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Turbojet control system for preventing compressor stall due to inlet air disturbances

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  • 3. FOR A JET ENGINE HAVING A COMPRESSOR WITH VARIABLE COMPRESSOR MEMBERS FOR VARYING THE COMPRESSOR GEOMETRY AND A THRUST REVERSER MECHANISM, A CONTROL MEANS FOR CONTROLLING THE COMPRESSOR GEOMETRY RESPONSIVE TO FIRST AND SECOND CONTROL SIGNALS. A FEEDBACK CIRCUIT CONNECTING SAID COMPRESSOR AND SAID CONTROL MEANS FOR SIGNALLING A FIRST CONTROL INPUT CORRESPONDING TO THE COMPRESSOR GEOMETRY, SAID FEEDBACK CIRCUIT BEING INTERRUPTED TO INCLUDE A COUPLING MEANS WHEREBY SAID FIRST CONTROL INPUT MAY BE CHANGED BY A SECOND CONTROL INPUT, A SECOND CIRCUIT CONNECTING SAID COUPLING MEANS WITH SAID THRUST REVERSER MECHANISM TO CHANGE SAID SECOND CONTROL INPUT RESPONSIVE TO THE POSITION OF SAID THRUST REVERSER THEREBY CAUSING SAID CONTROL MEANS TO CORRELATE THE COMPRESSOR GEOMETRY WITH THE POSITION OF THE THRUST REVERSER MECHANISM TO LESSEN THE EFFECTS OF DISTRURBANCE OF THE ENGINE INLET AIR STREAM DURING THRUST REVERSER OPERATION.
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