Patent ID: 6942181
Filing Date: 2005-09-13
Classification: B64D,F02C,F05D,Y02T

Abstract:
1. An auxiliary power unit assembly on an aircraft, the assembly comprising: an auxiliary power unit housed within a compartment of the aircraft, the auxiliary power unit including at least a compressor portion and a gas exhaust end; and an exhaust eductor in communication with the exhaust end of the auxiliary power unit, the eductor including: a nozzle disposed downstream of and in fluid communication with the auxiliary power unit exhaust end for receiving a gas exhaust flow from the auxiliary power unit in use; a mixing member in fluid communication with the nozzle and a source of secondary air, the mixing member adapted to introduce secondary air into the gas exhaust flow; and a bleed nozzle in fluid communication with the auxiliary power unit compressor portion and the nozzle, the bleed nozzle adapted to introduce pressurized air from the compressor portion into the exhaust flow, wherein the bleed nozzle introduces pressurized air into the nozzle at a position upstream of where the mixing member introduces secondary air into the nozzle.