Swirler for use in a burner of a gas turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
F02G-003/00
출원번호
US-0224242
(2007-02-15)
등록번호
US-8302404
(2012-11-06)
우선권정보
GB-0603488.8 (2006-02-22)
국제출원번호
PCT/EP2007/051469
(2007-02-15)
§371/§102 date
20080821
(20080821)
국제공개번호
WO2007/096294
(2007-08-30)
발명자
/ 주소
Nilsson, Ulf
Wilbraham, Nigel
출원인 / 주소
Siemens Aktiengesellschaft
인용정보
피인용 횟수 :
3인용 특허 :
10
초록▼
Disclosed is a swirler for use in a burner of a gas turbine engine, the swirler comprising a plurality of vanes arranged in a circle, flow slots being defined between adjacent vanes in the circle, each flow slot having an inlet end and an outlet end, in use of the swirler a flow of fuel and air trav
Disclosed is a swirler for use in a burner of a gas turbine engine, the swirler comprising a plurality of vanes arranged in a circle, flow slots being defined between adjacent vanes in the circle, each flow slot having an inlet end and an outlet end, in use of the swirler a flow of fuel and air travelling along each flow slot from its inlet end to its outlet end such that the swirler provides a swirling mix of the fuel and air, at least one vane having an edge adjacent an inlet end of a flow slot configured to generate within the flow slot one or more flow vortices that extend along the slot thereby to enhance mixing of the fuel and air travelling along the slot.
대표청구항▼
1. A swirler for use in a burner of a gas turbine engine, comprising: a plurality of vanes arranged in a circle pattern along the burner; anda plurality of flow slots where each slot is defined between adjacent vanes of the circle, each flow slot having an inlet end and an outlet end to direct an ai
1. A swirler for use in a burner of a gas turbine engine, comprising: a plurality of vanes arranged in a circle pattern along the burner; anda plurality of flow slots where each slot is defined between adjacent vanes of the circle, each flow slot having an inlet end and an outlet end to direct an air flow towards a central space within the circle, wherein fuel is supplied into the flow slot, such that a mixture of fuel and air enters the central space, wherein at least one vane has a first edge adjacent an inlet end of the flow slot,wherein the first edge adjacent to the inlet end of the flow slot is divided into a plurality of portions along said first edge, including a sharp straight portion and a smooth profiled portion, each portion being configured to provide a respective flow velocity therepast for forcibly redirecting a flow vortex so that the vortex no longer extends substantially parallel to the edge but extends at an angle to the parallel, andwherein the sharp straight portion and the smooth profiled portion are separated by a ledge. 2. The swirler according to claim 1, wherein the sharp straight portion has a substantially smaller length along the first edge that the smooth profiled portion. 3. The swirler according to claim 2, wherein each flow slot has a base and a top that extend between adjacent vanes defining the slot and along the slot from its inlet to its outlet ends, the sharp straight portion of the first edge adjacent the inlet end of the slot being disposed adjacent the base of the slot, the smooth profiled portion of the first edge adjacent the inlet end of the slot arranged adjacent the top of the slot, and wherein fuel is supplied to at least one slot at its base. 4. The swirler according to claim 3, wherein a second edge of each vane is adjacent an inlet end of a further flow slot, the second edge being sharp along its entire length. 5. The swirler according to claim 4, wherein the fuel is supplied to a flow slot from a location along the second edge. 6. The swirler according to claim 4, wherein the fuel is supplied to at least one flow slot from the smooth profiled portion of the first edge adjacent the inlet end of the flow slot. 7. The swirler according to claim 4, wherein the fuel is supplied to at least one flow slot from both the sharp straight portion and the smooth profiled portion of the first edge adjacent the inlet end of the flow slot. 8. The swirler according to claim 4, wherein the fuel is supplied to at least one flow slot from the ledge that separates the sharp straight portion and the smooth profiled portion of the first edge adjacent the inlet end of the flow slot. 9. The swirler according to claim 1, wherein the first edge adjacent the inlet end of the flow slot comprises three portions, having two sharp straight portions separated by a smooth profiled portion, and wherein the fuel is supplied to at least one flow slot from the smooth portion. 10. The swirler according to claim 1, wherein the first edge adjacent the inlet end of the flow slot comprises three portions having two smooth profiled portions separated by a sharp straight portion, and wherein the fuel is supplied to at least one flow slot from the sharp straight portion. 11. The swirler according to claim 10, wherein each vane is wedge shaped, and the wedge shaped vanes are arranged in the circle such that the thin ends of the wedge shaped vanes are directed generally radially inwardly, the opposite broad ends of the wedge shaped vanes face generally radially outwardly, and the flow slots defined between adjacent vanes are directed generally radially inwardly.
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이 특허에 인용된 특허 (10)
Simmons Harold C. (Richmond Heights OH) Conrad Robert R. (Chardon OH) Orav Mihkel (Euclid OH), Air-atomizing fuel nozzle.
Schmotolocha, Stephen N.; Morris, Donald H.; Pederson, Robert J.; Edelman, Raymond B.; Morrison, Jr., Calvin Q., Compact swirl augmented afterburners for gas turbine engines.
Toon, Ian J.; O'Dell, Stephen J.; Currin, John H.; Willis, Jeffrey D., Staged gas turbine combustion chamber with counter swirling arrays of radial vanes having interjacent fuel injection.
Yoshida, Shouhei; Hirata, Yoshitaka; Inoue, Hiroshi; Murota, Tomoya; Sasao, Toshifumi; Kobayashi, Nariyoshi, Combustor comprising a member including a plurality of air channels and fuel nozzles for supplying fuel into said channels.
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