# US 7,464,533 B2 · Apparatus for operating gas turbine engines > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 7,464,533 B2 - Document ID: US7464533B2 - Status: Granted - Kind: B2 - Application number: 11/143,246 - Filed: 2005-06-02 - Published: 2008-10-09 - Granted: 2008-12-16 - Earliest claimed: 2003-01-28 - Assignees: General Electric Company - Inventors: Gary C. Wollenweber - Web page: https://patentgrep.com/patent/US7464533B2 ## CPC - F02C 6/08: the gas being bled from the gas-turbine compressor - F02C 6/02: Plural gas-turbine plants having a common power output - F02C 6/06: providing compressed gas (F02C6/10 takes precedence) - F02C 7/277: the starter being a {separate} turbine - F02C 7/32: Arrangement, mounting, or driving, of auxiliaries - F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} - F02C 9/28: Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed (F02C9/30 - F02C9/38, F02C9/44 take precedence) - F02C 9/42: specially adapted for the control of two or more plants simultaneously - F02C 9/50: with control of working fluid flow - F02K 3/06: with front fan - F02K 3/12: characterised by having more than one gas turbine - F05D 2220/50: for auxiliary power units (APU's) - F05D 2270/13: to control two or more engines simultaneously - Y10T 29/4932: Turbomachine making - 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) - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract A method facilitates assembling a gas turbine engine assembly. The method comprises providing at least one propelling gas turbine engine that includes a core engine including at least one turbine, coupling an auxiliary engine to the propelling gas turbine engine such that during operation of the propelling gas turbine engine, such that at least a portion of the airflow entering the propelling gas turbine engine is extracted from the propelling gas and channeled to the auxiliary engine for generating power, and coupling a modulating valve in flow communication to the propelling gas turbine engine to control the flow of airflow from the propelling gas turbine engine to the auxiliary engine, wherein the modulating valve is selectively operable to control an extraction point of airflow from the propelling gas turbine engine. ## Claims ### Claim 1 A gas turbine engine assembly comprising: at least one propelling gas turbine engine comprising a fan, a core engine downstream from the fan, and a plurality of extraction points; a modulating valve coupled in flow communication to said at least one propelling gas turbine engine; and an auxiliary engine used for generating electrical power, said auxiliary engine comprising at least one turbine and an inlet, said inlet coupled in flow communication with said modulating valve, such that a portion of airflow entering said at least one propelling engine is extracted for use by said auxiliary engine and such that said modulating valve controls the flow of airflow from said at least one propelling engine to said auxiliary engine, said modulating valve is selectively operable to extract and mix airflow from at least two of said plurality of extraction points. ### Claim 2 (depends on 1) A gas turbine engine assembly in accordance with claim 1 wherein said modulating valve is coupled to a first of said plurality of extraction points for selectively controlling a flow of high-pressure airflow to said auxiliary engine and to a second of said plurality of extraction points for selectively controlling a flow of low-pressure airflow to said auxiliary engine. ### Claim 3 (depends on 1) A gas turbine engine assembly in accordance with claim 1 wherein said modulating valve is selectively operable to facilitate controlling at least one of a pressure, a temperature, and a density of airflow channeled to said auxiliary engine. ### Claim 4 (depends on 1) A gas turbine engine assembly in accordance with claim 1 wherein said modulating valve is selectively operable to facilitate increasing at least one of a stall margin and an operability of said propelling gas turbine engine. ### Claim 5 (depends on 1) A gas turbine engine assembly in accordance with claim 1 wherein said modulating valve is selectively operable to facilitate increasing an operating efficiency of said propelling gas turbine engine. ### Claim 6 (depends on 1) A gas turbine engine assembly in accordance with claim 1 wherein said modulating valve is coupled to at least two of said extraction points such that during at least some engine operations, said auxiliary engine receives airflow from at least one extrication point coupled in flow communication with a high-pressure source of air and from an extrication point coupled in flow communication with a low-pressure source of air. ### Claim 7 (depends on 1) A gas turbine engine assembly in accordance with claim 1 wherein said modulating valve facilitates said auxiliary engine generating increased shaft horsepower during operation of said gas turbine engine assembly. ### Claim 8 An aircraft gas turbine engine assembly, said assembly comprising; at least one propelling gas turbine engine comprising a core engine and an exhaust, said core engine comprising at least one turbine, said at least one propelling gas turbine engine for generating thrust for the aircraft; a modulating valve coupled in flow communication with at least one of a plurality of airflow extraction points defined within said at least one propelling gas turbine engine, said modulating valve is selectively operable to extract and mix airflow from at least two of said plurality of airflow extraction points; and at least one auxiliary engine comprising an inlet, at least one turbine, and an exhaust, said inlet coupled in flow communication with said modulating valve such that a portion of airflow flowing through said propelling engine is selectively extractable from said at least one propelling engine and is channeled to said auxiliary engine for generating electrical power. ### Claim 9 (depends on 8) An aircraft gas turbine engine assembly in accordance with claim 8 wherein said modulating valve is selectively operable to facilitate controlling at least one of a pressure, a temperature, and a density of airflow extracted from said at least one propelling engine and channeled to said at least one auxiliary engine. ### Claim 10 (depends on 8) An aircraft gas turbine engine assembly in accordance with claim 8 wherein said at least one auxiliary engine is operable independently of said at least one propelling gas turbine engine. ### Claim 11 (depends on 8) An aircraft gas turbine engine assembly in accordance with claim 8 wherein said modulating valve facilitates said auxiliary engine generating increased shaft horsepower during operation of said gas turbine engine assembly. ### Claim 12 (depends on 8) An aircraft gas turbine engine assembly in accordance with claim 8 wherein operation of said modulating valve facilitates enhancing at least one of a stall margin and the operability of said at least one propelling engine. ### Claim 13 (depends on 8) An aircraft gas turbine engine assembly in accordance with claim 8 wherein operation of said modulating valve facilitates improving operating performance of said at least one propelling engine, said modulating valve is coupled to at least two of said airflow extraction points such that during at least some engine operations, said auxiliary engine receives airflow from at least one extrication point coupled in flow communication with a high-pressure source of air and from at least one extrication point coupled in flow communication with a low-pressure source of air.