Intercooled cooling air using existing heat exchanger

Patent metadata

Field	Value
Publication number	US-2016237908-A1
Application number	US-201514804534-A
Country	US
Kind code	A1
Filing date	Jul 21, 2015
Priority date	Feb 12, 2015
Publication date	Aug 18, 2016
Grant date	—

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, passing 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 heat exchanger also receives air to be delivered to an aircraft cabin. An intercooling system for a gas turbine engine is also disclosed.

First claim

What is claimed is:

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 heat exchanger also receiving air to be delivered to an aircraft cabin.

2 . The gas turbine engine as set forth in claim 1 , wherein a single tap taps air to said heat exchanger for delivery to both said cooling compressor and to said aircraft cabin.

3 . The gas turbine engine as set forth in claim 2 , wherein a mixer is provided downstream of said cooling compressor to receive air from the high pressure compressor to mix with the air downstream of the cooling compressor.

4 . The gas turbine engine as set forth in claim 1 , wherein said cooling compressor includes a centrifugal compressor impeller.

5 . The gas turbine engine as set forth in claim 4 , wherein air temperatures at said downstream most location of said high pressure compressor are greater than or equal to 1350° F.

6 . The gas turbine engine as set forth in claim 5 , wherein said turbine section driving 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 driving an accessory gearbox.

8 . The gas turbine engine as set forth in claim 7 , wherein a gear ratio multiplier is included such that said impeller rotates at a faster speed than said tower shaft.

9 . The gas turbine engine as set forth in claim 8 , wherein an auxiliary fan is positioned upstream of the heat exchanger.

10 . The gas turbine engine as set forth in claim 9 , wherein said auxiliary fan operates at a variable speed.

11 . The gas turbine engine as set forth in claim 1 , wherein air temperatures at said downstream most location of said high pressure compressor are greater than or equal to 1350° F.

12 . The gas turbine engine as set forth in claim 1 , wherein said turbine section driving a bull gear, said bull gear further driving an impeller of said cooling compressor.

13 . The gas turbine engine as set forth in claim 12 , wherein said bull gear also driving an accessory gearbox.

14 . The gas turbine engine as set forth in claim 13 , wherein a gear ratio multiplier is included such that said impeller rotates at a faster speed than said tower shaft.

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 communicating the compressed air to a portion of a turbine section; and said heat exchanger also receiving air to be delivered to an aircraft cabin.

16 . The intercooling system as set forth in claim 15 , wherein a single tap taps air to said heat exchanger for delivery to both said cooling compressor and to said aircraft cabin.

17 . The intercooling system as set forth in claim 16 , wherein a mixer is provided downstream of said cooling compressor to receive air from a high pressure compressor to mix with the air downstream of the cooling compressor.

18 . The intercooling system as set forth in claim 15 , wherein said cooling compressor includes a centrifugal compressor impeller.

19 . The intercooling system as set forth in claim 15 , wherein a bull gear drives an impeller of said cooling compressor.

20 . A gas turbine engine comprising;
a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations, a low pressure compressor providing some of said more upstream locations; a turbine section having at least two turbine rotors, with a first being at a higher pressure than a second; and 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 to said first turbine rotor.

Assignees

• United Technologies Corp

Inventors

• Snape Nathan
• Suciu Gabriel L
• Merry Brian D
• Chandler Jesse M

Classifications

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F02C7/143

  before or between the compressor stages · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F02C7/185

  Cooling means for reducing the temperature of the cooling air or gas · CPC title