Pressure ratio control system for a gas turbine engine

Abstract

Abstract A PRESSURE RATIO CONTROL SYSTEM FOR A GAS TURBINE ENGINE HAVING A FUEL PUMP TOGETHER WITH MEANS REGULATING FUEL FLOW TO THE ENGINE BURNERS, COMPRISING A PRESSURE RATIOSENSING DEVICE HAVING A DISCHARGE NOZZLE AND A RECEIVER NOZZLE CO-AXIALLY SPACED THEREFROM, THE DIAMETERS AND SPACING OF THE NOZZLES BEING SUCH THAT IN THE REGION OF A PREDETERMINED CRITICAL RATIO OF INLET PRESSURE TO OUTLET PRESSURE OF THE DISCHARGE NOZZLE, THE RATE OF CHANGE OF PRESSURE IN THE RECEIVE NOZZLE, OCCURRING WITH A CHANGE IN THE DISCHARGE NOZZLE PRESSURE RATIO, PROVIDES A CONTROLLING PARAMETER RESTRICTOR MEANS FOR SUPPLYING THE INLET AND OUTLET RESPECTIVELY OF THE DISCHARGE NOZZLE WITH HIGHER AND LOWER FLUID PRESSURES DERIVED FROM TWO DIFFERENT PRESSURE SOURCES IN THE ENGINE COMPRESSOR, CONTROL MEANS OPERABLE ON THE RESTRICTOR MEANS TO SELECT A DISCHARGE NOZZLE PRESSURE RATIO AS A SELECTED PROPORTION OF THE COMPRESSOR PRESSURE RATIO OF THE TWO SOURCES, AND FLUID-OPERATED MEANS ARRANGED TO CONTROL THE FUEL FLOW REGULATING MEANS IN RESPONSE TO A CHANGE IN THE PRESSURE IN THE RECEIVER NOZZLE, WHEREBY THE RATE OF COMBUSTION OF FUEL REGULATES THE ENGINE SPEED AND THEREFORE THE SAID COMPRESSOR PRESSURE RATIO SUCH THAT THE DISCHARGE NOZZLE PRESSURE RATIO TENDS TOWARDS THE PREDETERMINED CRITICAL VALUE.

Inventors

• 👤 Ronald Rimmer

Bibliographic Details