SYSTEMS AND METHODS FOR CONTROLLING AN INLET AIR TEMPERATURE OF AN INTERCOOLED GAS TURBINE ENGINE

• US 20160237904A1
• Filed: 02/13/2015
• Published: 08/18/2016
• Est. Priority Date: 02/13/2015
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Harris, Joseph, Scarboro, Paul Roberts
• Application Number:
  US14/622,043
• Publication Number:
  US 20160237904A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F02C 7/143 before or between the compressor stages
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F02C 9/18 by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages F02C3/113 takes precedence
• CPC Class Codes: F04D 19/026 with a plurality of shafts rotating at different speeds F04D19/022 takes precedence
• CPC Class Codes: F04D 29/5826 Cooling at least part of the working fluid in a heat exchanger
• CPC Class Codes: F05D 2260/211 by intercooling, e.g. during a compression cycle
• CPC Class Codes: F05D 2270/303 Temperature

Abstract

The present application and the resultant patent provide an intercooled gas turbine engine. The intercooled gas turbine engine may include a low pressure compressor configured to produce a compressed flow of air, an intercooler, a low pressure compressor configured to produce a compressed flow of air, a high pressure compressor, a second air line positioned between the intercooler and the high pressure compressor and configured to direct the first portion of the compressed flow of air toward the high pressure compressor, and a bypass air line positioned between the low pressure compressor and the high pressure compressor and configured to direct a second portion of the compressed flow of air to the second air line. A related method of controlling a temperature of an incoming flow of air supplied to a core engine of an intercooled gas turbine engine also is provided.

Claims

1. An intercooled gas turbine engine, comprising:

a low pressure compressor configured to produce a compressed flow of air;

an intercooler;

a first air line positioned between the low pressure compressor and the intercooler and configured to direct a first portion of the compressed flow of air to the intercooler;

a high pressure compressor;

a second air line positioned between the intercooler and the high pressure compressor and configured to direct the first portion of the compressed flow of air toward the high pressure compressor; and

a bypass air line positioned between the low pressure compressor and the high pressure compressor and configured to direct a second portion of the compressed flow of air to the second air line.

2. The intercooled gas turbine engine of claim 1, wherein the bypass air line extends from an air outlet of the low pressure compressor to an intermediate portion of the second air line.

3. The intercooled gas turbine engine of claim 1, wherein the bypass air line extends from an intermediate portion of the first air line to an intermediate portion of the second air line.

4. The intercooled gas turbine engine of claim 1, further comprising a valve positioned on or along the bypass air line and configured to control a volumetric flow rate of the second portion of the compressed flow of air therethrough.

5. The intercooled gas turbine engine of claim 4, wherein the valve is selectively adjustable between an open position and a closed position to provide variable control of the volumetric flow rate of the second portion of the compressed flow of air.

6. The intercooled gas turbine engine of claim 4, further comprising a fluid mixer positioned at or downstream of an intersection of the bypass air line and the second air line and configured to mix the first portion of the compressed flow of air and the second portion of the compressed flow of air, thereby producing an incoming flow of air supplied to the high pressure turbine.

7. The intercooled gas turbine engine of claim 6, wherein the fluid mixer is spaced apart from an air inlet of the high pressure compressor to ensure a substantially uniform temperature distribution in the incoming flow of air prior to entry into the high pressure compressor.

8. The intercooled gas turbine engine of claim 6, further comprising a temperature sensor positioned downstream of the fluid mixer and configured to measure a temperature of the incoming flow of air.

9. The intercooled gas turbine engine of claim 8, wherein the temperature sensor is spaced apart from the fluid mixer to ensure a substantially uniform temperature distribution in the incoming flow of air prior to measurement of the temperature of the incoming flow of air.

10. The intercooled gas turbine engine of claim 8, wherein the temperature sensor is positioned at an air inlet of the high pressure compressor.

11. The intercooled gas turbine engine of claim 8, further comprising a controller in communication with the valve and the temperature sensor and operable to control the temperature of the incoming flow of air.

12. The intercooled gas turbine engine of claim 11, wherein the controller is operable to adjust a state of the valve based on the temperature of the incoming flow of air measured by the temperature sensor.

13. The intercooled gas turbine engine of claim 12, wherein the controller is operable to adjust the state of the valve to a fully open position, a fully closed position, or one of a plurality of partially open positions, based on the temperature of the incoming flow of air measured by the temperature sensor.

14. The intercooled gas turbine engine of claim 1, further comprising a combustor in communication with the high pressure compressor, and a high pressure turbine in communication with the combustor.

15. A method of controlling a temperature of an incoming flow of air supplied to a core engine of an intercooled gas turbine engine, the method comprising:

producing a compressed flow of air with a low pressure compressor;

directing a first portion of the compressed flow of air to an intercooler for cooling therein;

directing a second portion of the compressed flow of air to bypass the intercooler;

mixing the first portion of the compressed flow of air and the second portion of the compressed flow of air downstream of the intercooler to form the incoming flow of air; and

directing the incoming flow of air to the core engine.

16. The method of claim 15, further comprising measuring the temperature of the incoming flow of air, and adjusting a volumetric flow rate of the second portion of the compressed flow of air based on the temperature of the incoming flow of air.

17. An intercooled gas turbine engine, comprising:

a low pressure compressor configured to produce a compressed flow of air;

an intercooler;

a first air line positioned between the low pressure compressor and the intercooler and configured to direct a first portion of the compressed flow of air to the intercooler;

a high pressure compressor;

a second air line positioned between the intercooler and the high pressure compressor and configured to direct the first portion of the compressed flow of air toward the high pressure compressor;

a bypass air line positioned between the low pressure compressor and the high pressure compressor and configured to direct a second portion of the compressed flow of air to the second air line;

a combustor in communication with the high pressure compressor; and

a high pressure turbine in communication with the combustor.

18. The intercooled gas turbine engine of claim 17, further comprising:

a valve positioned on or along the bypass air line and configured to control a volumetric flow rate of the second portion of the compressed flow of air therethrough; and

a fluid mixer positioned at or downstream of an intersection of the bypass air line and the second air line and configured to mix the first portion of the compressed flow of air and the second portion of the compressed flow of air, thereby producing an incoming flow of air supplied to the high pressure turbine.

19. The intercooled gas turbine engine of claim 18, further comprising:

a temperature sensor positioned downstream of the fluid mixer and configured to measure a temperature of the incoming flow of air; and

a controller in communication with the valve and the temperature sensor and operable to control the temperature of the incoming flow of air.

20. The intercooled gas turbine engine of claim 19, wherein the controller is operable to adjust a state of the valve based on the temperature of the incoming flow of air measured by the temperature sensor.