Gas turbine engine with gas starter

Claim 1

A GAS TURBINE ENGINE INCLUDING COMPRESSOR MEANS, COMBUSTION EQUIPMENT AND A TURBINE ARRANGED IN FLOW SERIES, SAID TURBINE HAVING STATOR VANES AND ROTOR BLADES, FIRST, SECOND AND THIRD ANNULAR CASING MEMBERS ARRANGED SUCCESSIVELY RADIALLY OUTWARDLY OF ONE ANOTHER, SAID STATOR VANES BEING DISPOSED WITHIN AND MOUNTED ON SAID FIRST ANNULAR CASING MEMBER, SAID STATOR VANES HAVING PLATFORMS AT THEIR RADIALLY OUTER ENDS WHICH ARE RADIALLY SPACED FROM SAID SECOND CASING MEMBER, SAID PLATFORMS COMPLETING WITH SAID FIRST CASING MEMBER AN INNER WALL OF AN ANNULAR COOLING AIR PASSAGE WHOSE OUTER WALL IS FORMED BY SAID SECOND CASING MEMBER, MEANS FOR SUPPLYING A FLOW OF COOLING AIR TO SAID PASSAGE WHICH EFFECTS COOLING OF SAID STATOR VANES, SAID THIRD CASING MEMBER FORMING WITH SAID SECOND CASING MEMBER AN ANNULAR MANIFOLD ADAPTED TO BE SUPPLIED WITH GAS UNDER PRESSURE, A PLURALITY OF STRAIGHT CONDUITS SECURED TO SAID SECOND CASING MEMBER AND COMMUNICATING WITH SAID MANIFOLD, THE AXES OF SAID CONDUITS BEING OBLIQUELY INCLINED RELATIVE TO THE LONGITUDINAL AXIS OF THE ENGINE, A PLURALITY OF STRAIGHT NOZZLES FORMED INTEGRALLY WITH SAID PLATFORMS, SAID CONDUITS TRAVERSING SAID PASSAGE AND BEING SPACED TO PERMIT FLOW OF COOLING AIR THERETHROUGH AND COMMUNICATING WITH SAID NOZZLES, THE AXIS OF EACH NOZZLE BEING ALIGNED WITH THAT OF THE RESPECTIVE CONDUIT COMMUNICATING THEREWITH, SAID NOZZLES DIRECTING PRESSURIZED GAS FROM SAID MANIFOLD ONTO SAID ROTOR VANES FOR EFFECTING STARTING OF THE ENGINE.