# US 9,752,501 B2 · Aero boost—gas turbine energy supplementing systems and efficient inlet cooling and heating, and methods of making and using the same > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,752,501 B2 - Document ID: US9752501B2 - Status: Granted - Kind: B2 - Application number: 14/623,939 - Filed: 2015-02-17 - Published: 2016-06-16 - Granted: 2017-09-05 - Earliest claimed: 2012-10-04 - Assignees: Powerphase LLC - Applicants: PowerPHASE LLC - Inventors: Robert J. Kraft - Web page: https://patentgrep.com/patent/US9752501B2 ## CPC - F02C 7/10: by means of regenerative heat-exchangers - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F02C 3/10: with another turbine driving an output shaft but not driving the compressor - F02C 6/00: Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use - F02C 7/08: Heating air supply before combustion, e.g. by exhaust gases - F02C 7/12: Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) - F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} - H02K 7/1823: {structurally associated with turbines or similar engines} - F01K 23/02: the engine cycles being thermally coupled - Y02E 20/16: Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT] - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - H02K: DYNAMO-ELECTRIC MACHINES (dynamo-electric relays H01H53/00; conversion of DC or AC input power into surge output power {H03K3/53}) - F01K: STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES (gas-turbine or jet-propulsion plants F02; nuclear power plants, engine arrangements therein G21D) - Y02E: REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION ## 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 ### Claim 1 A system for heating an inlet region of a gas turbine engine having a compressor section coupled to a turbine section comprising: a fueled engine; one or more auxiliary compressors mechanically coupled to the fueled engine generating an auxiliary source of compressed air; and, a recuperator having an exhaust input connected to only the fueled engine; wherein the auxiliary source of compressed air from the one or more auxiliary compressors is heated in the recuperator with exhaust heat from the fueled engine and is injected into the inlet region of the gas turbine engine. ### Claim 2 (depends on 1) The system of claim 1, wherein the compressor section comprises at least a low pressure compressor and a high pressure compressor. ### Claim 3 (depends on 2) The system of claim 2, wherein the low pressure compressor is coupled to a low pressure turbine and the high pressure compressor is coupled to a high pressure turbine. ### Claim 4 (depends on 1) The system of claim 1, wherein an inlet to the compressor section is located at the inlet region of the gas turbine engine. ### Claim 5 (depends on 1) The system of claim 1, wherein the recuperator discharges a flow of hot compressed air. ### Claim 6 (depends on 1) The system of claim 1, wherein the heated compressed air from the one or more auxiliary compressors is injected downstream of a high pressure compressor. ### Claim 7 A system for integrating a power augmentation and inlet heating system for a gas turbine engine having a compressor section coupled to a turbine section comprising: the compressor section having an inlet region; an auxiliary source of compressed air; a fueled engine mechanically coupled to one or more auxiliary compressors; and, a recuperator having an exhaust input connected only to the fueled engine for heating the auxiliary source of compressed air from the one or more auxiliary compressors with exhaust heat from the fueled engine; wherein the heated compressed air from the recuperator is injected into the inlet region of the compressor section and into an exit area of the compressor section. ### Claim 8 (depends on 7) The system of claim 7, wherein the compressor comprises at least a low pressure compressor and a high pressure compressor. ### Claim 9 (depends on 8) The system of claim 8, wherein the low pressure compressor is coupled to a low pressure turbine and the high pressure compressor is coupled to a high pressure turbine. ### Claim 10 (depends on 7) The system of claim 7, wherein the inlet region to the compressor section is located at an inlet of the gas turbine engine. ### Claim 11 (depends on 7) The system of claim 7, wherein the recuperator discharges a flow of hot compressed air. ### Claim 12 (depends on 7) The system of claim 7, wherein the heated compressed air from the recuperator is injected into an inlet region of the gas turbine for inlet heating. ### Claim 13 (depends on 12) The system of claim 12, wherein the heated compressed air from the recuperator is injected into the inlet region of the gas turbine through an inlet bleed heat pipe system. ### Claim 14 A system for augmenting power of a multi-shaft gas turbine engine having multiple compressor sections coupled respectively to multiple turbine sections comprising: an inlet region for each of the multiple compressor sections; an auxiliary source of compressed air comprising: a fueled engine mechanically coupled to one or more auxiliary compressors for generating a source of compressed air, the compressed air comprising a first portion and a second portion; and, a recuperator having an exhaust input connected only to the fueled engine for heating the second portion of the compressed air from the auxiliary compressor with exhaust heat from the fueled engine; wherein the first portion of the compressed air is injected into an inlet of a high pressure compressor section of the multiple compressor sections and the second portion of the compressed air is injected into an exit area of the high pressure compressor section. ### Claim 15 (depends on 14) The system of claim 14, wherein the multiple compressor sections comprises at least a low pressure compressor section and the high pressure compressor section. ### Claim 16 (depends on 15) The system of claim 15, wherein the low pressure compressor section is coupled to a low pressure turbine and the high pressure compressor section is coupled to a high pressure turbine. ### Claim 17 (depends on 14) The system of claim 14, wherein the inlet regions for the multiple compressor sections are located at an inlet of the gas turbine engine. ### Claim 18 (depends on 14) The system of claim 14, wherein the heated compressed air from the auxiliary source of compressed air is injected into the inlet of the gas turbine for inlet heating. ### Claim 19 A system for integrating a power augmentation and inlet heating system for a multi-shaft gas turbine engine having multiple compressor sections coupled respectively to multiple turbine sections comprising: an inlet region for each compressor section of the multiple compressor sections; an auxiliary source of compressed air comprising: a fueled engine; one or more auxiliary compressors mechanically coupled to the fueled engine; and, a recuperator having an exhaust input connected only to the fueled engine for heating a second portion of compressed air from the one or more auxiliary compressors with heat from the fueled engine; and, a system for cooling a first portion of compressed air from the one or more auxiliary compressors; wherein heated compressed air is injected into the inlet region of one or more of the compressor sections of the multiple compressor sections, the first portion of compressed air is injected into an exit area of at least one of the multiple compressor sections of the multi-shaft gas turbine engine and injecting the second portion of compressed air into the inlet region of at least one of the multiple compressor sections. ### Claim 20 (depends on 19) The system of claim 19, wherein the multiple compressor sections comprises at least a low pressure compressor and a high pressure compressor. ### Claim 21 (depends on 20) The system of claim 20, wherein the low pressure compressor is coupled to a low pressure turbine and the high pressure compressor is coupled to a high pressure turbine. ### Claim 22 (depends on 19) The system of claim 19, wherein the inlet region of the one or more compressor sections is located at an inlet of the multi-shaft gas turbine engine. ### Claim 23 (depends on 22) The system of claim 22, wherein the heated compressed air from the auxiliary source of compressed air is injected into the inlet of the multi-shaft gas turbine engine through an inlet bleed heat pipe. ### Claim 24 A system for integrating a power augmentation and inlet heating system for a gas turbine engine having a compressor section coupled to a turbine section comprising: an inlet region for the compressor section; an auxiliary source of compressed air comprising: a fueled engine; one or more auxiliary compressors mechanically coupled to the fueled engine; and, a recuperator having an exhaust input coupled to the fueled engine for heating at least a portion of the compressed air generated by the one or more auxiliary compressors with exhaust heat from the fueled engine; and, one or more conduits of an inlet bleed heat system for injecting the heated compressed air into an exit area of the compressor section while not impacting a bleed functionality of the inlet bleed heat system.