초록 ▼

A method for recovering air in an aircraft includes bleeding bypass air from an engine bypass, bleeding core air from an engine core, and placing the bypass air and the core air in a heat exchange relationship to produce heated bypass air and cooled core air. The method further includes directing th

A method for recovering air in an aircraft includes bleeding bypass air from an engine bypass, bleeding core air from an engine core, and placing the bypass air and the core air in a heat exchange relationship to produce heated bypass air and cooled core air. The method further includes directing the heated bypass air to one or more of: the engine bypass, a cowl de-icing system, and a wing anti-ice system.

대표청구항 ▼

1. A method for recovering air in an aircraft, the method comprising: bleeding a portion of bypass air from an engine bypass;bleeding a portion of core air from an engine core;placing the bled bypass air and the bled core air in a heat exchange relationship external to an engine nacelle to produce h

1. A method for recovering air in an aircraft, the method comprising: bleeding a portion of bypass air from an engine bypass;bleeding a portion of core air from an engine core;placing the bled bypass air and the bled core air in a heat exchange relationship external to an engine nacelle to produce heated bypass bleed air and cooled core bleed air; anddirecting the heated bypass bleed air separately from the cooled core bleed air to one or more of: a cowl de-icing system, and a wing anti-ice system. 2. The method of claim 1, wherein the portion of core air is bled from a low pressure compressor. 3. The method of claim 1, wherein the portion of core air is bled from a high pressure compressor. 4. A system for recovering air in an aircraft, the system comprising: an engine core;an engine bypass surrounding the engine core;an air-to-air heat exchanger external to an engine nacelle, the heat exchanger having a first inlet, a second inlet, a first outlet, and a second outlet, the second inlet fluidly connected to the engine bypass to receive a portion of bypass air that is bled from the engine bypass, the first inlet fluidly connected to the engine core to receive a portion of core air that is bled from the engine core; anda fourth duct fluidly connected to the second outlet of the air-to-air heat exchanger for directing heated bled bypass air from the heat exchanger to another location in the aircraft for further use, the fourth duct directing only heated bled bypass air, wherein the fourth duct is connected to one or more of: a cowl de-icing system and a wing anti-ice system. 5. The system of claim 4, further comprising: a first duct fluidly connecting the engine core to the first inlet of the heat exchanger to direct the bled core air from the engine core to the heat exchanger; anda third duct fluidly connected to the first outlet of the air-to-air heat exchanger to direct bled core air from the heat exchanger away from the heat exchanger, the third duct directing only bled core air. 6. The system of claim 5, wherein the first duct and the fourth duct are located proximate to each other in a heat exchange relationship. 7. The system of claim 5, wherein the fourth duct surrounds the first duct in a heat exchange relationship. 8. A system for recovering air in an aircraft, the system comprising: an engine core including a compressor, a combustor, and a turbine in flow series for compressing, combusting, and expanding working fluid, respectively;an engine bypass surrounding the engine core, the engine bypass including an upstream end receiving bypass air from an outer perimeter of a fan connected to the compressor;a first duct having an inlet and an outlet, the inlet connected to the engine core to receive a portion of core air that is bled from the engine core;a second duct having an inlet and an outlet, the inlet connected to the engine bypass to receive a portion of bypass air that is bled from the engine bypass;an air-to-air heat exchanger having a first inlet, a second inlet, a first outlet, and a second outlet, the first inlet connected to the outlet of the first duct, the second inlet connected to the outlet of the second duct, the air-to-air heat exchanger external to an engine nacelle configured to place the bled core air in a heat exchange relationship with the bled bypass air;a third duct having an inlet and an outlet, the inlet connected to the first outlet of the air-to-air heat exchanger for receiving cooled bled core air from the heat exchanger and the outlet connected to an aircraft system that utilizes the cooled bled core air; anda fourth duct having an inlet and an outlet, the inlet connected to the second outlet of the heat exchanger for receiving heated bled bypass air and the outlet connected to deliver the heated bled bypass air to one or more of: a cowl de-icing system and a wing anti-icing system. 9. The system of claim 8, wherein the first duct and the fourth duct are adjacent to one another in a heat exchange relationship. 10. The system of claim 8, wherein the fourth duct surrounds a portion of the first duct in a heat exchange relationship.