Gas turbine engine and method to cool a gas turbine engine case assembly
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.
1. 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 precooler 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 precooler;
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 precooler and a closed position that inhibits the flow of bleed air from the compressor section to the precooler; and
a controller in communication with the fan air valve and the pressure regulating/shut-off valve,
the controller configured to:
calculate the open position of the fan air valve that is operatively connected to the precooler having the bypass inlet configured to receive bypass air that bypasses the gas turbine engine core to facilitate the provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, responsive to the pressure regulating/shut-off valve being in the closed position to inhibit the fluid flow through the bleed air inlet of the precooler;
monitor a core compartment temperature of the core compartment with a temperature sensor positioned within the core compartment;
when the pressure regulating/shut-off valve is in the closed position and the core compartment temperature is greater than a target core compartment temperature, move the fan air valve to the first open position; and
when the fan air valve is in the first open position, direct the bypass air through the bypass outlet of the precooler into the core compartment to impinge on the case assembly proximate a turbine section of the core compartment, thereby cooling the core compartment and the case assembly.
2. The gas turbine engine of claim 1 , wherein:
the target core compartment temperature is based on a rotational speed of the gas turbine engine and an ambient air temperature.
3. The gas turbine engine of claim 1 , wherein:
the controller being further configured to operate the fan air valve to inhibit the provision of bypass air to the precooler and the bypass outlet to cease the provision of bypass air to the core compartment, in response to the core compartment temperature becoming less than the target core compartment temperature.
4. The gas turbine engine of claim 1 , wherein
the bleed air conduit includes:
a first bleed air line having a first valve configured to provide low pressure bleed air from a low pressure stage of the compressor section of the gas turbine engine core;
a second bleed air line having a second valve configured to provide high pressure bleed air from a high pressure stage disposed downstream of the low pressure stage of the compressor section; and
a bleed air union operatively connected to the first bleed air line, the second bleed air line, and the bleed air inlet.
5. The gas turbine engine of claim 1 , wherein:
the controller is configured to move the fan air valve to a second open position to facilitate the provision of bypass air through the fan air valve inlet to the bypass inlet, in response to a bleed air conduit having the pressure regulating/shut-off valve operatively connected to the bleed air inlet of the precooler and a compressor section of the gas turbine engine core.
6. The gas turbine engine of claim 5 , wherein:
the second open position of the fan air valve is based on a temperature of bleed air supplied through the bleed air conduit.
7. The gas turbine engine of claim 1 , wherein:
the target core compartment temperature is based on at least one of a gas turbine engine rotational speed, an altitude, an aircraft mach number, and an ambient air temperature.
8. The gas turbine engine of claim 7 , wherein:
the gas turbine engine rotational speed is based on a rotational speed of at least one of a low pressure shaft and a high pressure shaft.
9. 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 precooler 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 precooler;
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 precooler and a closed position that inhibits the flow of bleed air from the compressor section to the precooler; and
a controller in communication with the fan air valve and the pressure regulating/shut-off valve,
the controller configured to:
estimate a core compartment temperature based on at least one of a gas turbine engine rotational speed and an ambient air temperature;
calculate a target core compartment temperature of the core compartment;
compare the estimated core compartment temperature to the target core compartment temperature, in response to the pressure regulating/shut-off valve operatively connected to the bleed air inlet of the precooler being in the closed position;
calculate a fan air valve position of the fan air valve operatively connected to the precooler based on the target core compartment temperature, in response to the estimated core compartment temperature being greater than the target core compartment temperature;
move the fan air valve to the calculated fan air valve position; and
when the fan air valve is in the calculated fan air valve position, direct bypass air from the precooler into the core compartment, to impinge on the gas turbine engine case assembly proximate a turbine section of the core compartment, to thereby cool the core compartment and the gas turbine engine case assembly, at least until the estimated core compartment temperature satisfies the target core compartment temperature.
10. The gas turbine engine of claim 9 , further comprising:
a temperature sensor positioned to measure the core compartment temperature.
11. The gas turbine engine of claim 9 , wherein:
the controller is further configured to operate the fan air valve to inhibit the provision of bypass air to the precooler and the bypass outlet to cease the provision of bypass air to the core compartment, in response to the estimated core compartment temperature becoming less than the target core compartment temperature.
12. The gas turbine engine of claim 9 , wherein
the bleed air conduit includes:
a first bleed air line having a first valve configured to provide low pressure bleed air from a low pressure stage of the compressor section of the gas turbine engine core;
a second bleed air line having a second valve configured to provide high pressure bleed air from a high pressure stage disposed downstream of the low pressure stage of the compressor section; and
a bleed air union operatively connected to the first bleed air line, the second bleed air line, and the bleed air inlet.
13. The gas turbine engine of claim 9 , wherein:
the controller is configured to close the fan air valve in response to the estimated core compartment temperature becoming less than the target core compartment temperature.