| 摘要 |
FIELD: mechanical engineering; gas-turbine engines. SUBSTANCE: rotary engine has housing, turbine, axial-flow compressor, combustion chambers, and fuel system. Blades of axial-flow compressor rigidly mounted on shaft in head portion of split housing are made three-stepped, each step has different angle of inclination relative to longitudinal axis of compressor. Guide step of blade located at inlet forms angle up to 40-50 degrees, middle compression step has angle from 0 to 10 degrees, and discharge step, up to 70-80 degrees. Compressor surface is divided into several similar sectors. Gradual elongation of guide step of each blade is provided within the limits of each sector which contributes to forming air in tale space. Thickness of compression step of each blade gradually increases towards discharge step whose thickness remains constant and its side planes form interblade slot channels with side planes of adjacent blades. Working rotor is rigidly mounted on the same shaft behind the compressor. Rotor first stage has cylindrical surface changing into second stage on which longitudinal slots of triangular shape with right angle are made. Angle of inclination of slots in third stage is 15 degrees relative to axis of rotation. Spaces are made on inner cylindrical surface of working rotor housing. Axes of spaces are arranged at angle of 60 degrees relative to radial axial plane passing through point of intersection of plane axis with pitch circle being simultaneously inner diameter of rotor housing. Axes of spaces which are initially square to one of planes of triangular slots of rotor are also axes of combustion chambers installed in spaces. Holes are made on end face split surface of rotor housing to communicate rotor housing spaces with high pressure space of compressor. Through holes are made also in rear wall of rotor housing. EFFECT: increased head pressure characteristics of compressor, increased service life and reliability of engine, simplified design and facilitated servicing. |
