SYSTEM FOR SECURING AUXILIARY EQUIPMENT TO AIRCRAFT GAS TURBINE ENGINE Russian patent published in 2019 - IPC F02C7/20 

FIELD: aircraft; machine building.

SUBSTANCE: invention relates to aircraft engineering, particularly, to systems for securing auxiliary equipment to aircraft gas turbine engine. System for attachment of auxiliary equipment to aircraft gas turbine engine comprises pylon with power beam, fairing secured thereon and pylon attachment means to aircraft body mechanically connected therewith. Power beam is made in the form of spatial frame frame located along length along engine axis, having end walls, mating surfaces, conjugated with docking surfaces of power housing elements of gas turbine engine and auxiliary equipment, and its attachment to power housing elements of gas turbine engine and auxiliary equipment located in front and rear parts of frame frame. Carcass frame is rectangular in cross section and is equipped with transverse power partition, which limits front and rear parts of frame frame, structural housing elements of gas turbine engine and auxiliary equipment are circular and equipped with additional means of attachment to aircraft body, located on opposite sides of structural housing elements relative to their mating surfaces. Matching surfaces of frame frame, coupled with docking surfaces of gas turbine engine and auxiliary equipment, are located on opposite sides of rear part of frame frame, attachment means of which to power housing elements of gas turbine engine and auxiliary equipment are threaded. Fasteners of front part of frame frame are made in form of two cylindrical trunnions with axes oriented along length of frame frame, and two brackets with couplings for trunnions, one of which is fixed on power housing of gas turbine engine, and the other one – on the power housing element of the auxiliary equipment, the cylindrical trunnion of the attachment facility of auxiliary equipment is fixed on the transverse power partition wall of the frame frame, and the cylindrical trunnion of the fastener of the gas turbine engine is fixed on the end wall of the front part of the frame frame.

EFFECT: invention allows improving reliability of auxiliary equipment attachment system to aircraft gas turbine engine.

1 cl, 6 dwg