# US 12,600,481 B1 · Aircraft air system with boost compressor(s) > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,600,481 B1 - Document ID: US12600481B1 - Status: Granted - Kind: B1 - Application number: 19/048,090 - Filed: 2025-02-07 - Granted: 2026-04-14 - Earliest claimed: 2025-02-07 - Assignees: Rtx Corporation - Applicants: RTX Corporation - Inventors: Murat Yazici; Thomas E. Clark - Web page: https://patentgrep.com/patent/US12600481B1 ## CPC - B64D 13/02: the air being pressurised - B64D 13/06: the air being conditioned (pressurising B64D13/02) - F02C 6/08: the gas being bled from the gas-turbine compressor - F02C 7/14: of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F02C 7/32: Arrangement, mounting, or driving, of auxiliaries - B64D 2013/0618: {with arrangements for reducing or managing bleed air, using another air source, e.g. ram air} - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2220/76: an electrical generator - F05D 2240/40: Use of a multiplicity of similar components - F05D 2260/213: by the provision of a heat exchanger within the cooling circuit - F05D 2260/4023: through a friction clutch - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - 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 ## Abstract A system is provided for an aircraft. This aircraft system includes a turbine engine and an air system. The turbine engine includes a flowpath, a compressor section, a combustor section and a turbine section. The flowpath extends through the compressor section, the combustor section and the turbine section from an airflow inlet into the flowpath to a combustion products exhaust from the flowpath. The air system includes an air circuit, a first boost compressor, a second boost compressor and a heat exchanger. A circuit inlet into the air circuit is fluidly coupled to the flowpath upstream of the combustor section. The air circuit projects out from the circuit inlet and extends through the first boost compressor, the second boost compressor and the heat exchanger. ## Claims ### Claim 1 A system for an aircraft, comprising: a turbine engine including a flowpath, a compressor section, a combustor section and a turbine section, the flowpath extending through the compressor section, the combustor section and the turbine section from an airflow inlet into the flowpath to a combustion products exhaust from the flowpath; an air system including an air circuit, a first boost compressor, a second boost compressor and a heat exchanger, a circuit inlet into the air circuit fluidly coupled to the flowpath upstream of the combustor section, and the air circuit projecting out from the circuit inlet and extending through the first boost compressor, the second boost compressor and the heat exchanger; a first electric machine comprising a first electric machine rotor, the first boost compressor comprising a first boost compressor rotor, and the first electric machine rotor mechanically coupled to and configured to drive rotation of the first boost compressor rotor; and a second electric machine comprising a second electric machine rotor, the second boost compressor comprising a second boost compressor rotor, and the second electric machine rotor mechanically coupled to and configured to drive rotation of the second boost compressor rotor. ### Claim 2 (depends on 1) The system of claim 1, further comprising an environmental control system for the aircraft, the air circuit extending from the circuit inlet to an airflow inlet into the environmental control system. ### Claim 3 (depends on 1) The system of claim 1, wherein the turbine engine further includes a first rotating structure and a second rotating structure; the first rotating structure comprises a first bladed rotor in the compressor section or the turbine section, and the first rotating structure is mechanically coupled to and configured to drive rotation of the first boost compressor rotor; and the second rotating structure is rotationally independent of the first rotating structure, the second rotating structure comprises a second bladed rotor in the compressor section or the turbine section, and the second rotating structure is mechanically coupled to and configured to drive rotation of the second boost compressor rotor. ### Claim 4 (depends on 1) The system of claim 1, further comprising a clutch mechanically coupling a rotating structure of the turbine engine to the one of the first boost compressor rotor or the second boost compressor rotor. ### Claim 5 (depends on 1) The system of claim 1, wherein the air system further includes a valve fluidly coupled inline along the air circuit between the circuit inlet and the first boost compressor. ### Claim 6 (depends on 1) The system of claim 1, wherein the air system further includes a valve fluidly coupled inline along the air circuit between the second boost compressor and the heat exchanger. ### Claim 7 (depends on 1) The system of claim 1, wherein the turbine engine further includes a first rotating structure and a second rotating structure that is rotationally independent of the first rotating structure; the first rotating structure comprises a first compressor rotor in the compressor section; the second rotating structure comprises a second compressor rotor in the compressor section, and the second compressor rotor is disposed between the first compressor rotor and a combustor in the combustor section; and the circuit inlet is fluidly coupled to