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Details

Veröffentlichungs-Nr.

EP4343116

Aktenzeichen

EP23199539

Anmeldetag

25. September 2023

Veröffentlichung

17. April 2024

Rechtsraum

EP

IPC

F01D5/14F01D5/18F01D9/06

Abstract

A turbine engine airfoil element has a plurality of main body passageways (210, 212, 214, 216, 218, 220) along a camber line (190) and having two or more chordwise distributed protuberant portions (240, 242, 246, 248, 22, 254, 256) with necks (244, 250, 258, 260) between the protuberant portions (240...256). A plurality of skin passageways (310, 312, 314, 316, 318, 320; 322, 324, 326, 328, 330, 332) include: at least one first skin passageway (312, 316; 324, 328) each nested between a first of the pressure side (132) and the suction side (134) and two adjacent main body passageways (212, 214, 216); and a plurality of second skin passageways (310, 314, 318, 320; 322, 326, 330, 332) each nested between first of the pressure side (132) and the suction side (134) and two said protuberant portions (240...256) of a corresponding main body passageway (212, 214, 216).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete