High frequency-stabilized combustion in aircraft gas turbines

Patent metadata

Field	Value
Publication number	US-9625145-B2
Application number	US-201414313474-A
Country	US
Kind code	B2
Filing date	Jun 24, 2014
Priority date	Jun 27, 2013
Publication date	Apr 18, 2017
Grant date	Apr 18, 2017

Abstract

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.

First claim

What is claimed is:

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; 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 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.

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; 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 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.

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.

Assignees

• Eads Deutschland Gmbh
• Airbus Defence & Space Gmbh

Inventors

• Steinwandel Juergen
• Stuhlberger Johannes

Classifications

• F23N2241/20

  Gas turbines · CPC title

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title

• F23C99/001 Primary

  Applying electric means or magnetism to combustion (for combustion engines F02B51/04, F02M27/04) · CPC title

• F23N5/006

  the detector being sensitive to oxygen · CPC title

• F02C7/00

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title