Power plants – Reaction motor – Method of operation
Patent
1993-09-22
1995-03-07
Casaregola, Louis J.
Power plants
Reaction motor
Method of operation
60243, 60 39281, F02C 928
Patent
active
053946898
ABSTRACT:
A gas turbine engine digital electronic control is disclosed which is capable of maintaining safe, efficient engine thrust levels in the event of loss of communication with an aircraft flight computer. Specifically, a limited number of engine sensor inputs are used in combination with an engine performance schedule to derive total inlet pressure. A compressible flow calculation yields flight Mach number which is used in a power management module to control engine power settings, such as corrected fan speed in a turbofan engine. Various correction factors and scalars are provided to configure the control for a variety of installation configurations, as well as improve system accuracy.
REFERENCES:
patent: 3617721 (1971-11-01), Foster
patent: 3656301 (1972-04-01), Katz
patent: 3717038 (1973-02-01), Plett et al.
patent: 3738102 (1973-06-01), Stearns et al.
patent: 3797233 (1974-03-01), Webb et al.
patent: 3936226 (1976-02-01), Harner et al.
patent: 4242864 (1981-01-01), Cornett et al.
patent: 4277940 (1981-07-01), Harner et al.
patent: 4294069 (1981-10-01), Camp
patent: 4528812 (1985-07-01), Cantwell
patent: 4748804 (1988-06-01), Krukoski
patent: 4829813 (1989-05-01), Syed
patent: 5133182 (1992-07-01), Marcos
Casaregola Louis J.
General Electric Company
Shay Bernard E.
Squillaro Jerome C.
LandOfFree
Gas turbine engine control system having integral flight Mach nu does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Gas turbine engine control system having integral flight Mach nu, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Gas turbine engine control system having integral flight Mach nu will most certainly appreciate the feedback.
Profile ID: LFUS-PAI-O-1399338