Lightweight triangular rotor structure for aviation rotor engine

Abstract

A lightweight triangular rotor structure for an aviation rotor engine comprises a triangular rotor made of an aluminum alloy material, a pit used for positioning a phase internal gear is formed in the triangular rotor, positioning pin holes matched with each other are formed in the bottom of the pit and the phase internal gear, and after a positioning pin is inserted into the positioning pin hole in the bottom of the pit, the phase internal gear is positioned in the pit. The phase internal gear is matched with the positioning pin and is positioned in the pit, then a screw sequentially penetrates through the phase internal gear and the triangular rotor, the screw is in threaded connection with the triangular rotor, and the end part of the screw is welded on the phase internal gear; an eccentric bearing seat is arranged in an inner cavity of the triangular rotor, one of the outer circumferential face of the eccentric bearing seat and the inner wall of the triangular rotor is provided with a protrusion, the other one of the outer circumferential face of the eccentric bearing seat and the inner wall of the triangular rotor is provided with a groove, installation grooves are formed in the two ends of the inner cavity of the triangular rotor, and elastic check rings used for abutting against the ends of the eccentric bearing seat to axially limit the eccentric bearing seat are arranged in the installation grooves. The assembling quality, the assembling efficiency and the reliability of parts are improved, and the requirement for light weight is met.

Description

technical field [0001] The invention relates to a rotary engine structure, in particular to a lightweight triangular rotor structure for an aeronautical rotary engine. Background technique [0002] At present, the connection between the triangular rotor and the phase internal gear in the domestic rotary engine is connected by 6 to 9 elastic pins. This structure has the following shortcomings: 1. There is no axial positioning, and there is a phase internal gear from the triangle during the working process of the engine. 2. At the same time, connect 6 to 9 elastic pins between the triangular rotor and the phase internal gear. Since the elastic pins are over-fit, it is difficult to install and the installation efficiency is low; 3. Due to the difficulty of installation, it may lead to Scratches the parts, causing damage to the parts, resulting in quality defects and low assembly quality; 4. The triangular rotor is usually made of cast iron, and the density of cast iron is high,...

AI Technical Summary

Problems solved by technology

[0003] In order to solve the above-mentioned technical problems of phase internal gear installation difficulty, easy detachment, low assembly quality of triangular rotor structure, and inconformity to light weight, the present invention provides an aerorotary engine The light-weight triangular rotor structure can completely eliminate the risk of the phase internal gear coming out of the triangular rotor, thereby improving the reliability of the triangular rotor engine; and effectively solving the risk of scratching parts caused by difficult installation, improving the installation quality and quality of the engine. Installation efficiency; at the same time, because the material of the triangular rotor is changed from cast iron to aluminum alloy, the density of aluminum alloy is only about one-third of that of cast iron, which greatly reduces the unbalanced rotating mass of the engine, and the matching front and rear balance weights are also reduced accordingly , about 60% lighter weight, in line with the lightweight requirements of aero-engines

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