Method and apparatus for operating gas turbine engine heat exchangers
OwnerMichael Ralph Storage, Kevin Richard Leamy +1inventors
InventorsMichael Ralph Storage, Kevin Richard Leamy, Brian Neal
Life of this patent
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Abstract
A method for assembling a turbine engine includes assembling a heat exchanger assembly that includes at least a radially inner plate, a radially outer plate, and a heat exchanger coupled between the radially inner and outer plates, forming the heat exchanger assembly such that the heat exchanger assembly has a substantially arcuate shape, and coupling the heat exchanger to a fan casing such that the heat exchanger is positioned upstream or downstream from the fan assembly.
Claims13
A method for assembling a turbine engine to facilitate reducing an operating temperature of a fluid utilized therein, the turbine engine including a core gas turbine engine, a splitter circumscribing the core gas turbine engine, the fan assembly disposed upstream from the core gas turbine engine, a fan casing substantially circumscribing the fan assembly, and a bypass duct that is defined between the fan casing and the splitter, said method comprising:
- providing an arcuate liquid-to-air heat exchanger that includes:
- a plurality of channels extending therethrough;
- a plurality of cooling fins coupled to each of the plurality of channels and configured to receive a flow of air to facilitate reducing a temperature of a liquid flowing through the channels;
- at least one attachment portion formed unitarily with the heat exchanger, the heat exchanger having a first width, the at least one attachment portion having a second width that is less than the first width such that a recess is defined radially inward from the at least one attachment portion;
- and at least one inner plate coupled at the recess to facilitate directing airflow over the cooling fins;
- bending the heat exchanger such that the heat exchanger has a circumferential and axial profile that is substantially conforms to the circumferential and axial profile of the fan duct at the location within the fan duct where the air cooled heat exchanger is mounted;
- and coupling the heat exchanger within in the bypass duct.
A gas turbine engine assembly comprising:
- a core gas turbine engine;
- a nacelle circumscribing said core gas turbine engine;
- and
- a heat exchanger assembly disposed within said nacelle, said heat exchanger assembly comprising:
- an arcuate liquid-to-air heat exchanger that is circumferentially oriented and is configured to be contacted by a flow of air within the nacelle and outside of the core gas turbine engine said heat exchanger comprising:
- a plurality of channels extending therethrough;
- a plurality of cooling fins coupled-thereto such that air can flow over said cooling fins to facilitate reducing a temperature of a liquid flowing through said channels;
- at least one attachment portion formed unitarily with said heat exchanger, said heat exchanger having a first width, said at least one attachment portion having a second width that is less than the first width such that a recess is defined radially inward from said at least one attachment portion;
- and
- at least one inner plate coupled at the recess to facilitate directing airflow over said cooling fins.
Dependencies are inferred from the claim text.