Patent · US Active

Cooled turbine runner, in particular for an aircraft engine

US10436031B2 · kind B2 · utility

0Cited by

41References

8Claims

0Family size

Assignee

ROLLS-ROYCE DEUTSCHLAND LTD & CO KG · DE

Inventors

Joana Negulescu · Berlin, DE
Jens Taege · Berlin, DE
Dimitrie Negulescu · Berlin, DE

Key dates

Filing date	Jul 19, 2016
Grant date	Oct 8, 2019
Priority date	—
Expiry date	Dec 12, 2037

Classification

Technology area (CPC Y)Emerging Cross-Sectional Technologies
CPC primaryY02T50/60
WIPO fieldEngines, pumps, turbines
WIPO sectorMechanical engineering

Abstract

A cooled turbine runner, in particular a high-pressure turbine runner for an aircraft engine, with turbine blades that are radially arranged at a circumferential surface of a rotor disk, wherein respectively one turbine blade with a profiled blade root is inserted into a correspondingly profiled disk finger groove at the circumferential surface of the rotor disk,and wherein a cooling device is provided with at least one cooling air supply channel that extends at least substantially axially and at least over a part of the axial length of the blade root, and with at least one cooling channel that branches off from the same and extends in the interior of the turbine blade up to an outlet opening at its surface. At an inflow side of the blade root, a plug with a cooling air passage is arranged in the cooling air supply channel, wherein the cooling air passage has a geometry that forms a micro-compressor.

Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.