|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02C-006/08 F02C-007/18 B64D-013/06|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 6 인용 특허 : 12|
The combined cooling system uses a single heat exchanger to cool both engine air for use in an engine system and aircraft air for use in an aircraft system. More particularly, a bleed air path leads from the compressor stage to the heat exchanger where it is placed in thermal exchange contact with a flow of cooling air coming from a cooling path. From an outlet end of the heat exchanger, the bleed air splits into two paths: an aircraft air path leading to at least one aircraft system such as an Environmental control system (ECS), a wind de-icing system o...
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 environmen...