Kühlungsverfahren für die Eintrittskante einer Turbinenschaufel einer Gasturbine

Details

Veröffentlichungs-Nr.

EP3000970

Aktenzeichen

EP14186560

Anmeldetag

26. September 2014

Veröffentlichung

12. Juni 2019

Erteilung

12. Juni 2019

Rechtsraum

EP

IPC

F01D5/18

Abstract

A turbine blade (12) of a gas turbine comprises a radially extending airfoil (29) with a suction side (26) and pressure side (27), which extend each in axial direction between a leading edge (24) and a trailing edge of said airfoil (29), whereby said leading edge (24) is cooled by means of impingement cooling with rows of radially distributed jets of a cooling medium impinging on the inner side of said leading edge (24), and whereby said row of radially distributed jets is generated at an internal web (16), which divides the hollow interior of the airfoil (29) into first and second cavities (15, 17), with the second cavity (17) being arranged at said leading edge (24). An enhanced cooling is achieved by said internal web (16) comprising two rows of radially distributed cooling medium supply holes (18, 19), through which cooling medium enters said second cavity (17) in form of impinging jets, whereby said cooling medium supply holes (18, 19) are oriented such that the directions of said jets of one row cross the directions of said jets of the other row.

Anmelder

Firmen

Ansaldo Energia Switzerland AG
General Electric Technology GmbH
ALSTOM Technology Ltd

Land

🇨🇭 Schweiz

Fachgebiete