| 摘要 |
FIELD: engines and pumps. ^ SUBSTANCE: gas turbine blades seat on cylindrical bush to rotate and axially displace thereon, fitted on conical ledge of bearing circular wall. Wall central part represent two-wall piston with spring fitted between aforesaid walls and resting upon circular ledge of cylindrical barrel rigidly fixed on the shaft. Circular wall and part of peripheral turbine vanes are made integral on barrel rear side to allow another part of aforesaid turbine vanes to enter therein. Said another part of turbine vanes is made on inner surface of load-bearing circular wall. Peripheral turbine vane outer parts are constrained by circular webs arranged on intermediate load-bearing turbojet engine housing and load-bearing circular wall. In compliance with total pressure in fuel lines, fuel makes cylindrical bush moves axially to vary annular gap of gas flow pass into gas turbine vane zone. ^ EFFECT: controlled power take-off. ^ 7 dwg |
