Rolls-royce Corporation

Siemens Westinghouse Power Corporation

Graham Mark Upton

William E North

Kent Goran Hultgren

Thomas Walter Zagar

Rez Manzoori

Michael J L Percival

Stephen Humphrey Robbins

A vane assembly for use within a gas turbine engine has a main vane portion with an internal cavity A cavity insert is located within the cavity close to the wall to define transpiration cooling paths. Cooling air leaves the insert through apertures directed at the wall to produce impingement cooling. The transpiration cooling paths are extended back to the trailing edge by means of a fairing The use of a fairing in addition to the insert allows more complicated cavity shapes to be filled.

Vane assembly

A turbine blade with a cooling air flow path specifically directed toward cooling the platform portion of the blade root. Cooling air passages are formed in the blade root platform just below its radially outward facing surface on an overhanging portion of the platform opposite the convex surface of the blade airfoil. Each of these passage extends radially outward from an inlet that receives a flow of cooling air, and then extends through the platform. Cavities are formed in a radially inward facing surface of an over hanging portion of the platform opposite the concave surface of the blade airfoil. An impingement plate directs cooling air as jets into these cavities. A passage is connected to the cavities and directs this cooling air through the overhanging portion of the platform opposite the concave surface.

Gas turbine blade platform cooling concept

Growing community of inventors

Derby, United Kingdom

Graham Mark Upton