Control for gas turbine engine

Details Control for gas turbine engine Control for gas turbine engine

G - Physics

05

D

341/17

G05D 7/06 (2006.01) F02K 1/17 (2006.01)

Patent

CA 1096463

CONTROL FOR GAS TURBINE ENGINE Abstract of the Disclosure Increased thrust during the transonic flight mode of an aircraft powered by a gas turbine engine is realized by a closed loop control that closes the loop on the pressure ratio across the fan by adjusting fuel flow and/ or exhaust nozzle area in a turbofan, variable exhaust nozzle installation. Fan pressure ratio is scheduled as a function of corrected fan speed and actual pressure ratio provides an error signal to readjust engine operation to null out this error signal. A turbine inlet temperature limit signal is generated to prevent inadvertent overheating and it or this pressure ratio error signal is selected for providing the lower fuel flow value. - 1 -

295674

Affiliated with

Also associated with

Rating

Control for gas turbine engine does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Control for gas turbine engine, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Control for gas turbine engine will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFCA-PAI-O-684411