GAS-TURBINE ENGINE COMBUSTION CHAMBER

摘要

FIELD: gas-turbine engines. SUBSTANCE: combustion chamber has case accommodating annular flame tube incorporating two double layer annular shells spaced apart and arranged to confine combustion zones. Walls of each shell external to combustion zone are provided with a number of holes. Walls facing the combustion zones are made in the form of segments each being joined with external wall of shell and has rib disposed along segment outline on its side facing external wall of external or internal shell. At least one edge of segment and rib form arc-shaped ledge whose concave side faces external wall of external or internal shell. Rib made on each segment is not closed in counterflow direction in flame tube. Arc- shaped ledges are disposed along downstream rib and along joints of adjacent segments forming annular section of flame tube. Surface of each ledge facing combustion zone is aligned with extension of segment surface facing combustion zone. Ledges and ribs of each joint of adjacent segment in each annular section as well as wall of external or internal shell form open-end passage. Walls of internal and external shells external relative to combustion zone have a number of annular corrugations disposed in plane of downstream ledges or upstream edges of segments. Ribs and wall of each segment as well as wall of external or internal shell form slit passage contracting toward annular corrugation in plane of upstream edge of segment. Segment walls are solid structures. Segment surface on side facing external wall of external or internal shell has plurality of projections whose thickness does not exceed that of mentioned wall. Ribs of adjacent segments are arranged in parallel to surface of their joint. Each of annular corrugations is made on wall of external or internal shell external to combustion zone in the form of circle arcs whose concave side faces segment shells. EFFECT: enhanced service life of combustion chamber and gas-turbine engine. 1 cl, 4 dwg