# US 2017/0283074 A1 · Aircraft air conditioning system including a thermoelectric device > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2017/0283074 A1 - Document ID: US20170283074A1 - Status: Published application - Kind: A1 - Application number: 15/087,347 - Filed: 2016-03-31 - Published: 2017-10-05 - Earliest claimed: 2016-03-31 - Assignees: Hamilton Sundstrand Corporation - Applicants: Hamilton Sundstrand Corporation - Inventors: Thomas M. Zywiak; Brian St. Rock - Web page: https://patentgrep.com/patent/US20170283074A1 ## CPC - B64D 13/08: the air being heated or cooled - B64D 13/02: the air being pressurised - B64D 13/06: the air being conditioned (pressurising B64D13/02) - F25B 9/004: {the refrigerant being air} - F25B 9/06: using expanders (F25B9/10 takes precedence) - F25B 21/02: using Peltier effect; using Nernst-Ettinghausen effect - F25B 43/00: Arrangements for separating or purifying gases or liquids (in analysers or rectifiers F25B33/00); Arrangements for vaporising the residuum of liquid refrigerant, e.g. by heat (F25B40/00 takes precedence) - B64D 2013/0603: {Environmental Control Systems} - B64D 2013/0618: {with arrangements for reducing or managing bleed air, using another air source, e.g. ram air} - B64D 2013/0648: {with energy recovery means, e.g. using turbines} - B64D 2013/0662: {with humidity control} - F25B 2321/0251: by a gas - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F25B: REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS ## Abstract A environmental control system (ECS) for an aircraft includes a primary heat exchanger configured to receive bleed air from a turbine compressor of the aircraft and a secondary heat exchanger having an input configured to receive a flow from the primary heat exchanger and a secondary heat exchanger output. The ECS also includes a thermoelectric condensing device having an input in fluid communication with the output of the secondary heat exchanger and also having a thermoelectric condensing device output. ## Claims ### Claim 1 A environmental control system (ECS) for an aircraft, the ECS including: a primary heat exchanger configured to receive bleed air from a turbine compressor of the aircraft; a secondary heat exchanger having an input configured to receive a flow from the primary heat exchanger and a secondary heat exchanger output; and a thermoelectric condensing device having an input in fluid communication with the output of the secondary heat exchanger and also having a thermoelectric condensing device output. ### Claim 2 (depends on 1) The ECS of claim 1, further comprising: a water cyclone in fluid communication with the thermoelectric condensing device outlet. ### Claim 3 (depends on 1) The ECS of claim 1, wherein at least one of the primary heat exchanger, the secondary heat exchanger and the thermoelectric condensing device are disposed in a ram air channel of the aircraft. ### Claim 4 (depends on 1) The ECS of claim 1, wherein the primary heat exchanger, the secondary heat exchanger and the thermoelectric condensing device are disposed in a ram air channel of the aircraft. ### Claim 5 (depends on 1) The ECS of claim 1, further comprising: an air cycle machine that includes a turbine and a compressor. ### Claim 6 (depends on 5) The ECS of claim 5, wherein the compressor includes a compressor input in fluid communication with the primary heat exchanger and an output in fluid communication with the input of the secondary heat exchanger such that the flow passes through the compressor after it leaves the primary heat exchanger and before it enters the secondary heat exchanger. ### Claim 7 (depends on 5) The ECS of claim 5, wherein the turbine has input in fluid communication with the thermoelectric condensing device output. ### Claim 8 An aircraft comprising: an aircraft cabin; a turbine compressor; and an environmental control system (ECS), the ECS including: a primary heat exchanger that receives bleed air from the turbine compressor; a secondary heat exchanger having an input configured to receive a flow from the primary heat exchanger and a secondary heat exchanger output; and a thermoelectric condensing device having an input in fluid communication with the output of the secondary heat exchanger and also having a thermoelectric condensing device output. ### Claim 9 (depends on 8) The aircraft of claim 8, wherein the ECS further includes: a water cyclone in fluid communication with the thermoelectric condensing device outlet. ### Claim 10 (depends on 8) The aircraft of claim 8, wherein at least one of the primary heat exchanger, the secondary heat exchanger and the thermoelectric condensing device are disposed in a ram air channel of the aircraft. ### Claim 11 (depends on 8) The aircraft of claim 8, wherein the ECS further includes: an air cycle machine that includes a turbine and a compressor. ### Claim 12 (depends on 11) The aircraft of claim 11, wherein the compressor includes a compressor input in fluid communication with the primary heat exchanger and an output in fluid communication with the input of the secondary heat exchanger such that the flow passes through the compressor after it leaves the primary heat exchanger and before it enters the secondary heat exchanger. ### Claim 13 (depends on 11) The aircraft of claim 11, wherein the turbine has input in fluid communication with the thermoelectric condensing device output. ### Claim 14 A environmental control system (ECS) for an aircraft, the ECS including: an air cycle machine that includes a turbine and a compressor; and a thermoelectric condensing device that is in fluid communication with an output of the compressor and an input of the turbine. ### Claim 15 (depends on 14) The ECS of claim 14, further comprising: a water cyclone in fluid communication with the thermoelectric condensing device and the turbine and disposed in a fluid path between them.