Accession Number : ADD002504
Title : Method of and Apparatus for Preventing Compressor Stall in a Gas Turbine Engine.
Descriptive Note : Patent,
Corporate Author : DEPARTMENT OF THE NAVY WASHINGTON D C
Personal Author(s) : Thomson,Faulkner C
Report Date : 17 Feb 1976
Pagination or Media Count : 4
Abstract : The patent relates to a method of and apparatus for detecting air distortion at the inlet of a gas turbine engine and adjusting fuel flow to anticipate and prevent compressor stall. A plurality of pressure taps are arranged in a spaced relation around the periphery of the engine inlet. A distortion detector senses the differential pressure between the instantaneous pressure at each pressure tap and the ambient pressure of a reference pressure chamber which communicates with the plurality of pressure taps. At a predetermined pressure differential the distortion detector activates a solenoid-operated fuel by-pass valve which reduces fuel flow to the fuel nozzles of the gas turbine engine.
Descriptors : *Gas turbines, *Fuel meters, *Patents, Compressors, Fuel systems, Regulators, Fuel nozzles
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE