1 (fr) * | 2001-06-18 | 2003-01-02 | Siemens Aktiengesellschaft | Turbine à gaz avec un compresseur d'air |
US6672070B2 (en) | 2001-06-18 | 2004-01-06 | Siemens Aktiengesellschaft | Gas turbine with a compressor for air |
CN1328492C (zh) * | 2001-06-18 | 2007-07-25 | 西门子公司 | 带有空气压缩机的燃气轮机 |
US7481037B2 (en) * | 2003-07-14 | 2009-01-27 | Mitsubishi Heavy Industries, Ltd. | Cooling structure of gas turbine tail pipe |
US20050241314A1 (en) * | 2003-07-14 | 2005-11-03 | Hiroya Takaya | Cooling structure of gas turbine tail pipe |
US20060101801A1 (en) * | 2004-11-18 | 2006-05-18 | Siemens Westinghouse Power Corporation | Combustor flow sleeve with optimized cooling and airflow distribution |
US7574865B2 (en) | 2004-11-18 | 2009-08-18 | Siemens Energy, Inc. | Combustor flow sleeve with optimized cooling and airflow distribution |
US20070175220A1 (en) * | 2006-02-02 | 2007-08-02 | Siemens Power Generation, Inc. | Gas turbine engine curved diffuser with partial impingement cooling apparatus for transitions |
US7870739B2 (en) | 2006-02-02 | 2011-01-18 | Siemens Energy, Inc. | Gas turbine engine curved diffuser with partial impingement cooling apparatus for transitions |
US20070180827A1 (en) * | 2006-02-09 | 2007-08-09 | Siemens Power Generation, Inc. | Gas turbine engine transitions comprising closed cooled transition cooling channels |
US7827801B2 (en) | 2006-02-09 | 2010-11-09 | Siemens Energy, Inc. | Gas turbine engine transitions comprising closed cooled transition cooling channels |
US20080276619A1 (en) * | 2007-05-09 | 2008-11-13 | Siemens Power Generation, Inc. | Impingement jets coupled to cooling channels for transition cooling |
US7886517B2 (en) | 2007-05-09 | 2011-02-15 | Siemens Energy, Inc. | Impingement jets coupled to cooling channels for transition cooling |
EP2028344A1 (fr) * | 2007-08-21 | 2009-02-25 | Siemens Aktiengesellschaft | Conduit de transition |
US8413449B2 (en) | 2008-02-20 | 2013-04-09 | Alstom Technology Ltd | Gas turbine having an improved cooling architecture |
US20110110761A1 (en) * | 2008-02-20 | 2011-05-12 | Alstom Technology Ltd. | Gas turbine having an improved cooling architecture |
WO2009103671A1 (fr) * | 2008-02-20 | 2009-08-27 | Alstom Technology Ltd | Turbine à gaz à architecture de refroidissement améliorée |
US20100005804A1 (en) * | 2008-07-11 | 2010-01-14 | General Electric Company | Combustor structure |
US20100037622A1 (en) * | 2008-08-18 | 2010-02-18 | General Electric Company | Contoured Impingement Sleeve Holes |
US8033119B2 (en) | 2008-09-25 | 2011-10-11 | Siemens Energy, Inc. | Gas turbine transition duct |
US20100071382A1 (en) * | 2008-09-25 | 2010-03-25 | Siemens Energy, Inc. | Gas Turbine Transition Duct |
US20100242485A1 (en) * | 2009-03-30 | 2010-09-30 | General Electric Company | Combustor liner |
US20100242487A1 (en) * | 2009-03-30 | 2010-09-30 | General Electric Company | Thermally decoupled can-annular transition piece |
US8695322B2 (en) * | 2009-03-30 | 2014-04-15 | General Electric Company | Thermally decoupled can-annular transition piece |
US8448416B2 (en) | 2009-03-30 | 2013-05-28 | General Electric Company | Combustor liner |
US8647053B2 (en) | 2010-08-09 | 2014-02-11 | Siemens Energy, Inc. | Cooling arrangement for a turbine component |
CN102563699A (zh) * | 2010-10-05 | 2012-07-11 | 株式会社日立制作所 | 燃气轮机燃烧器 |
EP2439452A3 (fr) * | 2010-10-05 | 2012-05-30 | Hitachi, Ltd. | Chambre de combustion de turbine à gaz |
US20120079828A1 (en) * | 2010-10-05 | 2012-04-05 | Hitachi, Ltd. | Gas Turbine Combustor |
US8839626B2 (en) * | 2010-10-05 | 2014-09-23 | Hitachi, Ltd. | Gas turbine combustor including a transition piece flow sleeve wrapped on an outside surface of a transition piece |
US8955332B2 (en) | 2010-10-05 | 2015-02-17 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine combustor including a transition piece flow sleeve wrapped on an outside surface of a transition piece |
CN102563699B (zh) * | 2010-10-05 | 2015-09-30 | 三菱日立电力系统株式会社 | 燃气轮机燃烧器 |
US20120324898A1 (en) * | 2011-06-21 | 2012-12-27 | Mcmahan Kevin Weston | Combustor assembly for use in a turbine engine and methods of assembling same |
CN103375262A (zh) * | 2012-04-30 | 2013-10-30 | 通用电气公司 | 涡轮机系统中具有延迟喷射的过渡管道 |
US20130283804A1 (en) * | 2012-04-30 | 2013-10-31 | General Electric Company | Transition duct with late injection in turbine system |
US9133722B2 (en) * | 2012-04-30 | 2015-09-15 | General Electric Company | Transition duct with late injection in turbine system |
CN103375262B (zh) * | 2012-04-30 | 2016-12-07 | 通用电气公司 | 涡轮机系统中具有延迟喷射的过渡管道 |
Also Published As
Publication number | Publication date |
---|---|
NL7112400A (fr) | 1972-05-25 |
IT941241B (it) | 1973-03-01 |
FR2115343B1 (fr) | 1974-05-31 |
DE2155107A1 (de) | 1972-05-25 |
FR2115343A1 (fr) | 1972-07-07 |
JPS5411443B1 (fr) | 1979-05-15 |
CH538602A (de) | 1973-06-30 |
GB1311630A (en) | 1973-03-28 |
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