Fixed nozzle support

Claim 1

IN A GAS TURBINE ENGINE, A ROTOR HAVING A COAXIAL SHAFT AND A PLURALITY OF PERIPHERAL BLADES, PASSAGE MEANS FOR CONDUCTING HOT MOTIVE GASES TO SAID BLADES TO DRIVE SAID ROTOR, A PLURALITY OF FLOW DIRECTING NOZZLES IN SAID PASSAGE MEANS ADJACENT SAID ROTOR AND SPACED AROUND ITS AXIS OF ROTATION, A BEARING SUPPORT, A BEARING CARRIED BY SAID SUPPORT AND HAVING SAID SHAFT JOURNALED THEREIN, SAID SUPPORT HAVING A PILOT PORTION PROXIMATE SAID BEARING AND IN THE REGION OF SAID SUPPORT HAVING AN OPERATING TEMPERATURE COMPARABLE TO THE OPERATING TEMPERATURE OF SAID BEARING, SAID PASSAGE MEANS HAVING INNER AND OUTER SHROUD MEANS SPACED BY SAID NOZZLES, SAID INNER SHROUD MEANS BEING SECURED TO SAID NOZZLES TO SUPPORT THE SAME, HEAT DISSIPATING MEANS FOR SUPPORTING SAID INNER SHROUD MEANS IN PREDETERMINED SPATIAL RELATIONSHIP WITH RESPECT TO SAID ROTOR BLADES COMPRISING SUPPORTING MEANS SECURED AT ONE END TO SAID INNER SHROUD MEANS, SAID SUPPORTING MEANS EXTENDING AXIALLY OF SAID ROTOR FROM SAID ONE END AND TERMINATING IN A PILOT PORTION SEATED AT THE FIRST NAMED PILOT PORTION OF SAID BEARING SUPPORT IN HEAT TRANSFER RELATIONSHIP THEREWITH, MEANS FOR URGING SAID SEATED PILOT PORTION INTO PREDETERMINED SPATIAL RELATIONSHIP WITH RESPECT TO THE OTHER PILOT PORTION, MEANS FOR MAINTAINING SAID BEARING SUPPORT AT A COMPARATIVELY LOW TEMPERATURE WITH RESPECT TO THE TEMPERATURE OF SAID MOTIVE GASES AND FOR MAINTAINING AN APPRECIABLE TEMPERATURE DIFFERENTIAL BETWEEN SAID ONE END AND SEATED PILOT PORTION INCLUDING MEANS FOR SHIELDING SAID BEARING SUPPORT AND SUPPORTING MEANS FROM SAID HOT MOTIVE GASES, THE AXIAL LENGTH OF SAID SUPPORTING MEANS BEING APPRECIABLY GREATER THAN ITS RADIAL THICKNESS AND BEING DETERMINED TO MAINTAIN A COMPARATIVELY SHALLOW TEMPERATURE GRADIENT ALONG ITS LENGTH AND TO APPRECIABLY RETARD THE HEAT FLOW FROM SAID ONE END TO SAID FIRST NAMED PILOT PORTION.