Hitzeschildanordnung zur Verwendung in einem Flugzeugtriebwerk

Details

Veröffentlichungs-Nr.

EP4144648

Aktenzeichen

EP22180057

Anmeldetag

21. Juni 2022

Veröffentlichung

29. Oktober 2025

Erteilung

29. Oktober 2025

Rechtsraum

EP

IPC

B64D29/06B64D29/02F16B5/02B64D27/40// F16B5/04F16B43/00

Abstract

A heat shield assembly for use with an aircraft engine. The heat shield assembly includes a structural member, a heat shield panel adapted for exposure to aircraft engine exhaust, an index joint coupling the heat shield panel to the structural member in a fixed positional location, and a plurality of slip joints coupling the heat shield panel to the structural member. Each slip joint includes at least one wear buffer coupled to the heat shield panel, and a slip fastener insertable through a slip joint hole in the heat shield panel with a clearance fit. A gap defined by the clearance fit is sized to provide a tolerance for expansion and contraction of the heat shield panel relative to the fixed positional location, and the at least one wear buffer is engageable by the slip fastener during expansion and contraction of the heat shield panel.

Anmelder

Firma

The Boeing Company

Land

🇺🇸 USA

Fachgebiete