Gas turbine fuel injector having flow guide for receiving air flow
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/28
F02C-007/22
F23R-003/04
F23R-003/12
F23D-011/10
F23R-003/14
F02C-003/09
출원번호
US-0901219
(2013-05-23)
등록번호
US-9404422
(2016-08-02)
발명자
/ 주소
Zupanc, Frank J.
Pardington, Ronald B.
Yankowich, Paul
출원인 / 주소
HONEYWELL INTERNATIONAL INC.
대리인 / 주소
Ingrassia Fisher & Lorenz, PC
인용정보
피인용 횟수 :
0인용 특허 :
13
초록▼
In accordance with an exemplary embodiment, a fuel injector assembly is provided for a gas turbine engine with a compressor section and a combustion section. The fuel injector assembly includes a stem defining a fuel path for fuel and a flow guide coupled to and extending along the stem. The flow gu
In accordance with an exemplary embodiment, a fuel injector assembly is provided for a gas turbine engine with a compressor section and a combustion section. The fuel injector assembly includes a stem defining a fuel path for fuel and a flow guide coupled to and extending along the stem. The flow guide receives an air flow. The assembly further includes a swirler apparatus coupled to the stem and configured to receive the fuel. The swirler apparatus is further coupled to the flow guide and configured to receive the air flow. The swirler apparatus is configured to mix the fuel and the air flow and direct the mixture into a combustor of the combustor assembly.
대표청구항▼
1. A fuel injector assembly for a gas turbine engine with a compressor section and a combustion section, the fuel injector assembly comprising: a stem defining a fuel path for fuel, wherein the stem includes a flange coupling the stem to an outer case of the combustion section, the stem defining a l
1. A fuel injector assembly for a gas turbine engine with a compressor section and a combustion section, the fuel injector assembly comprising: a stem defining a fuel path for fuel, wherein the stem includes a flange coupling the stem to an outer case of the combustion section, the stem defining a length between the flange and the swirler apparatus;a flow guide coupled to and extending along the stem, the flow guide receiving an air flow; anda swirler apparatus coupled to the stem and configured to receive the fuel, the swirler apparatus further coupled to the flow guide and configured to receive the air flow, the swirler apparatus configured to mix the fuel and the air flow and direct the mixture into a combustor of the combustor assembly,wherein the flow guide has a first radial end positioned along the length of the stem and a second radial end at the swirler apparatus, the first radial end of the flow guide being open to define a flow guide inlet for receiving the air flow and the second radial end of the flow guide being closed to direct the air flow within the flow guide into the swirler apparatus,wherein the stem and flow guide extend in a generally radial direction such that the first radial end of the flow guide receives the air flow in the generally radial direction to guide the air flow along the stem in the generally radial direction and such that the second radial end of the flow guide redirects the air flow in a generally axial direction into the swirler apparatus. 2. The fuel injector assembly of claim 1, wherein the first radial end and the flow guide inlet are positioned between about 75% and about 25% of the length of the stem. 3. The fuel injector assembly of claim 1, wherein the compressor section includes a deswirl assembly, and wherein the flow guide is configured to aerodynamically couple the deswirl assembly to the swirler apparatus. 4. The fuel injector assembly of claim 1, wherein swirler apparatus includes a manifold defining a flow path. 5. The fuel injector assembly of claim 4, wherein the manifold defines a fuel outlet coupled to the fuel path and configured to introduce the fuel into the flow path. 6. The fuel injector assembly of claim 4, wherein the swirler apparatus further includes a swirler positioned within the manifold. 7. A gas turbine engine, comprising: a compressor section comprising a compressor configured to compress an air flow and a deswirl assembly configured to receive the air flow from the compressor; anda combustion section comprising a fuel injector assembly with a stem defining a fuel path for fuel, a flow guide coupled to and extending along the stem, the flow guide receiving at least a portion of the air flow from the deswirl assembly, and a swirler apparatus coupled to the stem and configured to receive the fuel from the fuel path and the portion of the air flow from the flow guide, the swirler apparatus further configured to mix the fuel and the portion of the air to result in a fuel-air mixture,wherein the stem includes a flange coupling the stem to an outer case, the stem defining a length between the flange and the swirler apparatus,wherein the flow guide has a first radial end positioned along the length of the stem and a second radial end at the swirler apparatus, the first radial end of the flow guide being open to define a flow guide inlet for receiving the portion of the air flow from the deswirl assembly and the second radial end of the flow guide being closed to direct the portion of the air flow within the flow guide into the swirler apparatus,wherein the flow guide has two edges attached to the stem to form a flow guide path for the air flow within the flow guide, and wherein the flow guide path is semi-circular shaped or half-moon shaped in cross-section, and a combustor configured to receive the fuel-air mixture from the swirler apparatus and to ignite the fuel-air mixture to generate combustion gases. 8. The gas turbine engine of claim 7, wherein the compressor is a centrifugal compressor. 9. The gas turbine engine of claim 8, wherein the combustor is an axial annular combustor. 10. The gas turbine engine of claim 7, wherein the stem and flow guide extend in a generally radial direction such that the first radial end of the flow guide receives the portion of the air flow in the generally radial direction to guide the portion of the air flow along the stem in the generally radial direction and such that the second radial end of the flow guide redirects the portion of the air flow in a generally axial direction into the swirler apparatus. 11. The gas turbine engine of claim 7, wherein the first radial end and the flow guide inlet are positioned between about 75% and about 25% of the length of the stem. 12. The gas turbine engine of claim 7, wherein the flow guide is configured to aerodynamically couple the deswirl assembly to the swirler apparatus. 13. The gas turbine engine of claim 7, wherein swirler apparatus includes a manifold defining a flow path. 14. The gas turbine engine of claim 13, wherein the manifold defines a fuel outlet coupled to the fuel path and configured to introduce the fuel into the flow path. 15. The gas turbine engine of claim 14, wherein the swirler apparatus further includes a swirler positioned within the manifold. 16. A fuel injector assembly for a gas turbine engine with a compressor section and a combustion section, the fuel injector assembly comprising: a stem defining a fuel path for fuel, wherein the stem includes a flange coupling the stem to an outer case of the combustion section, the stem defining a length between the flange and the swirler apparatus;a flow guide coupled to and extending along the stem, the flow guide receiving an air flow; anda swirler apparatus coupled to the stem and configured to receive the fuel, the swirler apparatus further coupled to the flow guide and configured to receive the air flow, the swirler apparatus configured to mix the fuel and the air flow and direct the mixture into a combustor of the combustor assembly,wherein the flow guide has a first radial end positioned along the length of the stem and a second radial end at the swirler apparatus, the first radial end of the flow guide being open to define a flow guide inlet for receiving the air flow and the second radial end of the flow guide being closed to direct the air flow within the flow guide into the swirler apparatus,wherein the flow guide has two radially extending edges attached to the stem to form a flow guide path for the air flow within the flow guide. 17. The fuel injector of claim 16, wherein the stem and flow guide extend in a generally radial direction such that the first radial end of the flow guide receives the air flow in the generally radial direction to guide the air flow along the stem in the generally radial direction and such that the second radial end of the flow guide redirects the air flow in a generally axial direction into the swirler apparatus. 18. The fuel injector assembly of claim 16, wherein the flow guide path is semi-circular shaped or half-moon shaped in cross-section.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (13)
Romey Russell P. (Jacksonville FL) Greer Lonny R. (Jacksonville FL), Adjustable non-piloted air blast fuel nozzle.
Lipinski, John Joseph; Johnson, Thomas Edward; Ziegler, Robert Paul; Schroder, Mark Stewart, Axial flow sleeve for a turbine combustor and methods of introducing flow sleeve air.
Schmotolocha, Stephen N.; Morris, Donald H.; Pederson, Robert J.; Edelman, Raymond B.; Morrison, Jr., Calvin Q., Compact swirl augmented afterburners for gas turbine engines.
Yee, David K.; Corr, II, Robert Anthony; Nickolas, Sarento George, Design and control strategy for catalytic combustion system with a wide operating range.
Prociw Lev A. (Willowdale CAX) Bouchard Alain (St. Charles Borromee CAX) Bolduc Pierre (St. Amable CAX) Stastny Honze (West St. Bruno CAX), Radially mounted air blast fuel injector.
Schumacher,Jurgen C.; Zupanc,Frank J.; Yankowich,Paul R.; Dudebout,Rodolphe; Barton,Michael T., System for coupling flow from a centrifugal compressor to an axial combustor for gas turbines.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.