COMPRESSOR STRAIGHTENER OF GAS TURBINE ENGINE Russian patent published in 2017 - IPC F04D29/54 F01D11/00 

FIELD: engines and pumps.

SUBSTANCE: compressor straightener of gas turbine engine, comprising blades, mounted in the compressor body, inner ring, made split, in which the slots are provided around the circumference, in which the shanks of the blades are installed, the bases of which are made at an angle to the longitudinal axis of the compressor, the sealing ring is made split, which in accordance with the invention, comprises an elastic spacer made split and arranged between the sealing ring and the bases of the shanks of the blades. The surface of the elastic spacer, which contacts the bases of the shanks of the blades, is conical with respect to the longitudinal axis of the compressor. The sealing ring and the inner ring are connected to each other by means of a bead for their mutual fixation in radial and axial directions. In the sealing ring bead, located on the side of the larger diameter of a blade shank base, there are screws, the end of the rod of each contacts the side surface of the elastic spacer; in addition, at least one eye lug, provided with a fixing element, contacting with inner surface area of the inner ring.

EFFECT: increasing the maintainability and manufacturability of the straightener, reducing its weight due to the possibility of using composite materials, as well as increasing the reliability of its operation by adjusting the rigidity during engine development.

1 dwg