Combined Drive for Cooling Air Using Cooing Compressor and Aircraft Air Supply Pump
A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations 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 second tap taps air from the compressor section, passes the air across a cabin air pump, and delivers air from the cabin air pump for use on an aircraft receiving the gas turbine engine. The cooling compressor including a rotor, and the cabin air pump including a rotor, and a drive driven with the turbine section in turn drives both the cooling compressor rotor and the cabin air supply rotor. A combined intercooling system and cabin air supply system is also disclosed.
1 . A gas turbine engine comprising:
a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations;
a turbine section having a high pressure turbine;
a first tap tapping air from at least one of the more upstream locations in the compressor section, passing the tapped air through a heat exchanger and then to a cooling compressor, the cooling compressor compressing air downstream of the heat exchanger, and delivering air into the high pressure turbine;
a second tap tapping air from said compressor section, passing said air across a cabin air pump, and delivering air from said cabin air pump for use on an aircraft receiving the gas turbine engine; and
the cooling compressor including a rotor, and said cabin air pump including a rotor, and a drive driven with said turbine section to in turn drive both said cooling compressor rotor and said cabin air supply rotor.
2 . The gas turbine engine as set forth in claim 1 , wherein the cooling compressor rotor is a centrifugal compressor impeller.
3 . The gas turbine engine as set forth in claim 2 , wherein air temperatures at the downstream discharge of the high pressure compressor are greater than or equal to 1350° F.
4 . The gas turbine engine as set forth in claim 3 , wherein the turbine section driving a bull gear, the bull gear further driving the impeller of the cooling compressor.
5 . The gas turbine engine as set forth in claim 1 , wherein said second tap also tapping air from at least one of the more upstream locations in the compressor section.
6 . The gas turbine engine as set forth in claim 1 wherein said turbine section driving a drive shaft which drives a drive gear for said cooling compressor rotor, and said drive gear for said cooling compressor rotor driving a drive gear for said cabin air supply rotor.
7 . The gas turbine engine as set forth in claim 6 , wherein the turbine section driving a bull gear, the bull gear further driving the rotor of the cooling compressor.
8 . The gas turbine engine as set forth in claim 6 , wherein an idler gear driven by said drive shaft to in turn drive said drive gear for said cooling compressor.
9 . The gas turbine engine as set forth in claim 1 , wherein air temperatures at the downstream discharge of the high pressure compressor are greater than or equal to 1350° F.
10 . The gas turbine engine as set forth in claim 1 , wherein the turbine section driving a bull gear, the bull gear further driving the rotor of the cooling compressor.
11 . A combined intercooling system and cabin air supply system comprising:
a first tap tapping air, passing the tapped air through a heat exchanger and then to a cooling compressor, the cooling compressor compressing air downstream of the heat exchanger, and delivering air to a use;
a second tap tapping air and passing said air across a cabin air pump, to be delivered for use on an aircraft receiving the system; and
the cooling compressor including a rotor, and said cabin air pump including a rotor, and a drive driving both said cooling compressor rotor and said cabin air supply rotor.
12 . The combined intercooling system and cabin air supply system as set forth in claim 11 , wherein the cooling compressor rotor is a centrifugal compressor impeller.
13 . The combined intercooling system and cabin air supply system as set forth in claim 12 , wherein a bull gear drives the cooling compressor rotor.
14 . The combined intercooling system and cabin air supply system as set forth in claim 11 , wherein a bull gear drives the cooling compressor rotor.
15 . The combined intercooling system and cabin air supply system as set forth in claim 11 , wherein a drive shaft drives a drive gear for said cooling compressor rotor, and said drive gear for said cooling compressor rotor driving a drive gear for said cabin air supply rotor.
16 . The combined intercooling system and cabin air supply system as set forth in claim 15 , wherein an idler gear is driven by said drive shaft to in turn drive said drive gear for said cooing compressor.
17 . The combined intercooling system and cabin air supply system as set forth in claim 16 , wherein a bull gear drives the cooling compressor rotor.
18 . The combined intercooling system and cabin air supply system as set forth in claim 15 , wherein a bull gear drives the cooling compressor rotor.
19 . The combined intercooling system and cabin air supply system as set forth in claim 18 , wherein an idler is gear driven by said drive to in turn drive said drive gear for said cooling compressor.
20 . The combined intercooling system and cabin air supply system as set forth in claim 19 , wherein the turbine section drives a bull gear, the bull gear further driving the cooling compressor rotor.