Systems and methods for augmenting gas turbine power output with a pressurized air tank and/or an external compressor

Patent metadata

Field	Value
Publication number	US-10267231-B2
Application number	US-201514819770-A
Country	US
Kind code	B2
Filing date	Aug 6, 2015
Priority date	Aug 6, 2015
Publication date	Apr 23, 2019
Grant date	Apr 23, 2019

Abstract

A system for augmenting gas turbine power output is disclosed. The system may include a gas turbine engine having a compressor, a combustor, and a turbine. The system also may include a pressurized air tank in communication with the gas turbine engine. Moreover, the system may include an external compressor in communication with the pressurized air tank. The external compressor may be configured to supply compressed air to the pressurized air tank, and the pressurized air tank may be configured to supply compressed air to the gas turbine engine.

First claim

That which is claimed:

1. A system for augmenting gas turbine power output, comprising:
a gas turbine engine comprising a compressor, a combustor, and a turbine; a pressurized air tank in communication with the gas turbine engine; and
an external compressor in communication with the pressurized air tank, wherein the external compressor is configured to supply compressed air to the pressurized air tank or the gas turbine engine, and wherein the pressurized air tank is configured to supply compressed air to the gas turbine engine;
a bypass line from the external compressor to the gas turbine engine for bypassing the pressurized air tank, wherein the external compressor is configured to supply compressed air to the gas turbine engine by way of the bypass line; and
one or more flow valves disposed on the bypass line, wherein the one or more flow valves are configured to prevent compressed air from being supplied to the gas turbine engine from the external compressor when compressed air is supplied to the gas turbine engine from the pressurized air tank,
wherein the compressor is in communication with the pressurized air tank via a conduit that bypasses the external compressor, wherein the compressor is configured to supply compressed air directly to the pressurized air tank.

2. The system of claim 1 , wherein the pressurized air tank is in communication with a compressor discharge casing of the compressor.

3. The system of claim 1 , wherein the pressurized air tank is in communication with an inlet of the combustor.

4. The system of claim 1 , wherein the pressurized air tank is in communication with an inlet of the turbine.

5. The system of claim 1 , further comprising a filter house in communication with the compressor and the external compressor.

6. The system of claim 1 , wherein the pressurized air tank or the external compressor are in communication with a compressor discharge casing of the compressor.

7. The system of claim 1 , wherein the pressurized air tank or the external compressor are in communication with an inlet of the combustor.

8. The system of claim 1 , wherein the pressurized air tank or the external compressor are in communication with an inlet of the turbine.

9. The system of claim 1 , further comprising a filter house in communication with the compressor and the external compressor.

10. A system for augmenting gas turbine power output, comprising:
a gas turbine engine comprising a compressor, a combustor, and a turbine;
a pressurized air tank in communication with the gas turbine engine, wherein the compressor is in communication with the pressurized air tank, wherein the compressor is configured to supply compressed air to the pressurized air tank;
an external compressor in communication with the pressurized air tank, wherein the external compressor is configured to supply compressed air to the pressurized air tank;
a bypass line from the external compressor to the gas turbine engine for bypassing the pressurized air tank, wherein the external compressor is configured to supply compressed air to the gas turbine engine by way of the bypass line; and
one or more flow valves disposed on the bypass line, wherein the one or more flow valves are configured to prevent compressed air from being supplied to the gas turbine engine from the external compressor when compressed air is supplied to the gas turbine engine from the pressurized air tank,
wherein the compressor is in communication with the pressurized air tank via a conduit that bypasses the external compressor.

11. The system of claim 10 , wherein the pressurized air tank or the external compressor are in communication with a compressor discharge casing of the compressor.

12. The system of claim 10 , wherein the pressurized air tank or the external compressor are in communication with an inlet of the combustor.

13. The system of claim 10 , wherein the pressurized air tank or the external compressor are in communication with an inlet of the turbine.

14. A method for augmenting gas turbine power output, comprising:
filling, by an external compressor, a pressurized air tank in communication with a gas turbine engine;
filling, by a compressor of the gas turbine engine and via a conduit that bypasses the external compressor, the pressurized air tank; and
supplying, based on short term output demand, compressed air to the gas turbine engine from the pressurized air tank; and
configuring one or more flow valves to prevent compressed air from being supplied to the gas turbine engine from the external compressor when compressed air is supplied to the gas turbine engine from the pressurized air tank.

15. The method of claim 14 , further comprising:
bypassing, based on prolonged output demand, the pressurized air tank; and
supplying compressed air from the external compressor to the gas turbine engine.

16. The method of claim 15 , further comprising supplying compressed air from the pressurized air tank and/or the external compressor to a compressor discharge casing, an inlet of a combustor, an inlet of a turbine, or a combination thereof.

17. The method of claim 14 , further comprising supplying compressed air from the pressurized air tank to a compressor discharge casing, an inlet of a combustor, an inlet of a turbine, or a combination thereof.

Assignees

• Gen Electric

Inventors

• Klosinski Joseph Phillip
• Scipio Alston Ilford
• Ekanayake Sanji

Classifications

• F02C6/16 Primary

  for storing compressed air · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F02C6/06

  providing compressed gas (F02C6/10 takes precedence) · CPC title

• Y02E60/15

  Cross-Sectional Technologies · mapped topic

• Y02E60/16

  Mechanical energy storage, e.g. flywheels or pressurised fluids · CPC title