FIELD: machine engineering.
SUBSTANCE: system of air flow control for cooling turbine bypass turbojet engine (BTJE) relates to an aircraft engine building. In the system, each single piston valve is formed, it is placed at the input side of the cavity above the piston, the output - to the side surface of the piston and communicates with subpiston chamber and the outer contour of the spring mounted therein.
EFFECT: implementation of the invention can significantly simplify the design of the cooling air flow control system for the turbine BTJE, improve reliability, and make a smooth change in the cooling air flow at all engine operating conditions.
2 cl, 3 dwg
