US 9,810,158 B2
Bleed air systems for use with aircraft and related methods
David W. Foutch, Seattle, WA (US); and Steve G. Mackin, Bellevue, WA (US)
Assigned to THE BOEING COMPANY, Chicago, IL (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on Apr. 1, 2014, as Appl. No. 14/242,570.
Prior Publication US 2015/0275769 A1, Oct. 1, 2015
Int. Cl. F02C 9/18 (2006.01); F02C 3/10 (2006.01); F02C 7/047 (2006.01); F02C 7/27 (2006.01); F02C 7/32 (2006.01); B64D 13/06 (2006.01)
CPC F02C 9/18 (2013.01) [F02C 3/10 (2013.01); F02C 7/047 (2013.01); F02C 7/27 (2013.01); F02C 7/32 (2013.01); B64D 2013/064 (2013.01); B64D 2013/0648 (2013.01); Y02T 50/671 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A bleed air system for an aircraft comprising:
a turbo-compressor comprising a compressor, a turbine, and a first drive shaft coupled between the compressor and the turbine, the first drive shaft to enable the turbine to selectively drive the compressor, the compressor having a compressor inlet and a compressor outlet, the compressor outlet to be fluidly coupled to a system of the aircraft that receives pressurized air, the compressor inlet to receive bleed air from a low-pressure compressor of an engine of the aircraft;
a gearbox operatively coupled to the first drive shaft to drive the compressor, the gearbox operatively coupled to and powered by a second drive shaft extending from the engine; and
a clutch disposed between the first drive shaft and the gearbox to selectively connect the first drive shaft to the gearbox to enable the engine to drive the turbo-compressor.