Slinger combustor having main combustion chamber and sub-combustion chamber, and gas turbine engine system having the same

Patent metadata

Field	Value
Publication number	US-10907834-B2
Application number	US-201715609354-A
Country	US
Kind code	B2
Filing date	May 31, 2017
Priority date	Jul 1, 2016
Publication date	Feb 2, 2021
Grant date	Feb 2, 2021

Abstract

A slinger combustor includes; a first compressed air line connected to a compressor and configured to supply compressed air; a first fuel line connected to a fuel storage and configured to supply fuel; a rotation shaft configured to rotate and inject the fuel supplied from the first fuel line; a main combustion chamber configured to receive the fuel injected from the rotation shaft and receive the compressed air from the first compressed air line; and a sub-combustion chamber configured to selectively discharge a flame generated in an inner space of the sub-combustion chamber to the main combustion chamber.

First claim

What is claimed is:

1. A slinger combustor comprising:
a first compressed air line connected to a compressor and configured to supply compressed air, including a first compressed air portion and a second compressed air portion;
a first fuel line connected to a fuel storage and configured to supply fuel, including a first fuel portion and a second fuel portion;
a rotation shaft configured to rotate and inject the fuel supplied from the first fuel line;
a main combustion chamber configured to receive the fuel injected from the rotation shaft and receive the first compressed air portion from the first compressed air line;
a sub-combustion chamber configured to selectively discharge a flame generated in the sub-combustion chamber to the main combustion chamber; at least one valve through which the first fuel portion is supplied to the main combustion chamber and at least one other valve through which the second fuel portion is supplied to the sub-combustion chamber;
an opening/shutting valve through which the second compressed air portion is supplied to the sub-combustion chamber separately from the second fuel portion such that the second compressed air portion first contacts the second fuel portion within the sub-combustion chamber, the second compressed air portion comprising all the compressed air being supplied to the sub-combustion chamber; and
a controller comprising at least one processor, the processor configured to:
open the opening/shutting valve to supply the second compressed air portion to the sub-combustion chamber and shut off the at least one other valve to cut off the supply of the second fuel portion to the sub-combustion chamber, during combustion in the main combustion chamber; and
shut off the opening/shutting valve to cut off the supply of the second compressed air portion to the sub-combustion chamber and open the at least one other valve to supply the second fuel portion to the sub-combustion chamber while the opening/shutting valve is shut off, based on sensing occurrence of a flameout in the main combustion chamber, so that the flame is generated in the sub-combustion chamber and discharged to the main combustion chamber for re-ignition; and
wherein after the flame is generated in the sub-combustion chamber which stored the second compressed air portion for the re-ignition, the flame is discharged by an injector while rotation speed of the rotation shaft is maintained.

2. The slinger combustor of claim 1 , wherein, during the combustion in the main combustion chamber, the second compressed air portion is supplied to the main combustion chamber by passing through the sub-combustion chamber, and during the flameout in the main combustion chamber, the sub-combustion chamber generates the flame and discharges the flame to the main combustion chamber.

3. The slinger combustor of claim 2 , wherein the flame discharged to the main combustion chamber generates the re-ignition in the main combustion chamber at a moment of sensing the occurrence of the flameout while the rotation speed of the rotation shaft is not changed at the moment of sensing the occurrence of the flameout from a moment before sensing the occurrence of the flameout.

4. The slinger combustor of claim 1 , further comprising:
a second compressed air line having one end branched from the first compressed air line and an opposite end connected to the sub-combustion chamber; and
a second fuel line having one end branched from the first fuel line and an opposite end connected to the sub-combustion chamber.

5. The slinger combustor of claim 1 , wherein the sub-combustion chamber is arranged to face a nozzle of the rotation shaft for injecting the fuel.

6. The slinger combustor of claim 1 , wherein the sub-combustion chamber comprises
an ignition plug configured to generate the flame.

7. A gas turbine engine system comprising:
the slinger combustor of claim 1 ;
the compressor;
the fuel storage arranged spaced apart from the compressor; and
a turbine connected to an outlet of the slinger combustor.

Assignees

• Hanwha Aerospace Co Ltd

Inventors

• Park Soo Youl

Classifications

• F23R3/50 Primary

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title

• F23R3/28

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

• F23R3/16

  with devices inside the flame tube or the combustion chamber to influence the air or gas flow · CPC title

• F02C7/22

  Fuel supply systems · CPC title

• F23R3/38 Primary

  comprising rotary fuel injection means · CPC title