US 12,215,628 B2
Aircraft system with gas turbine engine powered compressor
Steven W. Burd, Cheshire, CT (US); and Christopher A. Eckett, Simsbury, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Dec. 30, 2022, as Appl. No. 18/091,860.
Claims priority of provisional application 63/391,470, filed on Jul. 22, 2022.
Prior Publication US 2024/0026827 A1, Jan. 25, 2024
Int. Cl. F02C 7/32 (2006.01); F02C 3/073 (2006.01); F02C 3/10 (2006.01); F02C 3/113 (2006.01); F02C 3/14 (2006.01); F02C 6/18 (2006.01); F02C 6/20 (2006.01); F02C 7/36 (2006.01); F02K 3/06 (2006.01)
CPC F02C 7/32 (2013.01) [F02C 3/073 (2013.01); F02C 3/113 (2013.01); F02C 3/14 (2013.01); F02C 6/18 (2013.01); F05D 2220/323 (2013.01); F05D 2220/50 (2013.01)] 19 Claims
OG exemplary drawing
 
1. An aircraft system, comprising:
a gas turbine engine including a compressor section, a turbine section, a combustor section and a rotating structure, the combustor section fluidly coupled with and between the compressor section and the turbine section, and the rotating structure including a compressor section rotor within the compressor section and a turbine section rotor within the turbine section;
an engine flowpath extending sequentially through the compressor section, the combustor section and the turbine section;
a gearbox;
at least one compressor including a compressor rotor rotatably driven by the rotating structure through the gearbox, wherein the gas turbine engine is dedicated to powering the at least one compressor, and the at least one compressor comprises a centrifugal flow compressor; and
a compressor flowpath extending through the at least one compressor to at least one fluid component outside of the gas turbine engine, wherein the compressor flowpath is discrete from the engine flowpath.