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US 2017/0363004 A1Published application
Combustor component having enhanced cooling
AssigneeUnited Technologies Corporation
InventorJinQuan Xu
Life of this patent
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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.
Claims20
A fuel injector for a gas turbine engine comprising:
- 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.
1 more element
A gas turbine engine comprising:
- a combustor section having a plurality of components;
- and
- a heat pipe configured with at least one of the plurality of components 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 at least one component and the condensation section is in thermal communication with a cooling source.
Dependencies are inferred from the claim text.