Turbine blade, more particularly turbine nozzle vane, for gas tu

Details Turbine blade, more particularly turbine nozzle vane, for gas tu Turbine blade, more particularly turbine nozzle vane, for gas tu

1982-03-12

1983-08-02

Hornsby, Harvey C.

Rotary kinetic fluid motors or pumps

With passage in blade, vane, shaft or rotary distributor...

415137, 416 96A, 416241B, F01D 1102

Patent

active

043963498

ABSTRACT:
A turbine blade, more particularly a turbine nozzle vane, for a gas turbine engine, consisting of a structural metallic core enveloped at a distance by a ceramic blade jacket. Through provision a primarily highly heat-resistant, ceramic metal compound structure of the blade, the blade jacket is compressively prestressed spanwise between the blade shrouds in the inoperative condition of the turbine and where said compressive prestressing of the blade jacket, produced during assembly and which exists in the inoperative condition, is at least maintained during the operation condition by selecting for the metallic core of the blade, a material of average coefficient of thermal expansion and for the metallic inner and outer shrouds of the blade, and for the inner and outer metallic, sleeve-like components producing the axial prestress, materials of higher coefficients of thermal expansion, and for the highly thermally stressed ceramic blade jacket, a material of average coefficient of thermal expansion.

REFERENCES:
patent: 2401826 (1946-06-01), Halford
patent: 2497041 (1950-02-01), Bodger
patent: 2859935 (1958-11-01), Roesch
patent: 3540810 (1970-11-01), Kercher

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