Gas turbine blade and method for producing such blade

US11396817B2 · kind B2 · utility

Assignee

• Siemens Energy Global GmbH & Co. KG · DE

Inventors

• Daniel M. Eshak · Orlando, US
• Susanne Kamenzky · Berlin, DE
• Andrew S. Lohaus · Berlin, DE
• Daniel Vöhringer · Berlin, DE
• Samuel R. Miller, Jr. · Port St. Lucie, US

Key dates

• Filing date: Jan 8, 2019
• Grant date: Jul 26, 2022
• Expiry date: Apr 17, 2039

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2260/941
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A gas turbine blade having a casted metal airfoil, the airfoil has a main wall defining at least one interior cavity, having a first side wall and a second side wall, which are coupled to each other at a leading edge and a trailing edge, extending in a radial direction from a blade root to a blade tip and defining a radial span from 0% at the blade root to 100% at the blade tip. The main airfoil has a radial span dependent chord length defined by a straight line connecting the leading edge and the trailing edge as well as a radial span dependent solidity ratio of metal area to total cross-sectional area. Solidity ratios in a machined zone of the airfoil from 80% to 85% of span are below 35%, in particular all solidity ratios in the zone.