Gas turbine engine control based on inlet pressure distortion

Details Gas turbine engine control based on inlet pressure distortion Gas turbine engine control based on inlet pressure distortion

1993-06-09

1995-09-12

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

Combined with regulation of power output feature

60242, 36443102, 415 26, F02C 916

Patent

active

054488818

ABSTRACT:
Circumferential and radial inlet pressure distortion on an aircraft gas turbine engine are detected by a plurality of static pressure sensors and a signal processor, which computes the total pressure for each sensor to determine a pressure distortion pattern which the processor correlates with stored data for the engine and inlet to determine if the airflow geometry should be altered during flight. Time varying changes in the pressure from one or more of the pressure sensors is used to determine a stall condition, causing a change in engine airflow geometry to increase stall margin.

REFERENCES:
patent: 3911260 (1975-10-01), Dustin
patent: 4130872 (1978-12-01), Harloff
patent: 4414807 (1983-11-01), Kerr
patent: 4550564 (1985-11-01), Callahan et al.
patent: 4581888 (1986-04-01), Schmitzer et al.

Affiliated with

Also associated with

Rating

Gas turbine engine control based on inlet pressure distortion 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 based on inlet pressure distortion, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Gas turbine engine control based on inlet pressure distortion will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-400206