Gas turbine combustor with heat exchanger between rich combustion zone and secondary combustion zone

Patent metadata

Field	Value
Publication number	US-11041623-B2
Application number	US-201815978635-A
Country	US
Kind code	B2
Filing date	May 14, 2018
Priority date	Jun 21, 2017
Publication date	Jun 22, 2021
Grant date	Jun 22, 2021

Abstract

A combustor for a turbomachine includes a rich combustion zone and a low temperature zone downstream of the rich combustion zone. A heat exchanger is positioned downstream of the rich combustion zone and upstream of the low temperature zone. The heat exchanger includes a plurality of air passages, a plurality of air inlets in fluid communication with the plurality of air passages, and a plurality of combustion gas passages. Each of the combustion gas passages extends between a combustion gas inlet in fluid communication with the rich combustion zone and a combustion gas outlet in fluid communication with the low temperature zone. The plurality of combustion gas passages are in thermal communication with the plurality of air passages.

First claim

What we claim is:

1. A combustor for a turbomachine, the combustor comprising:
a rich combustion zone;
a secondary combustion zone, the secondary combustion zone downstream of the rich combustion zone with respect to a flow of combustion gases through the combustor; and
a heat exchanger positioned downstream of the rich combustion zone and upstream of the secondary combustion zone with respect to the flow of the combustion gases, the heat exchanger comprising:
an axial centerline;
an inlet end;
an outlet end;
a plurality of air passages, the plurality of air passages configured to receive a cooling air flow;
a plurality of air inlets in fluid communication with the plurality of air passages;
a plurality of air outlets at the outlet end of the heat exchanger, the plurality of air outlets in fluid communication with the plurality of air passages and the secondary combustion zone; and
a plurality of combustion gas passages for receiving the combustion gases, each of the combustion gas passages extending between a combustion gas inlet at the inlet end in fluid communication with the rich combustion zone and a combustion gas outlet at the outlet end in fluid communication with the secondary combustion zone, the plurality of combustion gas passages in thermal communication with the plurality of air passages, wherein the cooling airflow from the plurality of air passages meets the combustion gas from the plurality of combustion gas passages in the secondary combustion zone, wherein the plurality of combustion gas passages extend along curved lines, and wherein at least two combustion gas passages in the plurality of combustion gas passages extend across one another, without intersecting, within the heat exchanger.

2. The combustor of claim 1 , wherein the combustor is in fluid communication with a compressor such that compressed air flows from the compressor to the combustor, the combustor further comprising a fuel nozzle, a first portion of the compressed air comprises a combustion air flow to the fuel nozzle and a second portion of the compressed air comprises a bypass flow to the plurality of air inlets of the heat exchanger.

3. The combustor of claim 1 , wherein the combustor is a single-stage combustor.

4. A gas turbine, the gas turbine comprising:
a compressor;
a turbine; and
a combustor disposed between the compressor and the turbine, the combustor comprising:
a rich combustion zone;
a secondary combustion zone downstream, the secondary combustion zone of the rich combustion zone with respect to a flow of combustion gases through the combustor;
a heat exchanger positioned downstream of the rich combustion zone and upstream of the secondary combustion zone with respect to the flow of the combustion gases, the heat exchanger comprising:
an axial centerline;
an inlet end;
an outlet end;
a plurality of air passages, the plurality of air passages configured to receive a cooling air flow;
a plurality of air inlets in fluid communication with the plurality of air passages;
a plurality of air outlets at the outlet end of the heat exchanger, the plurality of air outlets in fluid communication with the plurality of air passages and the secondary combustion zone; and
a plurality of combustion gas passages for receiving the combustion gases, each of the combustion gas passages extending between a combustion gas inlet at the inlet end in fluid communication with the rich combustion zone and a combustion gas outlet at the outlet end in fluid communication with the secondary combustion zone, the plurality of combustion gas passages in thermal communication with the plurality of air passages, wherein the cooling airflow from the plurality of air passages meets the combustion gas from the plurality of combustion gas passages in the secondary combustion zone, wherein the plurality of combustion gas passages extend along curved lines, and wherein at least two combustion gas passages in the plurality of combustion gas passages extend across one another, without intersecting, within the heat exchanger.

5. A method of operating a combustor of a turbomachine, wherein the combustor is a single-stage combustor, the combustor comprising:
a rich combustion zone;
a secondary combustion zone, the secondary combustion zone downstream of the rich combustion zone with respect to a flow of combustion gases through the combustor; and
a heat exchanger positioned downstream of the rich combustion zone and upstream of the secondary combustion zone with respect to the flow of the combustion gases, the heat exchanger comprising:
an axial centerline;
an inlet end;
an outlet end;
a plurality of air passages, the plurality of air passages configured to receive a cooling air flow;
a plurality of air inlets in fluid communication with the plurality of air passages;
a plurality of air outlets at the outlet end of the heat exchanger, the plurality of air outlets in fluid communication with the plurality of air passages and the secondary combustion zone; and
a plurality of combustion gas passages for receiving the combustion gases, each of the combustion gas passages extending between a combustion gas inlet at the inlet end in fluid communication with the rich combustion zone and a combustion gas outlet at the outlet end in fluid communication with the secondary combustion zone, the plurality of combustion gas passages in thermal communication with the plurality of air passages, wherein the cooling airflow from the plurality of air passages meets the combustion gas from the plurality of combustion gas passages in the secondary combustion zone, wherein the plurality of combustion gas passages extend along curved lines, and wherein at least two combustion gas passages in the plurality of combustion gas passages extend across one another, without intersecting, within the heat exchanger, the method comprising:

supplying a fuel to the combustor from a fuel supply;
flowing compressed air to the combustor;
mixing a first portion of the compressed air with the fuel from the fuel supply;
combusting the mixed fuel and air in the rich combustion zone to create the combustion gases;
flowing the combustion gases through the plurality of combustion gas passages; and
flowing a second portion of the compressed air through the plurality of air passages in the heat exchanger such that the combustion gases and the second portion of the compressed air are in thermal communication within the heat exchanger.

6. The method of claim 5 , wherein supplying the fuel comprises supplying a liquid fuel.

Assignees

• Gen Electric

Inventors

• Bolanos Felipe
• Wind Torsten
• Biagioli Fernando

Classifications

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F23C2201/401

  Cooling · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• F23R3/346

  for staged combustion · CPC title

• F23R3/005 Primary

  Combined with pressure or heat exchangers · CPC title