GAS TURBINE ENGINE Russian patent published in 2009 - IPC F02C7/28 

FIELD: engines and pumps.

SUBSTANCE: invention relates to ground-application gas turbine engines designed to drive electric generator or any mechanical hardware. The proposed engine features an aft-of-compressor labyrinth and mating stator flange fixed a rigid threaded joint between the compressor straightening grid flange and ball bearing support wherein a radial flange is fitted by similar joint to support the labyrinth upper and lower flanges screwed thereon. The threaded joint bolt head is located between the labyrinth upper flange and straightening grid flange. Note here that h/L=1-3, where h is the height the compressor last blade height, L is the distance between the compressor blading section and the nearest labyrinth seal knife edge. Since the unloading chamber is separated from the compressor blading chamber by the said labyrinth seal arranged at the maximum diameter with minimum distance from the labyrinth seal knife edge to the blading section, then axial force of gas forces acting on the compressor rotor is minimum value which increases the ball bearing and engine reliability. The threaded joint bolt heads fitted in the space between the labyrinth flange and straightening grid flange serve to lock the bolts in operation and to rule out their falling out into the compressor blading section.

EFFECT: higher reliability of gas turbine engine.

2 dwg