Patent application number | Description | Published |
20080203671 | Reverse flow tolerant brush seal - In accordance with the present application, a fluid seal | 08-28-2008 |
20080217859 | Speed fit brush seal - A seal assembly includes a component of a gas turbine engine having a circumferential surface, a first knife edge seal, a second knife edge seal, and a brush seal assembly. The first knife edge seal and the second knife edge seal extend radially from the circumferential surface of the component and form a gap at the circumferential surface of the component between the first knife edge seal and the second knife edge seal. The brush seal assembly is positioned within the gap between the first knife edge seal and the second knife edge seal and is attached to the circumferential surface of the component. | 09-11-2008 |
20080315529 | EASE OF ASSEMBLY AID FOR BRUSH SEAL - A brush seal assembly is formed of a bristle array receiving at least one housing member. Alignment structures are formed on the housing and bristle assembly to ensure that the bristle assembly will be properly positioned in a working environment. | 12-25-2008 |
20090000101 | Methods for Repairing Gas Turbine Engines - Methods for repairing gas turbines are provided. A representative method includes: identifying an affected area of a surface of a component of the gas turbine, the surface of the component defining a portion of a gas flow path through the gas turbine; applying an epoxy-based filler to the affected area; curing the epoxy-based filler; and blending the epoxy-based filler with the surface of the component. | 01-01-2009 |
20090035477 | Masks and Related Methods for Repairing Gas Turbine Engine Components - Masks and related methods for repairing a gas turbine engine components are provided. A representative method includes using a self-coiling strip of material as a mask during application of a coating to a surface of the component. | 02-05-2009 |
20090064500 | METHOD OF REPAIRING A TURBINE ENGINE COMPONENT - The inventive method involves the inspection of a turbine engine. A damaged component of the turbine engine is identified. Portions of the turbine engine component are removed from the damaged area to accommodate an overlay. The overlay is sized smaller than the turbine engine component. The overlay is then placed in a location previously occupied by the removed portion and attached to the turbine engine component. | 03-12-2009 |
20090208330 | SEALING ASSEMBLY FOR A TURBINE ENGINE - A sealing assembly for a turbine engine has a brush configured to provide an air seal between an outer air seal segment and a blade. A support is provided for the brush and is configured for attachment to the outer air seal segment. The support is a flexible planar carrier having a first side and a second side. The brush extends from the first side while the second side is for attachment to the outer air seal segment. The flexible planar carrier has a stiffness less than a stiffness of the outer air seal segment. | 08-20-2009 |
20110110783 | Trunnion hole repair utilizing interference fit inserts - A vane shroud for a gas turbine engine has a cylindrical shaped body and a hole arranged at a circumference of the body. The hole is for receiving a trunnion from a variable vane. A counterbore is arranged concentrically around the hole on a radially inward facing surface of the body, and receives a trunnion hub from the variable vane. A shrink-fit insert is seated into the counterbore such that the trunnion hub is provided with a contact surface, and the shrink-fit insert is secured to the shroud through an interference fit. | 05-12-2011 |
20130001883 | REPAIRABLE DOUBLE SIDED BRUSH SEAL - A brush seal includes a plurality of bristles aligned in parallel to form a brush pack having a first end and a second end, and a joint securing the brush pack together. The joint is located centrally between the first end and the second end such that both the first end and the second end of the brush pack can form a sealing surface. | 01-03-2013 |