Combustor assemblies for use in turbine engines and methods of assembling same
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
F02G-003/00
F01D-009/02
F02C-007/22
F23R-003/06
F23R-003/54
F23R-003/00
출원번호
US-0983393
(2011-01-03)
등록번호
US-8813501
(2014-08-26)
발명자
/ 주소
Cihlar, David William
Chila, Ronald James
Berkman, Mert Enis
출원인 / 주소
General Electric Company
대리인 / 주소
Armstrong Teasdale LLP
인용정보
피인용 횟수 :
0인용 특허 :
20
초록▼
A method of assembling a combustor assembly for use in a turbine engine is provided. A combustor liner that defines a combustion chamber therein is provided. The liner includes a forward end and an aft end, wherein the aft end includes at least one channel extending therethrough. The channel is alig
A method of assembling a combustor assembly for use in a turbine engine is provided. A combustor liner that defines a combustion chamber therein is provided. The liner includes a forward end and an aft end, wherein the aft end includes at least one channel extending therethrough. The channel is aligned obliquely with respect to a centerline extending through the aft end. A plurality of fuel nozzles are coupled to the forward end such that the fuel nozzles extend through the forward end. An annular sleeve that includes at least one opening extending radially therethrough is coupled to the aft end, wherein the sleeve substantially circumscribes the aft end such that a cavity is defined therebetween and such that a fluid channeled through the at least one opening impinges against a surface of the aft end prior to the fluid being channeled into the combustion chamber.
대표청구항▼
1. A method of assembling a combustor assembly for use in a turbine engine, said method comprising: providing a combustor liner that defines a combustion chamber therein, wherein the combustor liner includes a forward end and an aft end, wherein the aft end includes at least one channel extending th
1. A method of assembling a combustor assembly for use in a turbine engine, said method comprising: providing a combustor liner that defines a combustion chamber therein, wherein the combustor liner includes a forward end and an aft end, wherein the aft end includes at least one channel extending therethrough, wherein the at least one channel is aligned obliquely with respect to a centerline extending through the aft end;coupling a plurality of fuel nozzles to the forward end such that the plurality of fuel nozzles extend through the forward end; andcoupling an annular sleeve to the aft end, wherein the sleeve includes at least one opening extending radially therethrough, the sleeve substantially circumscribes the aft end such that a cavity is defined therebetween and such that a fluid channeled through the at least one opening impinges against a surface of the aft end that is substantially parallel to the sleeve, wherein the fluid is dispersed in both a first direction and an opposite second direction within the cavity prior to the fluid being channeled through the at least one channel into the combustion chamber. 2. A method in accordance with claim 1, wherein coupling an annular sleeve to the aft end further comprises aligning the at least one opening substantially obliquely with respect to the at least one channel. 3. A method in accordance with claim 1, further comprising coupling a flowsleeve radially outwardly from the combustor liner. 4. A method in accordance with claim 1, further comprising coupling a transition piece to the combustor liner. 5. A method in accordance with claim 1, wherein providing a combustor liner further comprises providing the combustor liner wherein the aft end includes an exterior surface and an interior surface. 6. A method in accordance with claim 5, wherein providing a combustor liner further comprises extending an upstream portion of the at least one channel from the aft end exterior surface to the centerline and extending a downstream portion of the at least one channel from the centerline to the aft end interior surface. 7. A combustor assembly for use in a turbine engine, said combustor assembly comprising: a combustor liner defining a combustion chamber therein, said combustor liner comprises a forward end and an aft end, wherein said aft end comprises at least one channel extending therethrough, said at least one channel is aligned obliquely with respect to a centerline extending through said aft end;a plurality of fuel nozzles extending through said forward end; andan annular sleeve substantially circumscribing said aft end such that a cavity is defined between said sleeve and said aft end, wherein said sleeve comprises at least one opening extending radially therethrough, said at least one opening is oriented such that a fluid channeled therethrough impinges against a surface of said aft end that is substantially parallel to the sleeve, wherein the fluid is dispersed in both a first direction and an opposite second direction within the cavity prior to the fluid being channeled through the at least one channel into said combustion chamber. 8. A combustor assembly in accordance with claim 7, wherein said at least one opening is oriented substantially obliquely with respect to said at least one channel. 9. A combustor assembly in accordance with claim 7, further comprising a flowsleeve coupled radially outwardly from said combustor liner. 10. A combustor assembly in accordance with claim 7, wherein said at least one channel comprises a plurality of channels extending substantially circumferentially about said aft end, said at least one opening comprises a plurality of openings spaced substantially circumferentially about said sleeve. 11. A combustor assembly in accordance with claim 7, wherein said aft end comprises an exterior surface and an interior surface. 12. A combustor assembly in accordance with claim 11, wherein said at least one channel comprises an upstream portion extending from said aft end exterior surface to said centerline and a downstream portion extending from said centerline to said aft end interior surface. 13. A combustor assembly in accordance with claim 12, wherein said channel upstream portion extends from said centerline at an angle of about 45 degrees with respect to said centerline and said channel downstream portion extends from said centerline at an angle of about 45 degrees with respect to said centerline. 14. A combustor assembly in accordance with claim 7, further comprising a transition piece coupled to said combustor liner. 15. A turbine engine comprising: a compressor; anda combustor coupled in flow communication with said compressor, said combustor comprising at least one combustor assembly comprising: a combustor liner defining a combustion chamber therein, said combustor liner comprises a forward end and an aft end, wherein said aft end comprises at least one channel extending therethrough, said at least one channel is aligned obliquely with respect to a centerline extending through said aft end;a plurality of fuel nozzles extending through said forward end; andan annular sleeve substantially circumscribing said aft end such that a cavity is defined between said sleeve and said aft end, wherein said sleeve comprises at least one opening extending radially therethrough, said at least one opening is oriented such that a fluid channeled therethrough impinges against a surface of said aft end that is substantially parallel to the sleeve, wherein the fluid is dispersed in both a first direction and an opposite second direction within the cavity prior to the fluid being channeled through the at least one channel into said combustion chamber. 16. A turbine engine in accordance with claim 15, wherein said at least one combustor assembly further comprises a flowsleeve coupled radially outwardly from said combustor liner. 17. A turbine engine in accordance with claim 15, wherein said at least one channel comprises a plurality of channels extending substantially circumferentially about said aft end and said at least one opening comprises a plurality of openings spaced substantially circumferentially about said sleeve. 18. A turbine engine in accordance with claim 15, wherein said aft end comprises an exterior surface and an interior surface. 19. A turbine engine in accordance with claim 18, wherein said at least one channel comprises an upstream portion extending from said aft end exterior surface to said centerline and a downstream portion extending from said centerline to said aft end interior surface. 20. A turbine engine in accordance with claim 19, wherein said channel upstream portion extends from said centerline at an angle of about 45 degrees with respect to said centerline and said channel downstream portion extends from said centerline at an angle of about 45 degrees with respect to said centerline.
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이 특허에 인용된 특허 (20)
Martling,Vincent C.; Xiao,Zhenhua, Combustion liner having improved cooling and sealing.
Ambrogi Christine J. M. (Bondoufle FRX) Ansart Denis R. H. (Bois Le Roi FRX) Meunier Serge M. (Le Chatelet En Brie FRX) Sandelis Denis J. M. (Nangis FRX), Double wall construction for a gas turbine combustion chamber.
Bunker,Ronald Scott; Bailey,Jeremy Clyde; Widener,Stanley Kevin; Johnson,Thomas Edward; Intile,John C, Method and apparatus for cooling combustor liner and transition piece of a gas turbine.
Commaret Patrice (Le Mee s/Seine FRX) Desaulty Michel A. A. (Vert St Denis FRX) Hernandez Didier H. (Ormoy FRX) Laugeois Jean-Claude (Palaiseau FRX) Mandet Grard M. F. (Fericy FRX) Martinez Rodolphe , Turbojet engine combustion chamber with a double wall converging zone.
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