Gasturbinenmotorturbinenschaufelablenkplatte und Schlangenförmiger Kühlkanal

Details

Veröffentlichungs-Nr.

EP3054094

Aktenzeichen

EP16154523

Anmeldetag

5. Februar 2016

Veröffentlichung

4. April 2018

Erteilung

4. April 2018

Rechtsraum

EP

IPC

F01D5/18

Abstract

An airfoil (78) for a gas turbine engine includes pressure and suction side walls (90, 92) joined to one another at leading and trailing edges (82, 84). The pressure and suction side walls (90, 92) surround an airfoil cavity (96) and provide an exterior airfoil surface (94). A baffle (98) is arranged in the airfoil cavity (96) and includes a supply hole (120). Ribs (100-108) extend from the pressure and suction side walls (90, 92) into the airfoil cavity (96) and engage the baffle (98). The ribs (100-108) are configured to provide a serpentine cooling passage (112) between the baffle (98) and at least one of the pressure and suction side walls (90, 92). The serpentine cooling passage (112) has first and second passes (116, 118) joined by a bend (117). The ribs (100-108) form a film cooling cavity (110) between the first and second passes (116, 118). The supply hole (120) fluidly connects the baffle (98) to the film cooling cavity (110). Film cooling holes (122) extend through at least one of the pressure and suction side walls (90, 92). The film cooling holes (122) are in fluid communication with the film cooling cavity (110).

Anmelder

Firma

United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete