US 12,358,630 B2
Cryogenic cooling system for an aircraft
Frederick M. Schwarz, Glastonbury, CT (US); Michael Winter, New Haven, CT (US); Charles E. Lents, Amston, CT (US); Nathan Snape, Tolland, CT (US); and Alan H. Epstein, Lexington, MA (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Dec. 16, 2022, as Appl. No. 18/082,888.
Application 18/082,888 is a division of application No. 16/360,280, filed on Mar. 21, 2019, granted, now 11,542,016.
Claims priority of provisional application 62/647,055, filed on Mar. 23, 2018.
Claims priority of provisional application 62/647,060, filed on Mar. 23, 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 62/653,604, filed on Apr. 6, 2018.
Claims priority of provisional application 62/656,451, filed on Apr. 12, 2018.
Claims priority of provisional application 62/656,453, filed on Apr. 12, 2018.
Prior Publication US 2023/0122852 A1, Apr. 20, 2023
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); 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 1/00 (2006.01); F25J 3/04 (2006.01); B64D 37/32 (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 1/0012 (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)] 20 Claims
OG exemplary drawing
 
1. An engine-driven cryogenic cooling system for an aircraft, the engine-driven cryogenic cooling system comprising:
a first air cycle machine comprising a plurality of components operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream from a first engine bleed source of the gas turbine engine;
a second air cycle machine operable to output a chilled air stream at a cryogenic temperature from a second engine bleed source cooled by the cooling air stream of the first air cycle machine; and
a means for condensing the chilled air stream into liquid air for an aircraft use.