STATOR OF GAS TURBINE Russian patent published in 2018 - IPC F01D25/24 

FIELD: engines and pumps.

SUBSTANCE: invention relates to the gas turbines stators for the aviation gas turbine engines. Gas turbine stator, in which outer casing the split honeycomb ring sectors are installed, made of two layers with supporting elements at the sector front and rear axial ends. In this invention, facing the casing sector layer is made U-shaped in plan view, the supporting elements are made in the form of separate bodies of revolution, for example, in the form of truncated cones, uniformly distributed around the circumference, and front along the gas flow supporting elements are larger than the rear supporting elements by the geometrical dimensions in 1.1…1.5 times.

EFFECT: implementation of the present invention with the said distinctive features, together with the claimed invention known features allows to reduce the gas turbine stator weight and improve reliability without the turbine efficiency compromising.

1 cl, 4 dwg