TURBINE VANE COOLER, TURBINE VANE WITH SAID COOLER, TURBINE AND AIRCRAFT ENGINE WITH SAID COOLER Russian patent published in 2011 - IPC F01D5/18 

FIELD: engines and pumps.

SUBSTANCE: vane has at least cavity surrounded by inner wall comprising cooling fins separated by gaps arranged with pitch (p) and having thickness (e). It comprises also jacket and is intervened by d-diameter bores. Every feed bore of said jacket is arranged opposite the vane inner wall point located between cooling fins. Note here that said jacket stays in contact with inner wall via several bulges on jacket surface and does not touch said fins. Aircraft engine comprises turbine vane cooler to drive cooling air toward jacket inner surface. Cooling air flows over vane inner wall via feed holes made in jacket as cooling flow with Reynolds number incorporates diameter d of feed holes as characteristics length. Every feed hole is located opposite vane inner wall point arranged between cooling fins. Note here that pitch (p), thickness (e) and Reynolds number (Re) corresponds to relations: : (1) (p/e)≥3 and (2) Re <10000.

EFFECT: higher efficiency of cooling.

10 cl, 4 dwg