STRUCTURE FOR A STATIONARY COOLED TURBINE VANE

Assignee

SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE METEUR D'AVIATON S.N.E.C.M.A.

Filed

Mar 13, 1985

Granted

Nov 26, 1996

Location

VAUX LE PENIL FR

Abstract

An improved turbine vane structure is disclosed which enables more effective cooling and the reduction of temperature gradients along its length. The hollow interior of the vane is divided into three separate cavities, two upstream cavities and a downstream cavity. The downstream cavity is partially filled with a body of porous, heat transfer material. Cooling air flows through the downstream cavity in a direction counter to the hot gases passing over the exterior surface of the vane so as to increase the heat exchange properties. The two upstream cavities lie adjacent to each other and are supplied with cooling air from opposite directions to achieve a counterflow, heat exchange effect. Several sets of cooling holes are provided through the vane wall to communicate with the interior cavities and supply cooling air to the exterior surface of the vane.

Source: Google Patents