Brennkammer mit Geschirmten Auskleidungen in einem Turbinenmotor

Details

Veröffentlichungs-Nr.

EP4800298

Anmeldetag

15. Januar 2026

Veröffentlichung

2. September 2026

Rechtsraum

EP

IPC

F23R3/00, F23R3/06

Abstract

A combustor (80, 300, 400) for a turbine engine (10) includes a dome (86, 306), an outer liner (82, 302) having a plurality of outer liner holes (302A) and one or more outer liner dilution holes (302B), an inner liner (84, 304) having a plurality of inner liner holes (304A) and one or more inner liner dilution holes (304B), the dome (86, 306), the outer liner (82, 302) and the inner liner (84, 304) defining a combustion chamber (88, 308), an outer baffle (312, 412) connected to the outer liner (82, 302) to define an outer cavity (316, 416) therebetween, the outer baffle (312, 412) including a plurality of outer baffle holes (312A, 412A), and an inner baffle (314, 414) connected to the inner liner (84, 304) to define an inner cavity (318, 418) therebetween, the inner baffle (314, 414) including a plurality of inner baffle holes (314A, 414A). The one or more outer liner dilution holes (302B) and the one or more inner liner dilution holes (304B) are configured to provide pressure drop across the outer liner (82, 302) and the inner liner (84, 304) to enhance penetration of a jet airflow (328, 332) into the combustion chamber (88, 308).

Anmelder

Firma

General Electric Company

Land

🇺🇸 USA

Fachgebiete