Gasturbinenmotordüse

Details

Veröffentlichungs-Nr.

EP4749084

Anmeldetag

26. November 2025

Veröffentlichung

27. Mai 2026

Rechtsraum

EP

IPC

F01D5/14, F01D5/18, F01D9/04

Abstract

Gas turbine engine (10) nozzle and associated airfoil (123) designs are disclosed. An example airfoil (123) includes: a convex panel (920, 1120); a concave panel (1020); an outer band (930, 1030, 1130); and an inner band (940, 1040, 1140), the inner band (940, 1040, 1140) having an inner band (940, 1040, 1140) flow area (IBFA) and including a plurality of metering holes (910, 1010, 1110), the airfoil (123) characterized by the following equation, in which the IBFA, inner band (940, 1040, 1140) radius (IBR), exhaust gas temperature (EGT), and engine core speed (N), are related as follows: =IBFA1e−6m22IBR∗14∗N300HzEGT10002, wherein 0.0000002 meters squared (m²) ≤ IBFA ≤ 0.0000019 m², 0.213 m ≤ IBR ≤ 0.221 m, 988 degrees Celsius (C) ≤ EGT ≤ 1120 C, 306 Hertz (Hz) ≤ N ≤ 353 Hz, and 0.169 ≤ Equation 1 ≤ 16.643.

Anmelder

Firma

General Electric Company

Land

🇺🇸 USA