Can annular combustion arrangement with flow tripping device
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/02
F23R-003/26
F23R-003/54
F23R-003/00
F23R-003/46
출원번호
US-0691947
(2012-12-03)
등록번호
US-9297532
(2016-03-29)
발명자
/ 주소
Wasif, Samer P.
Meisl, Juergen
Janus, Bertram
Koch, Andreas
출원인 / 주소
Siemens Aktiengesellschaft
인용정보
피인용 횟수 :
0인용 특허 :
12
초록▼
A can annular combustion arrangement (12) for a gas turbine engine (10), including: a combustor can (14) having an inlet (46) at a head end (62); an annular chamber (30) surrounding the combustor can (14) for delivering a flow of compressed air from a plenum (18) to the inlet (46); a fuel injector (
A can annular combustion arrangement (12) for a gas turbine engine (10), including: a combustor can (14) having an inlet (46) at a head end (62); an annular chamber (30) surrounding the combustor can (14) for delivering a flow of compressed air from a plenum (18) to the inlet (46); a fuel injector (49) configured to inject a flow of fuel into the flow of compressed air; and a flow tripping device (60) surrounding the combustor can (14) and disposed in the annular chamber (30) downstream of the fuel injector (49).
대표청구항▼
1. A can annular combustion arrangement for a gas turbine engine, comprising: a combustor can comprising a combustor can inlet and a burner, the combustor can defining a combustion zone therein downstream of a burner outlet;an annular chamber surrounding the combustor can and comprising an inner dim
1. A can annular combustion arrangement for a gas turbine engine, comprising: a combustor can comprising a combustor can inlet and a burner, the combustor can defining a combustion zone therein downstream of a burner outlet;an annular chamber surrounding the combustor can and comprising an inner dimension defined in part by an exterior surface of the combustor can for delivering a flow of compressed air from a plenum to the combustor can inlet;a fuel injector disposed within the annular chamber and configured to inject a flow of fuel into the flow of compressed air; anda circumferentially continuous, ring shaped flow tripping device extending radially outward with respect to a combustor can longitudinal axis from the combustor can into the annular chamber transverse to a direction of the flow of compressed air, surrounding the combustor can, and disposed axially downstream of the fuel injector and along the combustor can longitudinal axis in a region bounded at one end by the burner outlet and at another end by the combustor can inlet, wherein the flow tripping device defines a narrowest gap between the flow tripping device and a second surface that defines a radially outward boundary of the annular chamber, and wherein at least a portion of an axial length along the combustor can longitudinal axis of the exterior surface of the combustor can between the combustor can inlet and the flow tripping device is characterized by a constant diameter. 2. The can annular combustion arrangement of claim 1, wherein the flow tripping device occupies at least 20% of a height of the annular chamber. 3. The can annular combustion arrangement of claim 1, wherein a height of the flow tripping device varies circumferentially. 4. The can annular combustion arrangement of claim 1, wherein the flow tripping device occupies at least 15% of a cross sectional area of the annular chamber. 5. The can annular combustion arrangement of claim 1, wherein the flow tripping device comprises a tear drop shape with a tapering end of the tear drop shape on a combustor-inlet side of the flow tripping device with respect to the direction of flow of the compressed air in the annular chamber. 6. The can annular combustion arrangement of claim 1, wherein the flow tripping device comprises a vane shaped cross section. 7. The can annular combustion arrangement of claim 1, wherein the flow tripping device comprises a curved leading edge presented to the flow of compressed air. 8. The can annular combustion arrangement of claim 1, wherein the flow tripping device is disposed closer to the inlet than to an outlet of the combustor can. 9. A gas turbine engine, comprising: a can annular combustion assembly comprising a combustor can comprising a combustor inlet, a burner comprising a burner outlet, and defining a combustor can longitudinal axis:an annular chamber surrounding and defined in part by an exterior surface of the combustor can; andan arcuate shaped flow tripping device extending into the annular chamber transverse to a direction of flow of compressed air in the annular chamber, disposed axially along the combustor can longitudinal axis in a region bounded by the burner outlet and the combustor can inlet, and circumferentially extending across a percentage of a circumference of the annular chamber, wherein the percentage is less than 100% and equals at least a quotient of 100 divided by a number of burners in the combustor can;wherein the flow tripping device is disposed downstream of a fuel injector disposed within the annular chamber and configured to create a fuel/air mixture within the annular chamber. 10. The gas turbine engine of claim 9, wherein the flow tripping device is disposed in the annular chamber in a greater flow region of the circumference that experiences a relatively greater mass flow of compressed air when compared to a lesser mass flow region of the circumference, and wherein the flow tripping device is not present in the lesser mass flow region. 11. The gas turbine engine of claim 9, wherein the flow tripping device occupies at least 15% of a flow area of a circumferential portion of the annular chamber which the flow tripping device occupies. 12. The gas turbine engine of claim 9, wherein the flow tripping device comprises a vane-shaped cross section. 13. The gas turbine engine of claim 9, further comprising a plurality of flow tripping devices disposed at different locations in the annular chamber. 14. The gas turbine engine of claim 13, wherein the plurality of flow tripping devices are disposed at different axial locations with respect to the combustor can longitudinal axis. 15. The gas turbine engine of claim 9, wherein the flow tripping device defines an annular gap through which compressed air flows, and wherein at least a portion of an axial extension of the annular gap parallel to the combustor can longitudinal axis is unobstructed between the annular gap and the combustor can inlet. 16. A can annular combustion arrangement for a gas turbine engine, comprising: a combustor can comprising a combustor can inlet, an exterior surface, a radially outward flare in the exterior surface at the combustor can inlet, and a burner;an annular chamber surrounding the combustor can, comprising an inner dimension defined in part by the exterior surface of the combustor can, and configured to deliver a flow of compressed air from a plenum to the combustor can inlet;a fuel injector disposed within the annular chamber configured to inject a flow of fuel into the flow of compressed air; and a circumferentially continuous, ring shaped flow tripping device extending radially outward with respect to a combustor can longitudinal axis from the combustor can into the annular chamber transverse to a direction of the flow of compressed aft, surrounding the combustor can, and disposed axially downstream of the fuel injector and along the combustor can longitudinal axis between the burner outlet and the flare,wherein the flow tripping device defines a gap between the flow tripping device and a second surface that defines a radially outward boundary of the annular chamber, and wherein the gap is a narrowest gap in the annular chamber.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (12)
Alkabie,Hisham, Aerodynamic trip for a combustion system.
Ohyama Yoshishige (Katsuta JPX) Nishimura Yutaka (Katsuta JPX) Sato Yoshio (Hitachi JPX) Nishihara Motohisa (Katsuta JPX) Azuhata Shigeru (Hitachi JPX) Ito Kazuyuki (Katsuta JPX), Control apparatus for and control method of gas turbine.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.