Gasturbinentriebwerksschaufel-Kühlkonfiguration mit Druckgefälleseparatoren

Details

Veröffentlichungs-Nr.

EP3061913

Aktenzeichen

EP16157740

Anmeldetag

26. Februar 2016

Veröffentlichung

5. Juni 2019

Erteilung

5. Juni 2019

Rechtsraum

EP

IPC

F01D5/18

Abstract

A turbine blade (64) for a gas turbine engine (20) comprises an airfoil (78; 164) including spaced apart pressure and suction side walls (86, 88) joined at leading and trailing edges (82; 84; 182) to provide an exterior airfoil surface that extends in a radial direction (R) from a platform (76) to a tip (80; 180). A cavity (94; 194) is provided between the pressure and suction side walls (86, 88) near the trailing edge (84). The cavity (94; 194) includes an interior region (96) bounded by first and second exit regions (98, 100) arranged at an angle (102) relative to one another to form a cooling configuration used to effectively turn the cooling fluid at the adjacent cooling fluid exits. The first and second exit regions (98, 100) are respectively in low and high pressure regions (104, 106) relative to one another. First and second pedestal groups (110, 112; 210, 212) respectively are arranged at the first and second exit regions (98, 100). The second pedestal group (112; 212) has first and second pedestals (114, 116; 214, 216) each terminating in an end (120, 122). The ends (122) of the second pedestals (116; 216) extend beyond the ends (120) of first pedestals (114; 214).

Anmelder

Firma

United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete