US 11,988,106 B2
Heat-protection element for a bearing chamber of a gas turbine
Florian Neuberger, Dorfen (DE); and Kaspar Wolf, Munich (DE)
Assigned to MTU Aero Engines AG, Munich (DE)
Filed by MTU Aero Engines AG, Munich (DE)
Filed on Sep. 13, 2022, as Appl. No. 17/943,355.
Claims priority of application No. 102021124357.2 (DE), filed on Sep. 21, 2021.
Prior Publication US 2023/0184134 A1, Jun. 15, 2023
Int. Cl. F01D 25/08 (2006.01); F01D 5/08 (2006.01); F01D 25/12 (2006.01); F01D 25/14 (2006.01); F01D 25/16 (2006.01)
CPC F01D 25/08 (2013.01) [F01D 5/087 (2013.01); F01D 25/125 (2013.01); F01D 25/14 (2013.01); F01D 25/145 (2013.01); F01D 25/16 (2013.01); F01D 25/162 (2013.01); F05D 2240/15 (2013.01); F05D 2260/231 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A gas turbine comprising:
at least one bearing chamber; and a heat-protection element for a gas turbine, the heat-protection element adapted to at least partially surround the bearing chamber and including:
at least one connecting portion disposed in an axially forward region and connectable or connected by a material-to-material bond to a protective element of a seal carrier,
at least one supporting portion disposed in an axially central region and adapted to support the heat-protection element radially on the bearing chamber;
an end portion disposed in an axially rearward region and forming a free end of the heat-protection element and configured such that the end portion surrounds the bearing chamber in a contactless manner;
wherein the gas turbine is an airline gas turbine.