Patent ID: 9239005
Filing Date: 2016-01-19
CPC Classification: B64D,F02C

Claim Text:
1. A method of providing pressurized and cooled air to both an aircraft and a gas turbine engine thereof, the method comprising: bleeding pressurized air from the gas turbine engine; exposing the bleed air to thermal exchange contact with cooling medium in a heat exchanger, the heat exchanger having an operating envelope spanning from a high-power/low altitude reaction to a low-power/high altitude region and a capacity based on the entire operating envelope; subsequently to said thermal exposure, channeling a first portion of the bleed air to an environmental control system of the aircraft to satisfy an environmental cooling requirement and channelling a second portion of the bleed air to bearing cavities of bearings of rotary components of the gas turbine engine to fulfill a bearing air requirement, wherein the heat exchanger fulfills the environmental cooling requirement and the bearing air requirement across the entire operating envelope; wherein the steps of bleeding, exposing, and channeling are performed: