GAS TURBINE COOLING SYSTEM Russian patent published in 2007 - IPC F01D5/08 

FIELD: mechanical engineering; gas turbine.

SUBSTANCE: proposed system is designed for cooling blades of turbine rotor provided with axially spaced wheels, blades and intermediate rings installed between wheels. Cooling system contains great number of collector segments arranged at a distance from each other circumference and near rim of said rotor. Each segment of collector is in communication with at least one channel for cooling liquid flowing into and out of said segment of collector. Each segment of collector is provided with great number of holes for communicating with through channels of turbine blades of at least one of turbine wheels. Cooling system contains also two systems of fixing supported by segments of collectors and cable of interaction with intermediate ring for fastening segments of collectors with intermediate ring to ensure against considerable axial or circular displacement relative to rotor. First of locking system includes flange of intermediate ring with one member of ring usually projecting over radius of rib and cavity and other member of said rib and said cavity on each segment of collector. Rib is made for engagement with cavity to hold segment of collector on intermediate ring to prevent considerable axial displacement. Second system of locking includes slots in one part of said intermediate ring and said segments of collectors and stops of other part of intermediate ring and segments of collector capable of engagement with walls of slots.

EFFECT: reduced overall dimensions, provision of uniform cooling flow.

9 cl, 7 dwg