|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/3902 ; 60/3929|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 18 인용 특허 : 0|
A bleed air control system for an aircraft gas turbine engine operates in a fuel saving mode in response to operation of the aircraft in a steady-state cruise condition (215,350) within a threshold flight envelope (202,310) during steady-state engine operation above a threshold range. During operation in the fuel saving mode, a gas turbine engine compressor bleed valve (10) is closed. The rate of bleed valve closure is determined as a function of bleed valve position (12,20) and gas generator speed (26,30) at the instant the fuel savings mode is initiate...
A gas turbine engine bleed air control system for controlling a turbine engine compressor bleed valve in response to engine operating parameters, comprising: a normal bleed schedule; a fuel savings mode schedule; means responsive to the steady-state operation of said gas turbine engine above a threshold gas generator speed for providing an enable signal; and said bleed air control system replacing said normal bleed schedule with said fuel savings mode schedule in response to said enable signal.