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US 2019/0162118 A1Published application
Gas turbine engine with plural accessory air paths
AssigneeUnited Technologies Corporation
InventorsGabriel L. Suciu, Jesse M. Chandler
Life of this patent
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Abstract
A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications.
Claims20
A gas turbine engine comprising:
- a first source of air to be delivered into a core of the engine, a second source of air, distinct from said first source of air and including a controller configured to separately control first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications;
- and
- said distinct auxiliary applications including at least one of cooling a pitch control mechanism for a propeller included in the gas turbine engine, cooling a gear reduction and an environmental control system.
A gas turbine engine comprising:
- a first means for supply of a first source of air to a first auxiliary application through a first fan;
- a second means for supply of a second source of air, distinct from said first source of air, to a second auxiliary application through a second fan;
- and
- control means for separately controlling the first and second fans.
1 more element
Dependencies are inferred from the claim text.