GAS-TURBINE ENGINE COMBUSTION CHAMBER Russian patent published in 2003 - IPC

FIELD: gas- turbine engines. SUBSTANCE: combustion chamber has case provided with fuel connection and fuel-feed pipe whose inlet end is secured in fuel connection. Annular cavity is made in fuel connection past fuel-pipe joint along fuel flow that accommodates locking rings and damping bushing in-between. Second ring along fuel flow is spaced from inlet section of annular cavity through distance equal to at least two pipe diameters. Annular cavity has shoulder in inlet part. First ring along fuel flow is abutting against this shoulder. Both rings are mounted with interference fit relative to pipe. Damping bushing is made of flexible material and installed with interference fit at fuel connection-to-pipe contacting point. Blind radial hole is made on outer surface of fuel connection in vicinity of cavity inlet section and opposing slot is provided in combustion chamber case. Cylindrical locking pin is secured in hole in a spaced relation relative to slot. Diameters of hole and pin equal half the pipe diameter and hole depth measures 0.4 to 0.6 of pipe diameter. EFFECT: enhanced operating reliability of combustion chamber due to reduced stresses. 3 cl, 3 dwg