GAS TURBINE ENGINE COMPRESSOR STRAIGHTENER BLADES Russian patent published in 2018 - IPC F01D25/24 F01D9/04 F04D29/60 F04D29/54 

FIELD: engines and pumps.

SUBSTANCE: invention relates to the field of engine building, in particular to the gas turbine engine compressor straightener blades. In the gas turbine engine compressor straightener blades, comprising an outer ring, made dismountable and fixed in a compound housing, inner ring and a sealing ring, made dismountable, blades installed in the slots, made circumferentially in the outer and inner rings, respectively, wherein the outer and inner rings are made conical relative to the gas turbine engine compressor longitudinal axis, which smaller bases are directed to the opposite sides, according to the present invention, on the regions of the blades located above the outer ring and under the inner ring, in each of which by an elastic element is mounted contacting by both sides of the blade with the outer ring outer surface or the inner ring inner surface, respectively, at that, any of the resilient elements is fixed in the transverse slot by means of a locking member mounted therein in contact with its end face.

EFFECT: increase in the straightener blades maintainability and manufacturability, reducing its weight due to the possibility of using composite materials, as well as increase in the its operation reliability by adjusting the stiffness characteristics in the process of engine development.

1 cl, 4 dwg