Inventors:
Syed J. Khalid - Palm Beach Gardens FL
James V. French - Huntsville AL
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F02C 916
Abstract:
In an aircraft gas turbine engine, stator vane deflection and compressor bleed are controlled to alter the compressor airflow vs. compressor pressure relationship map when stall conditions are detected based on compressor speed and compressor temperature, a change that means that less change in pressure required to nudge the compressor from of a stall, accelerating stall recovery. Once the stall has ceased, the stator deflection and bleed are restored to pre-recovery values.