Fluid cooling systems for a gas turbine engine
AssigneeGeneral Electric Company
InventorsDaniel Jason Erno, Narendra Digamber Joshi, William Dwight Gerstler
Life of this patent
Estimating the term…
Abstract
A heat exchanger includes an airfoil configured to be positioned in a coolant stream. The airfoil includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and a trailing edge opposite the leading edge. The leading edge defines an impingement zone wherein the coolant stream is configured to impinge the airfoil. The heat exchanger also includes at least one channel defined within the airfoil between the pressure sidewall and the suction sidewall. The at least one channel is at least partially defined within the impingement zone proximate the leading edge.
Claims12
A heat exchanger comprising:
- an airfoil configured to be positioned in a coolant stream, said airfoil comprising:
- a pressure sidewall;
- and
- a suction sidewall coupled to said pressure sidewall, said suction sidewall and said pressure sidewall define a leading edge and a trailing edge opposite said leading edge, said leading edge defines an impingement zone wherein the coolant stream is configured to impinge said airfoil;
- and
- at least one channel defined within said airfoil between said pressure sidewall and said suction sidewall, said at least one channel at least partially defined within the impingement zone proximate said leading edge.
An outlet guide vane comprising:
- an airfoil comprising:
- a pressure sidewall;
- and
- a suction sidewall coupled to said pressure sidewall, said suction sidewall and said pressure sidewall define a leading edge and a trailing edge opposite said leading edge, said leading edge defines an impingement zone wherein the coolant stream is configured to impinge said airfoil;
- and
- a heat exchanger comprising at least one channel defined within said airfoil between said pressure sidewall and said suction sidewall, said at least one channel at least partially defined within the impingement zone proximate said leading edge.
A turbofan engine comprising:
- a core engine;
- a bypass duct at least partially extending about said core engine;
- and
- a plurality of circumferentially spaced outlet guide vanes extending between said core engine and said bypass duct, at least one outlet guide vane of said plurality of outlet guide vanes comprising:
- an airfoil comprising:
- a pressure sidewall;
- and
- a suction sidewall coupled to said pressure sidewall, said suction sidewall and said pressure sidewall define a leading edge and a trailing edge opposite said leading edge, said leading edge defines an impingement zone wherein the coolant stream is configured to impinge said airfoil;
- and
- a heat exchanger comprising at least one channel defined within said airfoil between said pressure sidewall and said suction sidewall, said at least one channel at least partially defined within the impingement zone proximate said leading edge.
Dependencies are inferred from the claim text.