Stall trip protective device for gas turbines

Claim 1

IN A GAS ENGINE INCLUDING A COMBUSTION CHAMBER, A COMPRESSOR, A TURBINE AND A LIQUID FUEL SUPPLY TO THE COMBUSTION CHAMBER, AN APPARATUS FOR PROTECTING THE TURBINE FROM THE EFFECTS OF SUDDEN BREAKDOWN IN THE COMPRESSOR AIR FLOW COMPRISING, A PNEUMATIC ACUATOR COMMUNICATING WITH THE DISCHARGE END OF THE COMPRESSOR STAGE OF THE TURBINE, MEANS ASSOCIATED WITH SAID PNEUMATIC ACTUATOR FOR RENDERING SAID ACUTATOR NONRESPONSIVE TO THE NORMAL VARIATION IN COMPRESSOR AIR DISCHARGE PRESSURE CCURING DURING NORMAL OPERATION OF THE COMPRESSOR, SAID PNEUMATIC ACUATOR BEING RESPONSIVE ONLY TO AN ABNORMAL SUDDEN DROP IN COMPRESSOR AIR DISCHARGE PRESSURE INDICATIVE OF THE EXISTENCE OF STALL CONDITIONS IN THE COMPRESSOR, AND A LIQUID FUEL FLOW INTERRUPTOR COUPLED TO CO-OPERATE WITH THE PNEUMATIC ACTUATOR, THE INTERRUPTOR BEING EFFECTIVE, UPON OPERATION OF THE ACTUATOR IN RESPONSE TO A SUDDEN DECREASE IN COMPRESSOR AIR DISCHARGE PRESSURE, TO SHUT OOFF THE FLOW OF LIQUID FUEL TO THE COMBUSTION CHAMBER.