the flowpath downstream of the first compressor rotor. ### Claim 8 (depends on 7) The system of claim 7, wherein the circuit inlet is fluidly coupled to the flowpath along the second compressor rotor. ### Claim 9 (depends on 1) The system of claim 1, further comprising: a ducted propulsor rotor; the turbine engine configured to drive rotation of the ducted propulsor rotor. ### Claim 10 (depends on 1) The system of claim 1, further comprising: an open propulsor rotor; the turbine engine configured to drive rotation of the open propulsor rotor. ### Claim 11 A system for an aircraft, comprising: a turbine engine including a flowpath, a compressor section, a combustor section and a turbine section, the flowpath extending through the compressor section, the combustor section and the turbine section from an airflow inlet into the flowpath to a combustion products exhaust from the flowpath; an air system including an air circuit, a first boost compressor, a second boost compressor and a heat exchanger, a circuit inlet into the air circuit fluidly coupled to the flowpath upstream of the combustor section, and the air circuit projecting out from the circuit inlet and extending through the first boost compressor, the second boost compressor and the heat exchanger; wherein the first boost compressor and the second boost compressor are mechanically powered by the turbine engine. ### Claim 12 A system for an aircraft, comprising: a turbine engine including a flowpath, a compressor section, a combustor section and a turbine section, the flowpath extending through the compressor section, the combustor section and the turbine section from an airflow inlet into the flowpath to a combustion products exhaust from the flowpath; and an air system including an air circuit, a first boost compressor, a second boost compressor and a heat exchanger, a circuit inlet into the air circuit fluidly coupled to the flowpath upstream of the combustor section, and the air circuit projecting out from the circuit inlet and extending through the first boost compressor, the second boost compressor and the heat exchanger, wherein the air circuit includes a first circuit leg extending through the first boost compressor; a second circuit leg extending through the heat exchanger; and a plurality of parallel circuit legs disposed between and fluidly coupled with the first circuit leg and the second circuit leg, a first of the plurality of parallel circuit legs extending through the second boost compressor, and a second of the plurality of parallel circuit legs bypassing the second boost compressor. ### Claim 13 (depends on 12) The system of claim 12, wherein the air circuit further includes a valve configured to fluidly couple the first circuit leg to the first of the plurality of parallel circuit legs during a first mode; and fluidly couple the second circuit leg to the second of the plurality of parallel circuit legs during a second mode. ### Claim 14 (depends on 13) The system of claim 13, wherein the valve is further configured to at least one of fluidly decouple the first circuit leg from the second of the plurality of parallel circuit legs during the first mode; or fluidly decouple the first circuit leg from the first of the plurality of parallel circuit legs during the second mode. ### Claim 15 A system for an aircraft, comprising: a turbine engine including a flowpath, a first rotating structure, a compressor section, a combustor section and a turbine section, the flowpath extending through the compressor section, the combustor section and the turbine section from an airflow inlet into the flowpath to a combustion products exhaust from the flowpath, and the first rotating structure comprising a first bladed rotor in the compressor section or the turbine section; an air system including an air circuit, a first boost compressor and a heat exchanger, a circuit inlet into the air circuit fluidly coupled to the flowpath upstream of the combustor section, the air circuit projecting out from the circuit inlet and extending through the first boost compressor and the heat exchanger, and the first boost compressor comprising a first boost compressor rotor; and a first electric machine comprising a first electric machine rotor, the first electric machine rotor operably coupled to and between the first rotating structure and the first boost compressor rotor. ### Claim 16 A system for an aircraft, comprising: a turbine engine including a flowpath, a first rotating structure, a compressor section, a combustor section and a turbine section, the flowpath extending through the compressor section, the combustor section and the turbine section from an airflow inlet into the flowpath to a combustion products exhaust from the flowpath, and the first rotating structure comprising a first bladed rotor in the compressor section or the turbine section; an air system including an air circuit, a first boost compressor and a heat exchanger, a circuit inlet into the air circuit fluidly coupled to the flowpath upstream of the combustor section, the air circuit projecting out from the circuit inlet and extending through the first boost compressor and the heat exchanger, and the first boost compressor comprising a first boost compressor rotor; and a first electric machine comprising a first electric machine rotor; the first boost compressor rotor operably coupled to and between the first rotating structure and the first electric machine rotor.