Gasturbinenmotorleitschaufel

Details

Veröffentlichungs-Nr.

EP4749087

Anmeldetag

26. November 2025

Veröffentlichung

27. Mai 2026

Rechtsraum

EP

IPC

F01D5/18, F01D9/04

Abstract

Gas turbine engine (10) nozzle and associated airfoil (123) designs are disclosed. An example airfoil (123) of an engine nozzle segment (140, 800) includes: a convex panel (920, 1120); a concave panel (1020); an outer band (930, 1030, 1130); and an inner band (940, 1040, 1140). The convex panel (920, 1120) includes a plurality of metering holes (910, 1010, 1110), and the airfoil (123) is characterized by the following equation, in which a convex panel (920, 1120) metering hole area (1230) (CVXA (860, 980)), inner band (940, 1040, 1140) radius (IBR), exhaust gas temperature (EGT), and engine core speed (N), are related as follows: =280∗CVXAm25x10−6m2+5x10−6IBRm1m∗3.8∗EGT°C1000°C∗NHz300Hz2 wherein 0.0000001 meters squared (m²) ≤ CVXA (860, 980) ≤ 0.000004 m², 0.213 m ≤ IBR ≤ 0.221 m, 988 degrees Celsius (C) ≤ EGT ≤ 1120 C, 306 Hertz (Hz) ≤ N ≤ 353 Hz, and 4.835 ≤ Equation 1 ≤ 281.150.

Anmelder

Firma

General Electric Company

Land

🇺🇸 USA