Schaufelblatt mit Vorderkantenkühlungsschema mit Rückschlagkompensation

Details

Veröffentlichungs-Nr.

EP3550110

Aktenzeichen

EP19167429

Anmeldetag

4. April 2019

Veröffentlichung

2. Juni 2021

Erteilung

2. Juni 2021

Rechtsraum

EP

IPC

F01D5/18

Abstract

Airfoils for gas turbine engines are provided. The airfoils (400) include an internal cold wall (414) defining a leading edge feed cavity (416) proximate a leading edge (404) and an external hot wall (412) defining a leading edge skin core cavity (410) between the external wall and the internal wall. The leading edge skin core cavity includes an inlet portion (420) and an outlet portion (422). At least one impingement hole (418) is formed in the internal wall and fluidly connects the leading edge feed cavity to the inlet portion. At least one film cooling hole (424) is formed in the external wall and fluidly connects the outlet portion to an exterior of an airfoil body (402). The impingement inlet portion has a first height (H) defined as a distance between the external wall and the internal wall for a length of the impingement inlet portion, and the film outlet portion has a second height (H) that is greater than the first height.

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete