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US 12,571,359 B2Granted
Inlets for gas turbine engine bypass duct heat exchangers
AssigneeRolls-Royce North American Technologies Inc.
InventorsPatrick C. Sweeney, Douglas J. Snyder, Kerry J. Lighty, Scott Schwenker
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Abstract
A bypass duct assembly for a gas turbine engine includes a bypass duct, a heat exchanger assembly, and an inlet cowl. The bypass duct is configured to direct bypass air around an engine core of the gas turbine engine. The heat exchanger assembly includes a heat exchanger located in the bypass duct and configured to transfer heat to the bypass air. The inlet cowl is coupled with the bypass duct and the heat exchanger assembly.
Claims20
A bypass duct assembly for a gas turbine engine, the bypass duct assembly comprising
- a bypass duct that includes an outer wall arranged around an axis and defining an outer boundary of a flow path of bypass air through the bypass duct and an inner wall defining an inner boundary of the flow path of the bypass air,
- a heat exchanger assembly that includes a heat exchanger located in the bypass duct radially between the inner wall and the outer wall and a shroud configured to direct a first portion of the bypass air into the heat exchanger and to direct a second portion of the bypass air in the bypass duct around the heat exchanger, and
- an inlet cowl coupled with the shroud and having a cowl duct configured to collect the first portion of the bypass air and conduct the first portion of the bypass air into the shroud and an air plow that extends radially away from the shroud toward one of the inner wall and the outer wall, and wherein the air plow is formed to define a bow that guides the second portion of the bypass air around the heat exchanger assembly.
A method comprising
- arranging a bypass duct circumferentially around a central axis of a gas turbine engine, the bypass duct including an outer wall defining an outer boundary of a flow path of bypass air through the bypass duct and an inner wall defining an inner boundary of the flow path of the bypass air,
- directing bypass air from an inlet of the gas turbine engine through the flow path,
- arranging a heat exchanger in the bypass duct radially between the inner wall and the outer wall,
- arranging a shroud in the bypass duct downstream from the inlet and upstream from the heat exchanger to direct a first portion of the bypass air into the heat exchanger and to direct a second portion of the bypass air in the bypass duct around the heat exchanger, and
- coupling an inlet cowl to the shroud upstream of the shroud, the inlet cowl having a cowl duct configured to collect the first portion of the bypass air and conduct the first portion of the bypass air into the shroud and an air plow that extends radially away from the shroud and toward one of the inner wall and the outer wall, the air plow formed to define a bow that guides the second portion of the bypass air around the heat exchanger.
2 more elements
Dependencies are inferred from the claim text.