TURBINE ROTATING BLADE Russian patent published in 2018 - IPC F01D5/18 

FIELD: machine building.

SUBSTANCE: turbine rotor blade for gas turbine engine contains aerodynamic part. Aerodynamic part comprises a tip at an outer radial end. Tip has a projecting edge that defines the tip cavity. Projecting edge comprises a circumscribing microchannel. Aerodynamic part has an increased pressure sidewall and reduced pressure sidewall, which are connected together at the leading edge and trailing edge of the aerodynamic part. Increased pressure sidewall and reduced pressure sidewall pass from blade tang to the tip and limit the chamber of the aerodynamic part. Tip comprises a plate, and the projecting edge is located near the tip plate or on its periphery. Projecting edge has an inner surface facing inwardly towards the tip cavity and an outer surface. Circumscribing microchannel is a microchannel, which extends around at least a greater part of the length of the inner surface of the projecting edge. Blade also comprises a feed microchannel passing through the tip plate and a portion of the projecting edge. Feed microchannel has an upstream end that is located on the tip plate, and a downstream end that is located on the projecting edge. Upstream end of the circumscribing microchannel communicates with the coolant passageway, which passes through the plate of the tip to the chamber of the aerodynamic part, and the downstream end is in fluidly connects to said circumscribing microchannel.

EFFECT: invention is aimed at increasing efficiency of aerodynamic part tip of working blade.

20 cl, 15 dwg