US 12,351,318 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. 18/082,848.
Application 18/082,848 is a division of application No. 16/360,280, filed on Mar. 21, 2019, granted, now 11,542,016.
Claims priority of provisional application 62/656,453, filed on Apr. 12, 2018.
Claims priority of provisional application 62/656,451, filed on Apr. 12, 2018.
Claims priority of provisional application 62/653,599, 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 62/647,060, filed on Mar. 23, 2018.
Claims priority of provisional application 62/647,055, filed on Mar. 23, 2018.
Prior Publication US 2023/0303254 A1, Sep. 28, 2023
Int. Cl. F02C 7/141 (2006.01); B01D 45/08 (2006.01); B01D 53/00 (2006.01); B03C 1/28 (2006.01); B64D 13/06 (2006.01); B64D 13/08 (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 7/143 (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. A gas turbine engine of an aircraft, the gas turbine engine comprising:
a compressor section;
a turbine section operably coupled to the compressor section;
a means for selectively releasing a cooling fluid flow produced on board the aircraft at a cryogenic temperature; and
a plumbing system in fluid communication with the means for selectively releasing the cooling fluid flow, the plumbing system configured to route the cooling fluid flow to either or both of the compressor section and the turbine section.