Compressed air bleed supply for buffer system
A method of designing a buffer system for a gas turbine engine according to an example of the present disclosure includes, among other things, configuring a heat exchanger to define a first inlet and a first outlet fluidly coupled to each other and a second inlet and a second outlet fluidly coupled to each other, configuring the first inlet to receive air from first and second air sources that are selectively fluidly coupled to the first inlet, configuring the second inlet to receive air from a third air source fluidly that is coupled to the second inlet, and configuring the first outlet to provide cooled pressurized air to multiple fluid-supplied areas that are located remotely from one another and that are fluidly coupled to the first outlet, the multiple fluid-supplied areas including a bearing compartment of a gas turbine engine.
1. A method of designing a buffer system for a gas turbine engine, the method comprising the steps of:
configuring a heat exchanger to define a first inlet and a first outlet fluidly coupled to each other and a second inlet and a second outlet fluidly coupled to each other;
configuring the first inlet to receive air from first and second air sources that are selectively fluidly coupled to the first inlet;
configuring the second inlet to receive air from a third air source that is fluidly coupled to the second inlet;
configuring the first outlet to provide cooled pressurized air to multiple fluid-supplied areas that are located remotely from one another and that are fluidly coupled to the first outlet, the multiple fluid-supplied areas including a bearing compartment of the gas turbine engine;
configuring a valve to be fluidly coupled to the first and second inlets;
designing the valve to regulate air from the first and second air sources, wherein the first and second air sources have different pressures;
designing the first, second and third air sources to be different than one another;
configuring the first air source to provide air at a first pressure and temperature state;
configuring the second air source to provide air at a higher pressure and temperature state than the first air source;
configuring a compressor section to compress air and deliver the air into a combustion section, the compressor section including first and second compressors;
configuring the first compressor to provide the third air source; and
configuring the second compressor to provide the second air source.
2. The method as recited in claim 1 , comprising the steps of:
configuring a mid-stage to provide a flow path between first and second compressors; and
configuring the mid-stage to provide the first air source.
3. The method as recited in claim 1 , wherein the third air source is provided by the compressor section.
4. The method as recited in claim 1 , wherein the step of configuring the compressor section includes arranging the first compressor to be upstream of the second compressor.
5. The method as recited in claim 4 , wherein the step of configuring the compressor section includes arranging the first compressor and the second compressor downstream of a fan.
6. The method as recited in claim 5 , wherein the third air source is provided by the compressor section.
7. The method as recited in claim 6 , wherein a pressure ratio across the fan is less than 1.45.
8. The method as recited in claim 7 , comprising the step of:
configuring a turbine section to drive the compressor section, the turbine section including a fan drive turbine configured to drive the fan.
9. The method as recited in claim 8 , wherein the bearing compartment includes a plurality of bearing compartments.
10. The method as recited in claim 8 , wherein the multiple fluid-supplied areas include one of a vane, a blade and a clearance control device.
11. The method as recited in claim 1 , comprising the steps of:
configuring a mid-stage to provide a flow path between the first and second compressors; and
configuring the mid-stage to provide the first air source.
12. The method as recited in claim 1 , comprising the step of:
designing the multiple fluid-supplied areas to include a component of the gas turbine engine, the component being at least one of a rotor of the second compressor and a shaft of a fan drive turbine driven by the compressor section.
13. The method as recited in claim 12 , wherein the multiple fluid-supplied areas includes the shaft.
14. The method as recited in claim 1 , comprising the step of:
configuring the second outlet to be fluidly coupled to a bypass flow path, the bypass flow path being arranged between core and fan nacelles of the gas turbine engine.
15. The method as recited in claim 14 , comprising the steps of:
configuring a fan to deliver a portion of air into the compressor section, and a portion of air into a bypass duct defining the bypass flow path; and
configuring a turbine section to drive the compressor section, the turbine section including a fan drive turbine configured to drive the fan.