High frequency-stabilized combustion in aircraft gas turbines
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
F23C-099/00
F23N-005/00
F23R-003/28
F02C-007/00
출원번호
US-0313474
(2014-06-24)
등록번호
US-9625145
(2017-04-18)
우선권정보
DE-10 2013 010 706 (2013-06-27)
발명자
/ 주소
Steinwandel, Juergen
Stuhlberger, Johannes
출원인 / 주소
Airbus Defence and Space GmbH
대리인 / 주소
Crowell & Moring LLP
인용정보
피인용 횟수 :
0인용 특허 :
6
초록▼
A gas turbine includes a combustion chamber and a microwave source to produce microwave radiation. The gas turbine is arranged to guide the microwave radiation into a cavity of the combustion chamber. Due to the microwave radiation, in the cavity of the combustion chamber, combustion in the cavity m
A gas turbine includes a combustion chamber and a microwave source to produce microwave radiation. The gas turbine is arranged to guide the microwave radiation into a cavity of the combustion chamber. Due to the microwave radiation, in the cavity of the combustion chamber, combustion in the cavity may be supported and thus lean operation of the gas turbine is made possible.
대표청구항▼
1. A gas turbine, comprising: a combustion chamber with a cavity configured to receive and burn a fuel-air mixture, wherein the combustion chamber is an annular combustion chamber that extends annularly about a rotational axis of the gas turbine; anda microwave source configured to produce microwave
1. A gas turbine, comprising: a combustion chamber with a cavity configured to receive and burn a fuel-air mixture, wherein the combustion chamber is an annular combustion chamber that extends annularly about a rotational axis of the gas turbine; anda microwave source configured to produce microwave radiation,wherein the gas turbine is configured to guide the microwave radiation into the cavity of the combustion chamber to support the combustion of the fuel-air mixture in the combustion chamber,wherein the gas turbine comprises an annular first chamber attached to the combustion chamber, so as to be disposed outside of the combustion chamber from a perspective of the rotational axis of the gas turbine, and extending annularly about the rotational axis of the gas turbine,wherein an annular second chamber is disposed inside the first chamber, and extending annularly about the rotational axis of the gas turbine,wherein a plurality of microwave-permeable windows is included in a limiting surface between the combustion chamber and the second chamber and are arranged annularly about the rotational axis of the gas turbine,wherein the second chamber has a plurality of slits that are arranged annularly about the rotational axis of the gas turbine and opposing the microwave-permeable windows, andwherein the microwave source is connected to an antenna that projects into the first chamber. 2. The gas turbine of claim 1, wherein the microwave source is arranged outside of the combustion chamber. 3. The gas turbine of claim 1, wherein at least one of the plurality of microwave-permeable windows is configured to pass the microwave radiation into the cavity of the combustion chamber. 4. The gas turbine of claim 1, further comprising: a horn antenna configured to radiate the microwave radiation into the cavity of the combustion chamber. 5. The gas turbine of claim 1, further comprising: a waveguide configured to guide the microwave radiation from the microwave source to the combustion chamber. 6. The gas turbine of claim 1, wherein the gas turbine has a plurality of microwave sources arranged annularly about the rotational axis of the gas turbine. 7. The gas turbine of claim 1, wherein the microwave source is configured to produce the microwave radiation with a frequency between 1 and 100 GHz. 8. The gas turbine of claim 1, wherein the microwave source is configured to produce a pulsed microwave radiation. 9. The gas turbine of claim 1, wherein the gas turbine is an aircraft gas turbine. 10. The gas turbine of claim 1, further comprising: an electronic control configured to regulate the microwave source. 11. An aircraft, comprising: a gas turbine, which comprises a combustion chamber with a cavity configured to receive and burn a fuel-air mixture, wherein the combustion chamber is an annular combustion chamber that extends annularly about a rotational axis of the gas turbine; anda microwave source configured to produce microwave radiation,wherein the gas turbine is configured to guide the microwave radiation into the cavity of the combustion chamber to support the combustion of the fuel-air mixture in the combustion chamber,wherein the gas turbine comprises an annular first chamber attached to the combustion chamber, so as to be disposed outside of the combustion chamber from a perspective of the rotational axis of the gas turbine, and extending annularly about the rotational axis of the gas turbine,wherein an annular second chamber is disposed inside the first chamber, and extending annularly about the rotational axis of the gas turbine,wherein a plurality of microwave-permeable windows is included in a limiting surface between the combustion chamber and the second chamber and are arranged annularly about the rotational axis of the gas turbine,wherein the second chamber has a plurality of slits that are arranged annularly about the rotational axis of the gas turbine and opposing the microwave-permeable windows, andwherein the microwave source is connected to an antenna that projects into the first chamber. 12. A method for controlling a gas turbine, the gas turbine comprising: a combustion chamber with a cavity configured to receive and burn a fuel-air mixture, wherein the combustion chamber is an annular combustion chamber that extends annularly about a rotational axis of the gas turbine; and a microwave source configured to produce microwave radiation, wherein the gas turbine is configured to guide the microwave radiation into the cavity of the combustion chamber to support the combustion of the fuel-air mixture in the combustion chamber, wherein the gas turbine comprises an annular first chamber attached to the combustion chamber, so as to be disposed outside of the combustion chamber from a perspective of the rotational axis of the gas turbine, and extending annularly about the rotational axis of the gas turbine, wherein an annular second chamber is disposed inside of the first chamber, and extending annularly about the rotational axis of the gas turbine, wherein a plurality of microwave-permeable windows is included in a limiting surface between the combustion chamber and the second chamber and are arranged annularly about the rotational axis of the gas turbine, wherein the second chamber has a plurality of slits that are arranged annularly about the rotational axis of the gas turbine and opposing the microwave permeable windows, and wherein the microwave source is connected to an antenna that projects into the first chamber, the method comprising the steps: determining an oxygen content of exhaust gases emitted by the gas turbine; regulating the microwave source to produce the microwave radiation as a function of the determined oxygen content of the exhaust gases; and introducing the microwave radiation from the microwave source into the cavity of the combustion chamber of the gas turbine.
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