Alliedsignal Inc.

Lloyd L Clevenger

Robert Clark Rowan, Jr

John D Sullivan

A turbine engine includes adjacent compressor and turbine sections and an interstage seal assembly interposing therebetween in cooperation with a rotor assembly of the engine to inhibit leakage of pressurized air between the sections. The interstage seal assembly includes an annular wall portions at its outer perimeter cooperating with a housing of the engine and at its inner perimeter sealingly cooperating with the rotor assembly. The wall portions of the interstage seal includes nested conical sections of opposite axial dispositions which cooperatively resist both thermal and pressure differential induced distortion of the seal assembly.

Turbine engine interstage seal

An improved variable geometry diffuser assembly is provided. This assembly includes a variety of features that reduce the leakage and improve the precision within the assembly. These features include: sealing disks mounted to the vane; cantilevered vanes mounted for rotation to coolside diffuser wall only, thereby reducing the effects of thermal growth on the assembly; and self lubricating, non-metallic bushings for supporting the various components in the assembly thereby reducing friction and any need for lubrication. Each vane is coupled to a single unison ring through an arm member also employing non-metallic bushings.

Variable geometry diffuser assembly

A turbine engine includes axially adjacent compressor and turbine rotors which define a groove therebetween. Into the groove between the rotors radially extends an annular interstage seal assembly. The seal assembly includes a thermally insulative cellular wall structure which resists thermal and pressure included distortions. At its radially inner extent the cellular wall defines a seal structure in cooperation with the rotors, and also carries heat shield members on an axial fore disposed toward the turbine rotor.

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Phoenix, AZ, United States of America

Lloyd L Clevenger