| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 277415000 | Having wear resistant, abradable, or ablative member | 6 |
| 20080258404 | Seal Arrangement and Method for Manufacturing a Sealing Body for a Seal Arrangement - A seal arrangement and a method for manufacturing a sealing body for a seal arrangement for a turbine engine is disclosed. The seal arrangement seals a gap between a rotor and a stator, and has at least one first seal body preferably assigned to the stator and at least one blade-shaped second seal body preferably assigned to the rotor which co-acts with the or each first seal body. The or each first seal body has a main body and a porous wear component, where the main body and the wear component have a graduated material composition. | 10-23-2008 |
| 20090200748 | ROTATING MEMBER AND METHOD FOR COATING THE SAME - A pulsed discharge is generated between tip ends of a rotating member such as a blade and a discharge electrode including a hard material such as cBN in dielectric liquid or gas by a power supply for discharge to melt the discharge electrode, and a part of the discharge electrode is attached to the tip end of the rotating member to form an abrasive coating film including the hard materials such as cBN. | 08-13-2009 |
| 20100259013 | ABRADABLE LABYRINTH SEAL FOR A FLUID-FLOW MACHINE - An abradable labyrinth seal for a fluid-flow machine seals a sealing gap between a stationary carrier ( | 10-14-2010 |
| 20120248708 | ABRADABLE LINER - A seal is provided between first and second relatively movable members. The seal comprises a liner attached to the first relatively movable member which liner is abraded by the second relatively movable member. The abradable liner comprises a metallic, open porous structure formed by fusing a metallic feedstock with an energy beam to build up sequential deposits of the fused feedstock. | 10-04-2012 |
| 20140062029 | THREADED SEAL FOR A GAS TURBINE ENGINE - A seal assembly includes a first component and a second component of a gas turbine engine. The first component has a threaded portion. The second component interfaces with the threaded portion and together the threaded portion and the second component form a seal that restricts fluid flow between a first cavity and a second cavity of the gas turbine engine. | 03-06-2014 |
| 20160195137 | ABRADABLE SEAL AND SEALING ARRANGEMENT | 07-07-2016 |
