petrie

Claim 1

AN AIRCRAFT COMPRISING AT LEAST ONE VERTICALLY MOUNTED GAS TURBINE ENGINE IN THE AIRCRAFT, SAID GAS TURBINE ENGINE COMPRISING TWO MULTI-STAGE AXIAL FLOW COMPRESSORS WHICH ARE AXIALLY ALIGNED AND ARRANGED WITH THEIR INLETS FACING EACH OTHER, COMBUSTION EQUIPMENT AND TURBINE MEANS ARRANGED IN AXIAL FLOW SERIES, SAID TURBINE MEANS BEING AXIALLY ALIGNED WITH SAID COMPRESSORS, SUBSTANTIALLY STRAIGHT LINE FLOW DUCTING, INCLUDING SAID COMBUSTION EQUIPMENT CONNECTING ONE OF SAID COMPRESSORS AND SAID TURBINE MEANS WHEREBY COMPRESSED AIR FROM THE ONE OF SAID COMPRESSORS IS SUPPLIED IN A SUBSTANTIALLY STRAIGHT LINE DIRECTION FORM THE ONE OF SAID COMPRESSORS TO THE COMBUSTION EQUIPMENT AND EXHAUST GASES FORM SAID COMBUSTION EQUIPMENT IS SUPPLIED IN A SUBSTANTIALLY STRAIGHT LINE DIRECTION TO AND THROUGH SAID TURBINE, THE OTHER OF SAID COMPRESSORS HAVING AN OUTLET FOR DELIVERING COMPRESSED AIR TO AUXILIARY EQUIPMENT REQUIRING COMPRESSED AIR, SHAFTING CONNECTING BOTH SAID COMPRESSORS TO SAID TURBINE MEANS, SAID TURBINE DRIVING SAID COMPRESSORS, AND AN AIR INTAKE WHICH IS DISPOSED BETWEEN THE TWO SAID INLETS TO THE TWO COMPRESSORS, SAID AIR INTAKE HAVING WALLS WHICH RESPECTIVELY DIRECT THE AIR INTO THE INLETS TO THE TWO COMPRESSORS.