BLADE PLATFORM AND FAN DISC FOR AIRCRAFT TURBINE ENGINE Russian patent published in 2020 - IPC F01D11/00 F01D5/30 

Abstract RU 2728547 C2

FIELD: machine building.

SUBSTANCE: proposed is platform (30) intended for arrangement between two adjacent blades (20) of fan (2) and comprising wall (34) of passage, lower wall (36), as well as axial and radial retaining surfaces. Wall (34) of passage defines fan air flow passage (2), lower wall (36) is main surface (36a) for tight fit to fan disc (40), and axial and radial retaining surfaces are located on two axial ends of platform (30). Radial retaining surface (38) located on platform (30) upper axial end, is radially offset from main surface (36a) of lower wall (36) in the direction in which bottom wall (36) is tightly adjacent to disc (40).

EFFECT: invention provides the least possible hub ratio at limitation of stresses on the tooth and groove of the disc.

10 cl, 6 dwg

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RU 2 728 547 C2

Authors

De Gaillard, Thomas, Alain

Boisson, Alexandre, Bernard, Marie

Dates

2020-07-30Published

2017-03-20Filed