System and method for selectively modulating the flow of bleed air used for high pressure turbine stage cooling in a power turbine engine
A method for selectively modulating bleed air used for cooling a downstream turbine section in a gas turbine engine. The method including: measuring an engine and/or aircraft performance parameter by an engine sensor device; comparing the engine and/or aircraft performance parameter to a performance threshold; determining a bleed trigger condition, if the engine and/or aircraft performance parameter crosses the performance threshold; determining a non-cooling condition, if the engine and/or aircraft performance parameter is below the performance threshold; actuating a flow control valve to an open position, in response to the bleed trigger condition, so that bleed air is extracted from the compressor section and flowed to the downstream turbine section; and terminating, in response to the non-cooling condition, the flow of the bleed air to the downstream turbine section of the engine by actuating the flow control valve to a closed position.
1. A method for selectively modulating bleed air used for cooling a downstream turbine section in a gas turbine engine; the gas turbine engine comprising a compressor section configured to produce a flow of bleed air, a combustion chamber, and the downstream turbine section configured to receive at least a portion of the bleed air; the method comprising:
measuring an engine performance parameter and/or aircraft performance parameter by an engine sensor device and/or an aircraft sensor device;
comparing, by a computer processor in an engine control unit, the engine performance parameter and/or the aircraft performance parameter to a performance threshold;
determining a bleed trigger condition, when the engine performance parameter and/or the aircraft performance parameter crosses the performance threshold;
determining a non-cooling condition, when the engine performance parameter and/or aircraft performance parameter is below the performance threshold;
actuating a flow control valve to an open position, in response to the bleed trigger condition, so that the bleed air is extracted from the compressor section and flowed to the downstream turbine section;
terminating, in response to the non-cooling condition, the flow of the bleed air to the downstream turbine section of the engine by actuating the flow control valve to a closed position;
identifying, by the computer processor, a cooling profile for the downstream turbine section based on the engine performance parameter and/or aircraft performance parameter;
wherein the cooling profile determines an amount of bleed air extracted from the compressor section and supplied to the downstream turbine section in the actuating a flow control valve step; the cooling profile includes the flow control valve actuated to a fully open position to provide a maximum amount of bleed air to the downstream turbine section; the cooling profile includes the flow control valve to be in the first partially open position for a first amount of time and the second partially open position for a second amount of time, wherein the first amount of time and second amount of time are substantially equal.
2. The system according to claim 1 , wherein the aircraft performance parameter comprises at least one of the following: airspeed, outside air temperature (OAT), altitude and rotor speed (Nr).
3. The system according to claim 1 , wherein the engine performance parameter comprises at least one of the following: shaft horsepower, measured gas temperature (MGT), torque output, gas generator shaft speed (N 1 ), output shaft speed (N 2 ).
4. The method according to claim 1 , wherein the downstream turbine section comprises a high pressure turbine section and a low pressure turbine section,
wherein when the non-cooling condition is determined, the flow of bleed air is terminated only to the high pressure turbine section.