US 11,926,426 B2
Electric distributed propulsion using exhaust recovery power
Jean Thomassin, Ste Julie (CA); and Todd A. Spierling, Rockford, IL (US)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Mar. 19, 2021, as Appl. No. 17/207,348.
Prior Publication US 2022/0297843 A1, Sep. 22, 2022
Int. Cl. B64D 27/24 (2006.01); B64D 27/04 (2006.01); F02B 37/00 (2006.01)
CPC B64D 27/24 (2013.01) [B64D 27/04 (2013.01); F02B 37/00 (2013.01); F05D 2220/40 (2013.01)] 19 Claims
OG exemplary drawing
 
1. An aircraft power system of an aircraft, the aircraft power system comprising:
an internal combustion engine;
a main air mover configured to provide thrust to the aircraft, the main air mover operatively connected to the internal combustion engine;
a turbocharger including:
a compressor for supplying combustion air to the internal combustion engine, a turbine operatively connected to the internal combustion engine to receive an exhaust flow from the internal combustion engine and convert energy of the exhaust flow into rotational power, and a turbo shaft operatively connecting the turbine to the compressor to transfer at least some of the rotational power to the compressor;
a generator mechanically connected to the turbo shaft to receive at least some of the rotational power from the turbo shaft for generating electrical power; and
at least one electrically powered air-mover electrically connected to the generator to receive at least some of the electrical power and to provide thrust to the aircraft in cooperation with the main air mover, the at least one electrically powered air-mover and the generator being electrically connected together, a pressure ratio of the at least one electrically powered air-mover being adjustable using a variable air nozzle of the at least one electrically powered air-mover.