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US 2014/0208714 A1Published application
Thermal Management for Gas Turbine Engine
AssigneeUnited Technologies Corporation
InventorsAnthony C. Jones, Charles Brian Travelbee, Patrick M. Lydon, Eric J. Alexander, Nagamany Thayalakhandan
Life of this patent
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Abstract
A gas turbine engine has an inlet duct, which is configured to communicate with an inlet to a compressor. The inlet duct is further configured to communicate air outwardly of an outer casing of the gas turbine engine, and to pass the air along an axial length of the gas turbine engine to cool a component associated with the gas turbine engine.
Claims16
A gas turbine engine comprising:
- an inlet duct, said inlet duct configured to communicate with an inlet to a compressor;
- said inlet duct further configured to communicate air outwardly of an outer casing of the gas turbine engine, and to pass the air along an axial length of the gas turbine engine to cool a component associated with said gas turbine engine.
A vehicle comprising:
- a body having at least one aerodynamic surface;
- and
- a gas turbine engine, the gas turbine engine including an inlet duct, said inlet duct configured to communicate with an inlet to a compressor;
- said inlet duct further configured to communicate cooling air outwardly of an outer casing of the gas turbine engine, and for passing along an axial length of the gas turbine engine to cool a component associated with said gas turbine engine.
1 more element
Dependencies are inferred from the claim text.