MOUNTING STRUCTURE OF NOZZLE GUIDE VANES AT INLET CHANNEL OF RADIAL GAS TURBINE OF ENGINE Russian patent published in 2015 - IPC F01D9/04 

FIELD: machine building.

SUBSTANCE: device to transfer gaseous combustion products to a turbine comprises several guide vanes of a nozzle, a pair of ring-shaped side walls with nozzle guide vanes being set in-between, a pair of supports distanced from each other, and a unit to fix the side walls and the connected nozzle guide vanes between the supports. The fixing unit consists of several bolt unit assemblies passing in the axial direction through ring supports, holes in the side walls and slots in the nozzle guide vanes. Every hole and slot in the radial direction has the inner diameter greater than the outer dimension of the bolt unit assembly, the inner dimension has the value corresponding to the travel of the side walls and the nozzle guide vanes in respect to the supports in the radial direction at thermal expansion and compression. An assembly unit of the nozzle guide vanes comprises several guide vanes of the nozzle, a pair of side walls of a ring-shaped nozzle with the guide vanes installed in-between, several hollow inserts and several pins. The hollow inserts serve for the rigid connection of opposite axial ends of every guide vane to the adjacent side wall. The pins serve for the connection of one of the axial ends of every guide vane to the adjacent side wall. Several through holes formed inside the inserts pass through both side walls and the guide vanes in the axial direction. The through holes are designed for mounting of the assembly unit of the nozzle guide vanes on an engine with the possibility of replacement, with the usage of several bolt unit assemblies and providing for the radial movement of the assembly unit of the nozzle guide vanes in respect to the bolt unit assemblies at thermal expansion and compression. At configuring the central section of a gas turbine engine, one ring support element is rigidly fixed to the stationary structural element of the engine. The turbine housing is attached to another support element in an adjustable manner to fix it. The ring assembly unit of the nozzle guide vanes is set and fixed between the support elements mounted at a certain distance from each other.

EFFECT: group of inventions allows for the reduction of the heat deformation of the gas turbine engine.

15 cl, 10 dwg