Unitary nozzles and shroud sections

Claim 1

IN A GAS TURBINE ENGINE, A BLADED ROTOR, A ROTOR SHAFT SECURED COAXIALLY TO SAID ROTOR, BEARING MEANS HAVING SAID SHAFT JOURNALED THEREIN ADJACENT SAID ROTOR, A BEARING SUPPORT FOR SAID BEARING MEANS AND HAVING ANNULAR PILOT MEANS ARRANGED COAXIALLY WITH SAID ROTOR ADJACENT SAID BEARING MEANS AND SHAFT, A ONE-PIECE ASSEMBLY FOR DIRECTING MOTIVE GASES TO THE BLADES OF SAID ROTOR INCLUDING INNER AND OUTER ANNULAR SHROUDS DEFINING AN ANNULAR GAS PASSAGE COAXIAL WITH SAID ROTOR, A PLURALITY OF FLOW DIRECTING NOZZLES SPACED CIRCUMFERENTIALLY WITHIN SAID PASSAGE AND HAVING RADIALLY INNER AND OUTER ENDS INTEGRAL WITH SAID INNER AND OUTER SHROUDS RESPECTIVELY TO SUPPORT THE SAME, AND AXIALLY EXTENDING SUPPORTING MEANS ARRANGED ANNULARLY AROUND THE AXIS OF SAID ROTOR AT A LOCATION RADIALLY INWARDLY OF SAID INNER SHROUD FOR SUPPORTING SAID SHROUDS AND NOZZLES IN PREDETERMINED ALIGNMENT WITH RESPECT TO SAID BLADES, SAID SUPPORTING MEANS BEING INTEGRAL AT ONE AXIAL END WITH SAID INNER SHROUD AND HAVING AN INTEGRAL ANNULAR PILOT MEANS AT ITS OTHER AXIAL END SEATED AGAINST THE FIRST NAMED PILOT MEANS IN HEAT CONDUCTING AND IN PREDETERMINED SPATIAL RELATIONSHIP THEREWITH, MEANS SECURING BOTH PILOT MEANS TOGETHER IN SAID RELATIONSHIP, MEANS COOPERABLE WITH SAID INNER SHROUD FOR SHIELDING SAID BEARING SUPPORT AND SUPPORTING MEANS FROM SAID HOT MOTIVE GASES TO MAINTAIN SAID BEARING SUPPORT COMPARATIVELY COOL WITH RESPECT TO SAID MOTIVE GASES, THE AXIAL LENGTH OF SAID SUPPORTING MEANS BEING DETERMINED TO EFFECT AN AXIAL TEMPERATURE GRADIENT THEREIN SUFFICIENT TO MAINTAIN THE SECOND NAMED PILOT MEANS AT APPROXIMATELY THE TEMPERATURE OF SAID FIRST NAMED PILOT MEANS AND TO DISTRIBUTE THE THERMAL STRESSES IN SAID SUPPORTING MEANS TO ENABLE THERMAL DISTORTION OF SAID INNER AND OUTER SHROUD AND NOZZLES WITH SAID BLADES WITHOUT DISRUPTING SAID PREDETERMINED SPATIAL RELATIONSHIP AND ALIGNMENT.