Heat-protection element for a bearing chamber of a gas turbine

US11988106B2 · kind B2 · utility

Assignee

• MTU Aero Engines AG · DE

Inventors

• Florian Neuberger · Munich, DE
• Kaspar Wolf · Munich, DE

Key dates

• Filing date: Sep 13, 2022
• Grant date: May 21, 2024
• Expiry date: Sep 26, 2042

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2260/30
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

Described is a heat-protection element (50) for a gas turbine (10), in particular an aircraft gas turbine, the heat-protection element (50) being adapted to at least partially surround a bearing chamber (60) of the gas turbine (10) and having at least one connecting portion (52) which is disposed in an axially forward region (VB) and connectable or connected by a material-to-material bond to a protective element (54) of a seal carrier, in particular a seal carrier with a carbon seal, at least one supporting portion (58) which is disposed in an axially central region (MB) and adapted to support the heat-protection element (50) radially on the bearing chamber (60), an end portion (64) which is disposed in an axially rearward region (HB) and forms a free end (66) of the heat-protection element (50) and which is configured such that the end portion surrounds (64) the bearing chamber (60) in a contactless manner.