Gas turbine engine and method to cool a gas turbine engine case assembly
AssigneeUnited Technologies Corporation
InventorsJoseph D. Evetts, William J. Riordan, Federico Papa
Life of this patent
Estimating the term…
Abstract
A method of cooling a gas turbine engine case assembly includes moving a fan air valve that is operatively connected to a pre-cooler having a bypass inlet that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet of the pre-cooler into a core compartment.
Claims15
A gas turbine engine, comprising:
- a case assembly is disposed about a gas turbine engine core disposed within a cowl, the cowl defining a core compartment;
- a pre-cooler having a bypass inlet, a bleed air inlet, a bleed air outlet operatively connected to an environmental control system, and a bypass outlet, a fan air valve operatively connected to the bypass inlet, the fan air valve configured to selectively inhibit and facilitate a provision of bypass air to the pre-cooler;
- a bleed air conduit having a pressure regulating/shut-off valve operatively connected to the bleed air inlet and a compressor section of the gas turbine engine core, the pressure regulating/shut-off valve being movable between an open position that facilitates a flow of bleed air from the compressor section to the pre-cooler and a closed position that inhibits the flow of bleed air from the compressor section to the pre-cooler;
- and
- a controller in communication with the fan air valve and the pressure regulating/shut-off valve, the controller configured to operate the fan air valve to facilitate the provision of bypass air to the pre-cooler and the bypass outlet provides bypass air to the core compartment, in response to the pressure regulating/shut-off valve being in the closed position and a core compartment temperature being greater than a target core compartment temperature.
A method of cooling a gas turbine engine case assembly, comprising:
- moving a fan air valve being operatively connected to a pre-cooler having a bypass inlet configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature;
- and
- bleeding the bypass air through a bypass outlet of the pre-cooler into a core compartment.
A method of cooling a gas turbine engine case assembly, comprising:
- monitoring a core compartment temperature;
- calculating a target core compartment temperature;
- comparing the core compartment temperature to the target core compartment temperature, in response to a pressure regulating/shut-off valve operatively connected to a bleed air inlet of a pre-cooler being in a closed position;
- and
- calculating a fan air valve position of a fan air valve operatively connected to the pre-cooler based on the target core compartment temperature, in response to the core compartment temperature being greater than the target core compartment temperature.
Dependencies are inferred from the claim text.