Accession Number : ADD005039

Title :   Compressor Stall Warning System.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE NAVY WASHINGTON D C

Personal Author(s) : Gallant,Richard Paul

Report Date : 11 Apr 1978

Pagination or Media Count : 5

Abstract : This patent describes a compressor stall warning system for jet aircraft gas turbine engines. The turbine inlet temperature and the compressor rotor speed are monitored and signals representative of the ratio of these two functions and the inlet temperature itself are produced. If the turbine inlet temperature increases while the compressor rotor speed decreases their ratio would increase rapidly. When either this ratio or the turbine inlet temperature alone increase beyond predetermined thresholds, a signal is furnished to the aircraft pilot warning him of impending aircraft engine stall. (Author)

Descriptors :   *Patents, *Stall warning indicators, *Jet engines, Gas turbines, Jet engine inlets, Temperature measuring instruments, Compressors, Velocity, Ratios

Subject Categories : Flight Control and Instrumentation

Distribution Statement : APPROVED FOR PUBLIC RELEASE