US 12,110,116 B1
Pre-heating aircraft engine in standby mode
Ryan A. Mitchell, Jupiter, FL (US); and Robert B. Fowler, West Palm Beach, FL (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Jun. 30, 2023, as Appl. No. 18/217,228.
Int. Cl. B64D 13/06 (2006.01); B64D 13/08 (2006.01); B64D 27/10 (2006.01); F02C 3/13 (2006.01); F02C 6/08 (2006.01); F02C 6/18 (2006.01); F02C 7/08 (2006.01); F02C 9/42 (2006.01); F02K 3/12 (2006.01)
CPC B64D 13/06 (2013.01) [B64D 13/08 (2013.01); B64D 27/10 (2013.01); F02C 3/13 (2013.01); F02C 6/08 (2013.01); F02C 6/18 (2013.01); F02C 7/08 (2013.01); F02C 9/42 (2013.01); F02K 3/12 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A method of operation, comprising:
directing a heating fluid through a first passage into a combustor section to heat a component within the combustor section when an aircraft engine is in a first standby mode, the aircraft engine including a flowpath, a compressor section, the combustor section, a turbine section and an exhaust section, and the flowpath extending through the compressor section, the combustor section, the turbine section and the exhaust section from an inlet into the flowpath to an exhaust from the flowpath; and
directing the heating fluid through a second passage into the exhaust section when the aircraft engine is in a second mode, wherein the heating fluid directed through the second passage bypasses the turbine section;
wherein the heating fluid is received from an aircraft environmental control system.