Fuel injector with heat pipe cooling

Patent metadata

Field	Value
Publication number	US-10458331-B2
Application number	US-201615187149-A
Country	US
Kind code	B2
Filing date	Jun 20, 2016
Priority date	Jun 20, 2016
Publication date	Oct 29, 2019
Grant date	Oct 29, 2019

Abstract

Fuel injectors for gas turbine engines are provided herein. The fuel injectors include a nozzle configured to dispense fuel into a combustor of a gas turbine engine, a fuel conduit fluidly connecting a fuel source to the nozzle, and a heat pipe having a vaporization section and a condensation section, wherein the vaporization section is in thermal communication with the nozzle and the condensation section is in thermal communication with a cooling source of the gas turbine engine.

First claim

What is claimed is:

1. A fuel injector for a gas turbine engine comprising:
a nozzle configured to dispense fuel into a combustor of the gas turbine engine;
a fuel conduit fluidly connecting a fuel source to the nozzle to supply fuel therethrough; and
a heat pipe having a vaporization section and a condensation section, wherein the vaporization section is in thermal communication with the nozzle and the condensation section is in thermal communication with the fuel source, wherein the condensation section extends into the fuel source.

2. The fuel injector of claim 1 , wherein the vaporization section of the heat pipe is wrapped around the nozzle.

3. The fuel injector of claim 1 , wherein at least a portion of the heat pipe passes through a wall of a portion of the fuel injector.

4. The fuel injector of claim 1 , wherein the heat pipe is integrally formed with at least one of the nozzle and the fuel conduit.

5. The fuel injector of claim 1 , wherein the heat pipe is one of a thermosiphon, a capillary-driven heat pipe, an annular heat pipe, a vapor chamber, a gas-loaded heat pipe, a loop heat pipe, a capillary pumped loop heat pipe, a pulsating heat pipe, a micro heat pipe, or a miniature heat pipe.

6. The fuel injector of claim 1 , wherein the nozzle and fuel conduit are components of an axially staged fuel injector.

7. The fuel injector of claim 1 , wherein the nozzle and fuel conduit are components of a radially staged fuel injector.

8. The fuel injector of claim 1 , wherein at least a portion of the fuel injector is additively manufactured and the heat pipe is formed by the additive manufacturing process within the fuel injector.

9. The fuel injector of claim 1 , wherein the heat pipe is a pulsating heat pipe.

10. A gas turbine engine comprising:
a combustor section having a plurality of components; and
a heat pipe configured with a first fuel injector of the combustor section, the heat pipe having a vaporization section and a condensation section, wherein the vaporization section of the heat pipe is in thermal communication with the first fuel injector and the condensation section is in thermal communication with a cooling source,
wherein the first fuel injector includes a nozzle and a fuel conduit fluidly connecting a first fuel source to the nozzle to supply fuel therethrough, wherein the vaporization section is in thermal communication with the nozzle and the condensation section is in thermal communication with the cooling source, and wherein with the cooling source is the first fuel source, wherein the condensation section extends into the fuel source.

11. The gas turbine engine of claim 10 , wherein the vaporization section of the heat pipe is wrapped around the nozzle.

12. The gas turbine engine of claim 10 , wherein the nozzle and fuel conduit are components of an axially staged fuel injector.

13. The gas turbine engine of claim 10 , further comprising a second fuel injector that is a radially staged fuel injector of the gas turbine engine.

14. The gas turbine engine of claim 13 , wherein the second fuel injector includes a second nozzle configured to dispense fuel into the combustor and a second fuel conduit fluidly connecting a second fuel source to the second nozzle, the gas turbine engine further comprising a second heat pipe having a vaporization section and a condensation section, wherein the vaporization section of the second heat pipe is in thermal communication with the nozzle of the second fuel injector and the condensation section of the second heat pipe is in thermal communication with a second cooling source.

15. The gas turbine engine of claim 14 , wherein at least one of the first and second fuel sources are the same fuel source and the first and second cooling sources are the same cooling source.

16. The gas turbine engine of claim 10 , wherein the heat pipe is integrally formed with the first fuel injector.

17. The gas turbine engine of claim 10 , wherein the heat pipe is one of a thermosiphon, a capillary-driven heat pipe, an annular heat pipe, a vapor chamber, a gas-loaded heat pipe, a loop heat pipe, a capillary pumped loop heat pipe, a pulsating heat pipe, a micro heat pipe, or a miniature heat pipe.

18. The gas turbine engine of claim 10 , wherein the first fuel injector is additively manufactured and the heat pipe is formed by the additive manufacturing process within the first fuel injector.

Assignees

• United Technologies Corp

Inventors

• Xu Jinquan

Classifications

• F23R3/346

  for staged combustion · CPC title

• F28D2021/0024

  for combustion apparatus, e.g. for boilers · CPC title

• F28D15/04

  with tubes having a capillary structure · CPC title

• F23D2214/00

  Cooling · CPC title

• F02C7/12 Primary

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title