Gas turbine component with reduced cooling air requirement

US7967568B2 · kind B2 · utility

Assignee

• SIEMENS ENERGY, INC. · US

Inventors

• John P. Dalton · Wellington, US
• Tilmann Auf Dem Kampe · Lewes, US
• Frank Maichle · Mellingen, CH
• Rex A. Smith · Boise, US
• Stuart Bishop · Stuart, US
• Stefan Irmisch · Untersiggenthal, CH

Key dates

• Filing date: Sep 21, 2007
• Grant date: Jun 28, 2011
• Expiry date: Dec 19, 2030

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2300/60
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

Introducing a plurality of geometrically shaped members (27) into a cooling passage (16) of a gas turbine airfoil (10) will effectively reduce the cross-sectional flow area while simultaneously retaining a sufficiently thick external contour desired for proper gas path aerodynamic behavior. Small cooling sub-passages (18a, 18b) formed around the geometric members will create a preferentially higher coolant flow rate and heat transfer coefficient at the cooled surface (14) when compared to the interior of the cavity. The geometric shapes may be metal or ceramic spheres retained in the cooling cavity by a retaining structure such as a screen grid (30) or perforated plate (32). The openings (34) in the retaining structure may be unevenly distributed to preferentially allow more coolant to enter the cavity proximate the cooled walls. The size/shape of the geometrically shaped members may be varied to achieve a desired heat transfer coefficient along the cooled wall surface (17).