Doppelt Gespeiste Schaufelspitze

Details

Veröffentlichungs-Nr.

EP3196414

Aktenzeichen

EP17152351

Anmeldetag

20. Januar 2017

Veröffentlichung

28. November 2018

Erteilung

28. November 2018

Rechtsraum

EP

IPC

F01D9/02F01D25/12F04D29/32F04D29/54F04D29/58F01D5/18

Abstract

An airfoil (201; 301; 401; 501) of a gas turbine engine is provided including a leading edge (212; 312) extending in a radial direction, a tip (232; 332; 432; 532) extending in an axial direction from the leading edge, a first rib (232; 332; 432; 532) extending radially within the airfoil, the leading edge and the first rib defining a leading edge cavity (220; 320; 420; 520) within the airfoil, a second rib (234; 334), the second rib and the first rib defining a serpentine cavity (228; 328; 428; 528) therein, a third rib (236; 336; 436; 536) extending axially within the tip, a flag tip cavity (226; 326; 426; 526) defined by the third rib, the leading edge, and the tip, the leading edge cavity fluidly connected to the flag tip cavity, and a bypass aperture (240; 340; 440; 540) formed between the first rib and the third rib, the bypass aperture configured to fluidly connect the serpentine cavity with the flag tip cavity.

Anmelder

Firma

United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete