Patent ID: 9062604
Filing Date: 2015-06-23
Classification: B64D,F02C,Y02T

Abstract:
1. A bleed air conditioning system within an aircraft, the system comprising: a low-pressure bleed air line for carrying bleed air at a first pressure from a compressor; a high-pressure bleed air line for carrying bleed air at a second pressure from the compressor, wherein the second pressure is higher than the first pressure; an air-to-air heat exchanger cooled by a cooling air flow; an un-cooled bleed air line connecting the low-pressure bleed air line and the high-pressure bleed air line to the air-to-air heat exchanger for carrying a flow of un-cooled bleed air from at least one of the low-pressure bleed air line and the high-pressure bleed air line to the air-to-air heat exchanger; a cooled bleed air line connected to the air-to-air heat exchanger for carrying cooled bleed air from the air-to-air heat exchanger; a low-pressure bypass line connecting the low-pressure bleed air line to the cooled bleed air line for bypassing un-cooled bleed air from the low-pressure line around the air-to-air heat exchanger to the cooled bleed air line; wherein the cooled bleed air line is connected to an environmental control system for providing cooled bleed air to the environmental control system; and wherein the low-pressure bypass line flows into the cooled bleed air line upstream of the environmental control system.