GAS TURBINE ENGINE BLADE ASSEMBLY AND GAS TURBINE STATOR WITH SAID ASSEMBLY Russian patent published in 2012 - IPC F01D9/02 

FIELD: engines and pumps.

SUBSTANCE: turbine blade assembly comprises cases of low- and high-pressure sides with front edge, rear edge and convex or concave surface there between to form radial outer and inner edges as well as radial inner and outer deck. Every case has inner and outer flanges extending from outer and inner edges, respectively. Radial inner deck comprises multiple lengthwise grooves to receive radial inner flanges of cases of low- and high-pressure sides. Radial outer deck comprises multiple lengthwise grooves to receive radial outer flanges of cases of low- and high-pressure sides. Another invention relates to gas turbine stator comprising blade assembly and radial inner and outer decks. Blade assembly comprises blade, radial inner and outer face plugs and clamping element arranged there between. Blade extends radially between said plugs and comprises cases of low- and high-pressure sides. Clamping element supports cases of low- and high-pressure sides in definite relative orientation and relative to inner and outer face plugs. Radial inner deck comprises lengthwise groove to accommodate radial inner face plug while radial outer deck comprises lengthwise groove to receive radial outer plug.

EFFECT: simplified production of blades from ceramic composite materials.

3 cl, 4 dwg