Gasturbinentriebwerkheckkonus

Details

Veröffentlichungs-Nr.

EP3267023

Aktenzeichen

EP17180589

Anmeldetag

10. Juli 2017

Veröffentlichung

6. Mai 2020

Erteilung

6. Mai 2020

Rechtsraum

EP

IPC

F02K1/82// F02K1/08F02K1/38F01D25/30

Abstract

The invention is related to tail cones (46) for gas turbine engines (10) including a tip section (64) comprising an apex (72) and an inner radius (74), an outer sheet (50) converging to the tip section (64), wherein the outer sheet (50) comprises a plurality of film cooling openings (58) for cooling the outer sheet (50) which is exposed to a hot exhaust gas (62). A cooling opening (58) nearest the apex (72) is located between 0.25 mm (0.010 inches) and 3.175 mm (0.125 inches) from the inner radius (74). The tail cone (46) further comprises an inner sheet (48) comprising cooling holes (54) for cooling an inner surface (56) of the outer sheet (50) by impingement. The inner sheet (48) is fixed to outer sheet (50) via a locating portion (66). The combination of impingement and film cooling improves durability of the tail cone (46).

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete