Gas-turbine burner for a gas turbine with purging mechanism for a fuel nozzle
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/22
F02C-007/232
출원번호
US-0382572
(2009-03-18)
등록번호
US-8443609
(2013-05-21)
우선권정보
DE-10 2008 014 744 (2008-03-18)
발명자
/ 주소
Doerr, Thomas
Rackwitz, Leif
Lazik, Waldemar
출원인 / 주소
Rolls-Royce Deutschland Ltd & Co KG
대리인 / 주소
Klima, Timothy J.
인용정보
피인용 횟수 :
2인용 특허 :
13
초록▼
A gas-turbine burner for a gas turbine includes a fuel nozzle 1 having several fuel exit holes 23, which are each connected to a fuel line 5, 7, 29, 30, through which fuel can be passed selectively Between individual fuel exit holes 23, different static pressures of the airflow are provided between
A gas-turbine burner for a gas turbine includes a fuel nozzle 1 having several fuel exit holes 23, which are each connected to a fuel line 5, 7, 29, 30, through which fuel can be passed selectively Between individual fuel exit holes 23, different static pressures of the airflow are provided between fuel lines flown by fuel and fuel lines not flown by fuel.
대표청구항▼
1. A burner for a gas turbine, comprising: a fuel nozzle having a plurality of fuel exit holes, each connected to a fuel line, through which fuel is selectively passed, wherein certain ones of the fuel exit holes are selectively subjected to different static pressures of airflow through the burner t
1. A burner for a gas turbine, comprising: a fuel nozzle having a plurality of fuel exit holes, each connected to a fuel line, through which fuel is selectively passed, wherein certain ones of the fuel exit holes are selectively subjected to different static pressures of airflow through the burner than others of the fuel exit holes interconnected with the certain ones to create a purging air flow through the fuel exit holes;wherein a surface contour of flow-wetted components upstream of the fuel exit holes has a convergent profile and the convergent profile provides the different static pressures. 2. The burner of claim 1, wherein the different static pressures are provided by selecting different pressures in the fuel lines. 3. The burner of claim 1, wherein the certain ones of the fuel exit holes are positioned in burner areas with different static pressures than the others of the fuel exit holes. 4. The burner of claim 3, wherein the certain ones of the fuel exit holes are staggered with respect to the others of the fuel exit holes with reference to a burner axis. 5. The burner of claim 1, and further comprising swirler vanes that generate pressure differences between fuel exit holes. 6. The burner of claim 5, wherein a setting of vanes provides for the generation of pressure differences between fuel exit holes. 7. The burner of claim 5, wherein a profiling of the vanes provides for the generation of pressure differences between fuel exit holes. 8. The burner of claim 1, wherein the certain ones of the fuel exit holes have different bore diameters than the others of the fuel exit holes. 9. The burner of claim 1, and further comprising at least one directional control valve for selectively applying purging to the fuel lines. 10. A method for draining fuel lines of a nozzle of a gas-turbine burner, comprising: subjecting at least one group of fuel exit holes to a different static pressure than another group of interconnected fuel exit holes to create a purging airflow through the fuel exit holes;providing a surface contour of flow-wetted components upstream of the fuel exit holes with a convergent profile to provide the different static pressure. 11. The method of claim 10, wherein the different static pressures are provided by selecting different pressures in the fuel lines. 12. The method of claim 10, wherein the different static pressures are created by different positioning of the one group with respect to the other group in the nozzle to be respectively exposed to different static pressures in the nozzle. 13. A fuel nozzle, comprising a plurality of fuel exit holes selectively connectable between at least one line connected to a pressurized fuel supply for supplying fuel to a gas turbine from the fuel exit holes and an air supply for purging fuel from the at least one line, wherein certain ones of the fuel exit holes are selectively subjected to different static pressures of airflow through the fuel nozzle than others of the fuel exit holes interconnected with the certain ones to create a purging air flow through the fuel exit holes; wherein a surface contour of flow-wetted components upstream of the fuel exit holes has a convergent profile and the convergent profile provides the different static pressures. 14. The fuel nozzle of claim 13, wherein the air supply is selectively connected by blocking the connection to the pressurized fuel supply. 15. The fuel nozzle of claim 13, and further comprising a directional control valve connected to the at least one line that can be opened to selectively connect the fuel exit holes to the air supply for purging fuel. 16. A fuel nozzle, comprising: a first aperture set and a second aperture set, at least one of the aperture sets selectively connected to a fuel supply for supplying fuel to the gas turbine, at least one aperture of the first aperture set being flowingly connected by at least one line to at least one aperture of the second aperture set, the at least one line selectively supplying fuel to at least one of the apertures of the first and second aperture sets, the fuel nozzle configured and arranged to provide a higher air pressure at the at least one aperture of the first aperture set than at the at least one aperture of the second aperture set such that when a flow of pressurized fuel is shut-off to the at least one aperture set for supplying fuel, a pressure differential between the higher air pressure aperture and the lower air pressure aperture causes air to flow through the line between the higher air pressure aperture and the lower air pressure aperture to purge fuel from the line;wherein a surface contour of flow-wetted components upstream of the fuel exit holes has a convergent profile and the convergent profile provides the higher and lower air pressures. 17. The fuel nozzle of claim 16, wherein the at least one aperture of the first aperture set is selectively connected to the at least one aperture of the second aperture set by a directional control valve. 18. The fuel nozzle of claim 16, wherein the at least one line selectively supplies fuel to both of the at least one aperture of the first aperture set and the at least one aperture of the second aperture set. 19. The fuel nozzle of claim 16, wherein the first aperture set comprises a plurality of apertures, the second aperture set comprises a like plurality of apertures and each of the apertures in the first aperture set is connected to a counterpart aperture of the second aperture set by a respective line.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (13)
Joshi Narendra D. (Cincinnati OH) Ekstedt Edward E. (Montgomery OH) Epstein Michael J. (West Chester OH), Air fuel mixer for gas turbine combustor.
Sharifi Mehran (Winter Springs FL) Stokes Mitchell O. (Orlando FL) Foss David T. (Austin TX), Gas turbine combustor with turbulence enhanced mixing fuel injectors.
Dobbeling Klaus,CHX ; Engelbrecht Geoffrey,CHX ; Magni Fulvio,CHX ; Muller Gerhard,DEX, Method for reliably removing liquid fuel from the fuel system of a gas turbine, and a device for carrying out the method.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.