US 12,140,088 B1
Method for detecting and annunciating gas turbine engine compressor stall
Ryan Perera, Mississauga (CA); Zubair Ahmad, Mississauga (CA); Fady Freiga, Aurora (CA); and Safi Nizami, Mississauga (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Sep. 22, 2023, as Appl. No. 18/472,568.
Int. Cl. F02C 9/32 (2006.01); F02C 7/262 (2006.01); F02C 9/18 (2006.01); F02C 9/28 (2006.01); F02C 9/20 (2006.01)
CPC F02C 9/32 (2013.01) [F02C 7/262 (2013.01); F02C 9/18 (2013.01); F02C 9/28 (2013.01); F02C 9/20 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a propulsor, a compressor and a turbine section having a first turbine rotor connected to the compressor through a first shaft, and a second turbine rotor connected to at least the propulsor through a second shaft, the first turbine rotor for driving the compressor at a first speed, and the second turbine rotor for driving the propulsor at a second speed;
a control for the gas turbine engine, the control being programmed to compare one of the first speed and the second speed to a commanded speed to determine a difference, the control also being programmed to identify a flame out condition, and identify a locked in stall condition when the difference between the two speeds exceeds a threshold for at least a threshold period of time at least in part concurrently with the flame out condition; and
the control being programmed to take a corrective action should the locked in stall condition be identified.