Transient gas turbine engine bleed control

Details Transient gas turbine engine bleed control Transient gas turbine engine bleed control

F - Mech Eng,Light,Heat,Weapons

02

C

341/38.1

F02C 9/18 (2006.01) F04D 27/02 (2006.01)

Patent

CA 1240381

- 7 - Abstract Transient Gas Turbine Engine Bleed Control Flexibility in the control of the compressor bleed valve is of the type utilized in a twin spool axial flow engine for preventing compressor surge is manifested by electronically summing an approximated burner pressure that has a first order time constant introduced to actual burner pressure and a burner pressure limit that is scheduled as a function of corrected high pressure compressor speed and the altitude of the aircraft. The signal may be treated by a hysteresis circuit to stabilize the bleed valve.

490234

Affiliated with

Also associated with

Rating

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

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

Rate now

Comments { 0 }

Profile ID: LFCA-PAI-O-1271973