Aero boost—gas turbine energy supplementing systems and efficient inlet cooling and heating, and methods of making and using the same

• US 9,388,737 B2
• Filed: 10/03/2013
• Issued: 07/12/2016
• Est. Priority Date: 10/04/2012
• Status: Active Grant

• Current Assignee: Powerphase International LLC
• Original Assignee: Powerphase LLC
• Inventors: Kraft, Robert J.
• Primary Examiner(s): Sung, Gerald L
• Application Number:
  US14/419,853
• Publication Number:
  US 20150240713A1
• Time in Patent Office: 1,013 Days
• US Class Current: 1/1
• CPC Class Codes: F01K 23/02 the engine cycles being thermally coupled
• CPC Class Codes: F02C 3/10 with another turbine driving an output shaft but not driving the compressor
• CPC Class Codes: F02C 7/08 Heating air supply before combustion, e.g. by exhaust gases
• CPC Class Codes: F02C 7/12 Cooling of plants of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P
• 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: Y02E 20/16 Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]

Abstract

The invention relates generally to electrical power systems, including generating capacity of a gas turbine, and more specifically to pressurized air injection that is useful for providing additional electrical power during periods of peak electrical power demand from a gas turbine system power plant, as well as to inlet heating to allow increased engine turn down during periods of reduced electrical demand.

Claims

1. A method of efficiently operating a gas turbine energy system, comprising:

(a) providing a coupled gas turbine engine having a compressor section coupled to a turbine section;

(b) providing a booster system fluidly connected to the gas turbine engine, the booster system having a fueled engine coupled to an auxiliary compressor, a cooling system, and a recuperator;

(c) pressurizing ambient air using the auxiliary compressor driven by the fueled engine to produce compressed air, while intercooling the compressed air between compression stages by transferring heat therefrom to the cooling system; and

,

(d) heating the compressed air in the recuperator using exhaust from only the fueled engine and then injecting the compressed air into the combustor.

2. A method of efficiently operating a gas turbine energy system, comprising:

(a) providing a multiple shaft gas turbine engine having in series a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, and a low pressure turbine, wherein the low pressure compressor is coupled to the low pressure turbine, and the high pressure compressor is coupled to the high pressure turbine;

(b) providing a booster system having a fueled engine, an auxiliary compressor and a recuperator;

(c) pressurizing ambient air using the auxiliary compressor driven by the fueled engine to produce compressed air;

(d) heating the compressed air in the recuperator using exhaust from only the fueled engine and then injecting said compressed air into an inlet of said low pressure compressor.

3. A method of efficiently operating a gas turbine energy system, comprising:

(a) providing a gas turbine engine having in series a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, and a low pressure turbine, wherein the low pressure compressor is coupled to the low pressure turbine, and the high pressure compressor is coupled to the high pressure turbine;

(b) providing a booster system having a fueled engine, an auxiliary compressor, a cooling system, and a recuperator;

(c) pressurizing ambient air using the auxiliary compressor driven by the fueled engine to produce compressed air, while intercooling the compressed air between compression stages by transferring heat therefrom to the cooling system;

(d) injecting a first portion of said compressed air into an inlet of said high pressure compressor, and heating a second portion of said compressed air in the recuperator using exhaust from only the fueled engine and then injecting said second portion of compressed air into said combustor.