# US 7,607,307 B2 · Methods and apparatus for controlling cooling air temperature in 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 7,607,307 B2 - Document ID: US7607307B2 - Status: Granted - Kind: B2 - Application number: 11/327,623 - Filed: 2006-01-06 - Published: 2007-07-12 - Granted: 2009-10-27 - Earliest claimed: 2006-01-06 - Assignees: General Electric Company - Inventors: Robert Frederick Bergholz - Web page: https://patentgrep.com/patent/US7607307B2 ## CPC - F01D 5/082: {on the side of the rotor disc} - F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)} - F02C 7/185: {Cooling means for reducing the temperature of the cooling air or gas} - F05D 2260/232: characterized by the cooling medium - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A cooling system for a gas turbine engine including a compressor, a combustor and a high-pressure turbine, coupled together in serial flow arrangement. The cooling system includes a storage tank, a working fluid stored within the storage tank, and a manifold coupled to the channel that supplies cooling air to the high pressure turbine. The working fluid is discharged from the manifold into the turbine cooling air supply channel, thereby reducing the temperature of the compressed cooling airflow channeled to the high pressure turbine. ## Claims ### Claim 1 A cooling system for a gas turbine engine including a compressor, a combustor, a high-pressure turbine, and a high-pressure turbine cooling air supply duct, coupled together in serial flow arrangement, said cooling system comprising: a storage tank; a working fluid stored within the storage tank; a manifold coupled in flow communication between the combustor and the high-pressure turbine, said cooling system configured to discharge the working fluid from said storage tank into the high-pressure turbine cooling air supply duct using said manifold to facilitate reducing an operating temperature of the compressed airflow channeled to the high pressure turbine and a return conduit comprising a first end coupled to an outlet of said manifold and a second end coupled to an inlet of said storage tank, said return conduit configured to channel an unused portion of said working fluid to the inlet of said storage tank. ### Claim 2 (depends on 1) A cooling system in accordance with claim 1 wherein said storage tank, said manifold, and the gas turbine engine are installed on an aircraft. ### Claim 3 (depends on 1) A cooling system in accordance with claim 1 wherein said manifold comprises a toroidal manifold. ### Claim 4 (depends on 1) A cooling system in accordance with claim 1 wherein the gas turbine engine includes an off-take duct and a high-pressure turbine inducer, said manifold positioned proximate to an entrance of the off-take duct feeding the high-pressure turbine inducer. ### Claim 5 (depends on 1) A cooling system in accordance with claim 1 further comprising a pump coupled in flow communication with said storage tank and said manifold, said pump selectively energized to channel the working fluid from said storage tank into said manifold. ### Claim 6 (depends on 5) A cooling system in accordance with claim 5 wherein said storage tank and said pump are each placed in a selected core cowl space proximate to a plane of a high-pressure turbine vane inlet to facilitate maintaining the working fluid at a predetermined operational temperature. ### Claim 7 (depends on 1) A cooling system in accordance with claim 1 further comprising a plurality of nozzles coupled to said manifold, said nozzles configured to inject a predetermined quantity of working fluid into the airflow stream entering the high-pressure turbine. ### Claim 8 A gas turbine engine assembly comprising: a core gas turbine engine comprising a compressor; a combustor downstream from said compressor; and a high-pressure turbine downstream from said combustor; and a cooling system comprising a storage tank; a working fluid stored within said storage tank; a manifold coupled to a duct that supplies cooling air to the high pressure turbine, discharging the fluid into the turbine cooling air supply duct, and thereby reducing the temperature of the compressed cooling airflow channeled to the high pressure turbine; and a return conduit comprising a first end coupled to an outlet of said manifold and a second end coupled to an inlet of said storage tank, said return conduit configured to channel an unused portion of said working fluid to the inlet of said storage tank. ### Claim 9 (depends on 8) A gas turbine engine assembly in accordance with claim 8 wherein said cooling system and said core gas turbine engine are installed on an aircraft. ### Claim 10 (depends on 8) A gas turbine engine assembly in accordance with claim 8 wherein said manifold comprises a toroidal manifold. ### Claim 11 (depends on 8) A gas turbine engine assembly in accordance with claim 8 wherein said core gas turbine engine further comprises an off-take duct and a high-pressure turbine inducer, said manifold positioned proximate to an entrance of said off-take duct feeding said high-pressure turbine inducer. ### Claim 12 (depends on 8) A gas turbine engine assembly in accordance with claim 8 further comprising a pump coupled in flow communication with said storage tank and said manifold, said pump selectively energized to channel the working fluid from said storage tank into said manifold. ### Claim 13 (depends on 11) A gas turbine engine assembly in accordance with claim 11 wherein said storage tank and said pump are each placed in a selected core cowl space proximate to a plane of a high-pressure turbine vane inlet to facilitate maintaining the working fluid at a predetermined operational temperature. ### Claim 14 (depends on 8) A gas turbine engine assembly in accordance with claim 8 further comprising a plurality of nozzles coupled to said manifold, said nozzles configured to inject a predetermined quantity of working fluid into the airflow stream entering said high-pressure turbine.