US 12,291,338 B2
Chilled working fluid generation and separation for an aircraft
Michael Winter, New Haven, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Mar. 10, 2022, as Appl. No. 17/691,578.
Application 17/691,578 is a division of application No. 16/361,482, filed on Mar. 22, 2019, granted, now 11,299,279.
Claims priority of provisional application 62/656,453, filed on Apr. 12, 2018.
Claims priority of provisional application 62/656,451, filed on Apr. 12, 2018.
Claims priority of provisional application 62/653,604, filed on Apr. 6, 2018.
Claims priority of provisional application 62/653,599, filed on Apr. 6, 2018.
Claims priority of provisional application 62/653,602, filed on Apr. 6, 2018.
Claims priority of provisional application 62/647,060, filed on Mar. 23, 2018.
Claims priority of provisional application 62/647,055, filed on Mar. 23, 2018.
Prior Publication US 2022/0194604 A1, Jun. 23, 2022
Int. Cl. B64D 13/08 (2006.01); B01D 45/08 (2006.01); B01D 53/00 (2006.01); B03C 1/28 (2006.01); B64D 13/06 (2006.01); B64D 27/12 (2006.01); B64D 33/08 (2006.01); B64D 37/32 (2006.01); F01D 15/00 (2006.01); F01D 25/12 (2006.01); F02C 6/08 (2006.01); F02C 7/141 (2006.01); F02C 7/143 (2006.01); F02C 7/16 (2006.01); F02C 7/18 (2006.01); F02C 9/18 (2006.01); F02K 3/06 (2006.01); F17C 7/02 (2006.01); F17C 7/04 (2006.01); F25B 9/14 (2006.01); F25J 3/04 (2006.01)
CPC B64D 13/08 (2013.01) [B01D 45/08 (2013.01); B01D 53/002 (2013.01); B03C 1/288 (2013.01); B64D 13/06 (2013.01); B64D 27/12 (2013.01); B64D 33/08 (2013.01); F01D 15/00 (2013.01); F01D 25/12 (2013.01); F02C 6/08 (2013.01); F02C 7/141 (2013.01); F02C 7/143 (2013.01); F02C 7/16 (2013.01); F02C 7/185 (2013.01); F02C 9/18 (2013.01); F02K 3/06 (2013.01); F17C 7/02 (2013.01); F17C 7/04 (2013.01); F25B 9/14 (2013.01); F25J 3/04254 (2013.01); F25J 3/04975 (2013.01); B64D 2013/0614 (2013.01); B64D 2013/0659 (2013.01); B64D 2013/0674 (2013.01); B64D 2013/0677 (2013.01); B64D 2013/0681 (2013.01); B64D 37/32 (2013.01); F05D 2220/323 (2013.01); F05D 2260/205 (2013.01); F05D 2260/211 (2013.01); F05D 2260/232 (2013.01); F05D 2260/60 (2013.01); F25J 2240/42 (2013.01); F25J 2240/80 (2013.01); F25J 2290/70 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A system for an aircraft, the system comprising:
an engine bleed source of a gas turbine engine;
a means for chilling an engine bleed air flow from the engine bleed source to produce liquid air comprising a cryogenic cooling system comprising a heat exchanger system operable to pre-cool the engine bleed air flow, a compressor operable to further compress the engine bleed air flow as compressed air, and at least one turbine operable to expand and cool the compressed air as a cooled flow, wherein the heat exchanger system is configured to receive a cooling air intake that pre-cools the engine bleed air flow and cools the compressed air from the compressor prior to reaching the at least one turbine; and
a means for providing the liquid air for an aircraft use.