# US 10,309,310 B2 · Two spool gas generator with improved air porting > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,309,310 B2 - Document ID: US10309310B2 - Status: Granted - Kind: B2 - Application number: 14/758,277 - Filed: 2013-05-10 - Published: 2015-11-26 - Granted: 2019-06-04 - Earliest claimed: 2013-01-10 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Gabriel L. Suciu; Jesse M. Chandler; Wesley K. Lord - Web page: https://patentgrep.com/patent/US10309310B2 ## CPC - F02C 7/185: {Cooling means for reducing the temperature of the cooling air or gas} - F02C 3/13: having variable working fluid interconnections between turbines or compressors or stages of different rotors {(controlling flow ratio between different flows of multi-flow jet-propulsion plant, e.g. ducted fan F02K3/075)} - F02C 3/145: {the combustion chamber being in the reverse flow-type} - F02C 6/04: Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output (F02C6/18 takes precedence {; for a fluidised-bed combustor F02C3/205}) - F02C 6/08: the gas being bled from the gas-turbine compressor - F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} - F02K 3/00: Plants including a gas turbine driving a compressor or a ducted fan - F02K 3/02: in which part of the working fluid by-passes the turbine and combustion chamber - F05D 2220/3217: for the first stage of a compressor or a low pressure compressor - F05D 2220/3218: for an intermediate stage of a compressor - 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 ## Abstract In a featured embodiment, a gas turbine engine has a first compressor rotor driven by a first turbine rotor, and a second compressor rotor driven by a second turbine rotor. The second compressor rotor is upstream of the first compressor rotor and the first turbine rotor is upstream of the second turbine rotor. An air mixing system taps air from a location upstream of the first compressor rotor for delivery to an environmental control system. The air mixing system receives air from a first air source and a second air source. The first air source includes air at a first pressure upstream of the first compressor rotor. The second air source includes air at a lower second pressure. At least one valve controls a mixture of air from the first and second sources to achieve a predetermined pressure for the environmental control system. ## Claims ### Claim 1 A gas turbine engine comprising: a first compressor rotor driven by a first turbine rotor, and a second compressor rotor driven by a second turbine rotor, with said second compressor rotor being upstream of the first compressor rotor and said first turbine rotor being upstream of said second turbine rotor; an air mixing system for tapping air from a location upstream of said first compressor rotor and for delivery to an environmental control system, the air mixing system receiving air from a first air source and a second air source, the first air source including air at a first pressure upstream of said first compressor rotor, and the second air source including air at a lower second pressure upstream of said first air source, a first valve and a second valve, with said first valve controlling delivery of air from said first air source into a mixing box, and said second valve controlling delivery of air from said second air source into said mixing box; said second valve controlling delivery of air at a lower pressure than said first valve such that the air from the second valve is delivered into the mixing box at a lower pressure than the air from the first valve; wherein said first and second valves are controllable to achieve a predetermined pressure of a mixture of air from said first and second sources within said mixing box; and an outlet of said mixing box for delivery of said mixture of air to said environmental control system; wherein said second air source communicating into a first line and a second line, with the first line including the second valve controlling the amount of air from said second air source reaching said mixing box, and the second line including a third valve controlling the amount of air passing to a second air source outlet downstream of said first compressor rotor. ### Claim 2 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said second compressor rotor having a first overall pressure ratio, and said first compressor rotor having a second overall pressure ratio, with a ratio of said first overall pressure ratio to said second overall pressure ratio being greater than or equal to about 2.0, wherein said ratio of said first overall pressure ratio to said second overall pressure ratio being less than or equal to about 8.0. ### Claim 3 (depends on 2) The gas turbine engine as set forth in claim 2, wherein said ratio of said first overall pressure ratio to said second overall pressure ratio is greater than or equal to about 3.0. ### Claim 4 (depends on 3) The gas turbine engine as set forth in claim 3, wherein said ratio of said first overall pressure ratio to said second overall pressure ratio is greater than or equal to about 3.5. ### Claim 5 (depends on 1) The gas turbine engine as set forth in claim 1, wherein a propulsor turbine is positioned downstream of the second turbine rotor. ### Claim 6 (depends on 5) The gas turbine engine as set forth in claim 5, wherein the propulsor turbine drives a propeller. ### Claim 7 (depends on 5) The gas turbine engine as set forth in claim 5, wherein the propulsor turbine drives a fan at an upstream end of the engine. ### Claim 8 (depends on 7) The gas turbine engine as set forth in claim 7, wherein an axially upstream position is defined by said fan, and said propulsor turbine being positioned between said fan and said first and second turbine rotors, and said first and second compressor rotors being positioned further into said engine relative to said first and second turbine rotors. ### Claim 9 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said second air source is positioned to be upstream of said second compressor rotor. ### Claim 10 (depends on 9) The gas turbine engine as set forth in claim 9, wherein said second air source delivers air across a heat exchanger, and includes a particle separator for separating impurities. ### Claim 11 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said second air source communicates through a conduit to a connection leading into said mixing box, and said second air source further selectively communicating with the second air source outlet which is downstream of said first compressor rotor. ### Claim 12 (depends on 11) The gas turbine engine as set forth in claim 11, wherein said second air source communicates from the conduit through a port leading into said mixing box and, alternatively, flowing to said second air source outlet downstream of said first compressor rotor. ### Claim 13 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said first and second valves are associated with a supply port from said first air source, and also on said second air source. ### Claim 14 (depends on 1) The gas turbine engine as set forth in claim 1, wherein said location upstream of said first compressor rotor is in an intermediate case intermediate said first and second compressor rotors. ### Claim 15 A gas turbine engine comprising: a first shaft connecting a first compressor rotor to be driven by a first turbine rotor, and a second shaft connecting a second compressor rotor to be driven by a second turbine rotor, with said second compressor rotor being upstream of the first compressor rotor and said first turbine rotor being upstream of said second turbine rotor; and an air mixing system for tapping air from a location upstream of said first compressor rotor and for delivery to an environmental control system, the air mixing system receiving air from a first air source and a second air source, the first air source including air at a first pressure upstream of said first compressor rotor, and the second air source including air at a lower second pressure upstream of said first air source; a propulsor turbine outwardly connected to drive one of a fan or propeller through a third shaft; said first shaft surrounding said second shaft, but said first and second shafts not surrounding said third shaft; said second compressor rotor having a first overall pressure ratio, and said first compressor rotor having a second overall pressure ratio, with a ratio of said first overall pressure ratio to said second overall pressure ratio being greater than or equal to about 2.0 and less than 8.0; said second air source is positioned to be upstream of said second compressor rotor; and a first valve and a second valve, with said first valve controlling delivery of air from said first air source into a mixing box, and said second valve controlling delivery of air from said second air source into said mixing box; said second valve controlling delivery of air at a lower pressure than said first valve such that the air from the second valve is delivered into the mixing box at a lower pressure than the air from the first valve; wherein said first and second valves are controllable to achieve a predetermined pressure for a mixture of air from said first and second sources within said mixing box; and an outlet of said mixing box for delivery of said mixture of air to said environmental control system; wherein said second air source communicating into a first line and a second line, with the first line including the second valve controlling the amount of air from said second air source reaching said mixing box, and the second line including a third valve controlling the amount of air passing to a second air source outlet downstream of said first compressor rotor. ### Claim 16 (depends on 15) The gas turbine engine as set forth in claim 15, wherein said second air source communicates through a conduit to a connection leading into said mixing box, and said second air source further selectively communicating with the second air source outlet which is downstream of said first compressor rotor. ### Claim 17 (depends on 15) The gas turbine engine as set forth in claim 15, wherein said first air source is in an intermediate case intermediate said first and second compressor rotors.