Intercooled cooling air with improved air flow
First Claim
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 tap tapping air from at least one of said more upstream locations 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 said high pressure turbine; and
said cooling compressor including a downstream connection for delivering discharge pressure air to an upstream location in said high pressure turbine and a second tap from an intermediate pressure location within said cooling compressor, and said second tap being connected to a downstream location within said high pressure turbine without further compression.
4 Assignments
0 Petitions
Accused Products
Abstract
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 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. The cooling compressor includes a downstream connection that delivers discharge pressure air to an upstream location in the high pressure turbine and a second tap from an intermediate pressure location within the cooling compressor. The second tap is connected to a downstream location within the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.
22 Citations
19 Claims
-
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 tap tapping air from at least one of said more upstream locations 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 said high pressure turbine; and said cooling compressor including a downstream connection for delivering discharge pressure air to an upstream location in said high pressure turbine and a second tap from an intermediate pressure location within said cooling compressor, and said second tap being connected to a downstream location within said high pressure turbine without further compression. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
-
-
15. An intercooling system for a gas turbine engine comprising:
-
a heat exchanger for cooling air drawn from 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 for communicating the compressed air to a portion of a turbine section; and said cooling compressor including a downstream connection for delivering discharge pressure air to an upstream location in the high pressure turbine and a second tap tapped from an intermediate pressure location within said cooling compressor, and said second tap for being connected to a downstream location within the high pressure turbine without further compression. - View Dependent Claims (16, 17, 18, 19)
-
Specification