Intercooled cooling air with auxiliary compressor control
A gas turbine engine comprises a main compressor section having a high pressure compressor, and at least one more upstream compressor. A turbine section has a high pressure turbine. A tap line taps air from at least one of the more upstream compressors in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions. An intercooling system is also disclosed.
1. A gas turbine engine comprising;
a main compressor section having a high pressure compressor, and at least one more upstream compressor;
a turbine section having a high pressure turbine;
a tap line tapping air from at least one of said more upstream compressors in said compressor section, passing said tapped air through a heat exchanger and then to a cooling compressor, said cooling compressor compressing air downstream of said heat exchanger, and delivering air into one of said high pressure compressor and said high pressure turbine;
a bypass valve positioned downstream of said main compressor section, and upstream of said heat exchanger, wherein said bypass valve selectively delivers air directly to said cooling compressor without passing through said heat exchanger under certain conditions; and
a control, which under relatively low power conditions, including idle, is configured to position the bypass valve to bypass the heat exchanger, and, under higher power conditions, including take-off, is configured to flow all air through the heat exchanger.
2. The gas turbine engine as set forth in claim 1 , wherein said bypass valve being positioned on said tap line, and further comprising a separate bypass line connecting said tap line to said cooling compressor without passing through said heat exchanger.
3. The gas turbine engine as set forth in claim 1 , wherein said bypass valve completely bypasses said heat exchanger.
4. The gas turbine engine as set forth in claim 1 , wherein said bypass valve may be modulated to control the volume of air delivered through the heat exchanger.
5. The gas turbine engine as set forth in claim 1 , wherein said cooling compressor includes a centrifugal compressor impeller.
6. The gas turbine engine as set forth in claim 1 , wherein said turbine section drives a bull gear, said bull gear further driving an impeller of said cooling compressor.
7. The gas turbine engine as set forth in claim 6 , wherein said bull gear also drives an accessory gearbox.
8. An intercooling system for a gas turbine engine comprising:
a heat exchanger for cooling air drawn from a tap line at a portion of a main compressor section at a first temperature and pressure for cooling the air to a second temperature cooler than the first temperature;
a cooling compressor compressing air communicated from the heat exchanger to a second pressure greater than the first pressure and communicating the compressed air to a portion of at least one of said main compressor section and a turbine section;
a bypass valve to be positioned downstream of the main compressor section, and upstream of said heat exchanger, wherein said bypass valve selectively delivers air directly to said cooling compressor without passing through said heat exchanger under certain conditions; and
a control, which, under relatively low power conditions, including idle, is configured to position the bypass valve to bypass the heat exchanger, and, under higher power conditions, including take-off, is configured to flow all air through the heat exchanger.
9. The system as set forth in claim 8 , wherein said bypass valve is positioned on said tap line, and further comprising a separate bypass line connecting said tap line to said cooling compressor without passing through said heat exchanger.
10. The system as set forth in claim 8 , wherein said bypass valve completely bypasses said heat exchanger.
11. The system as set forth in claim 8 , wherein said bypass valve may be modulated to control the volume of air delivered through the heat exchanger.
12. The system as set forth in claim 8 , wherein said cooling compressor includes a centrifugal compressor impeller.
13. The system as set forth in claim 8 , wherein a turbine section driving a bull gear, said bull gear further drives an impeller of said cooling compressor.
14. The system as set forth in claim 13 , wherein said bull gear also drives an accessory gearbox.
15. The system engine as set forth in claim 8 , wherein an auxiliary fan is positioned upstream of the heat exchanger.