METHOD AND SYSTEM FOR ADJUSTMENT OF CLEARANCE AT TURBINE ROTOR BLADE EDGES Russian patent published in 2015 - IPC F01D11/24

Abstract RU 2566510 C2

FIELD: engines and pumps.

SUBSTANCE: invention relates to control over clearance between the edges of aircraft gas turbine blades and outer housing turbine shroud. Valve is arranged in air channel opens to cool the turbine shroud at high rpm phase (TO+CL) corresponding to aircraft takeoff and climb phases and at rated rpm phase (CR) following after high-rpm phase and corresponding to aircraft cruising phase. Invention covers also the system to implement described method.

EFFECT: simplified design, decreased weight.

10 cl, 4 dwg

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RU 2 566 510 C2

Authors

Bonno Dam'En

Kruamari Mark

Denes Frank Rozhe Deni

Golli Brjuno Rober

Dates

2015-10-27—Published

2011-06-01—Filed