Brennkammerwand mit Kühllöchern mit Abgestufter Stromaufwärts-Seitenwand

Details

Veröffentlichungs-Nr.

EP4793544

Anmeldetag

17. Februar 2026

Veröffentlichung

19. August 2026

Rechtsraum

EP

IPC

F23R3/00, F23R3/06

Abstract

Apparatus and associated methods relate to geometry of cooling holes (18) in a combustion liner (10) for a gas turbine engine. The combustion liner (10) includes a base-alloy substrate (12) having a bottom surface (22) and a top surface (26), a thermal barrier coat (TBC) metallic layer (14) on the top surface (26) of the base-alloy structure (12), and a TBC ceramic layer (16) on the TBC metallic layer (14). The cooling holes (18) are formed at oblique angles to the top surface (26) of the TBC ceramic layer (16), thereby forming oval-characteristic exit apertures (24) at the top surface (26) of the TBC ceramic layer (16). The oval-characteristic exit apertures (24) define a long axis (L) and a short axis (S). The long axis (L) extends between an upstream side (30) and a downstream side (32) and the short axis (S) extends between opposite lateral sides, thereby defining an upstream sidewall (32) and a downstream sidewall (34). The upstream sidewalls (32) have stepped sidewall profiles in the cooling holes (18).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete