Gas turbine airfoil including integrated leading edge and tip cooling fluid passage and core structure used for forming such an airfoil

US10697306B2 · kind B2 · utility

Assignee

• Siemens Aktiengesellschaft · DE

Inventors

• Ching-Pang Lee · Cincinnati, US
• Jae Y. Um · Cincinnati, US
• Gerald L. Hillier · Charlottesville, US
• Wayne J. McDonald · Charlotte, US
• Erik Johnson · Cedar Park, US
• Anthony Waywood · Cincinnati, US
• Eric Schroeder · Loveland, US
• Zhengxiang Pu · Oviedo, US

Key dates

• Filing date: Sep 18, 2014
• Grant date: Jun 30, 2020
• Expiry date: Feb 4, 2036

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2260/2212
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A core structure (10) includes a first core element (16) including a leading edge section (30), a tip section (32), and a turn section (34) joining the leading edge and tip sections (30, 32). The first core element (16) is adapted to be used to form a leading edge cooling circuit (102) in a gas turbine engine airfoil (100). The leading edge cooling circuit (102) includes a cooling fluid passage (104) having a leading edge portion (106) formed by the first core element leading edge section (30), a tip portion (108) formed by the first core element tip section (32), and a turn portion (110) formed by the first core element turn section (34). Each of the leading edge portion (106), the tip portion (108), and the turn portion (110) of the cooling fluid passage (104) are formed concurrently in the airfoil (100) by the first core element (16).