| Patent application number | Description | Published |
|---|
| 20080219835 | ABRADABLE COMPONENT FOR A GAS TURBINE ENGINE - A gas turbine engine component includes an airfoil having a radial outward end and a radial inward end. A seal member is positioned adjacent to the radial inward end of the airfoil. A tip of the radial inward end of the airfoil is coated with an abradable material. The seal member is coated with an abrasive material. | 09-11-2008 |
| 20080226879 | Low stress metallic based coating - A composition for deposition as a coating includes a matrix material having a molten fraction of between about 33% and about 90% by volume and a filler material interspersed within the matrix. | 09-18-2008 |
| 20090053422 | MASKING FIXTURE FOR A COATING PROCESS - A masking fixture for use in a coating process includes a first fixture plate for supporting a first work piece, a second fixture plate spaced from the first fixture plate for supporting a second work piece, and at least one spacer secured between the first fixture plate and the second fixture plate. | 02-26-2009 |
| 20090053554 | THERMAL BARRIER COATING SYSTEM FOR THERMAL MECHANICAL FATIGUE RESISTANCE - A composite article includes a substrate including a first metallic material having a nominal composition, and a bond coat disposed on the substrate. The bond coat includes a second metallic material having the nominal composition of the first metallic material. A ceramic top coat is disposed on the bond coat. | 02-26-2009 |
| 20090060747 | ORIENTED FIBER CERAMIC MATRIX COMPOSITE ABRADABLE THERMAL BARRIER COATING - A method of manufacturing a gas turbine engine component includes the steps of forming a ceramic workpiece having oriented ceramic reinforcement, and severing the ceramic workpiece to produce a ceramic member having a desired orientation of the ceramic reinforcement. The ceramic member is then attached to a turbine engine component as a thermal barrier layer for the turbine engine component. | 03-05-2009 |
| 20090097970 | Systems and Methods Involving Abradable Air Seals - Systems and methods involving air seals are provided. In this regard, a representative air seal for a gas turbine engine comprises a layer of ceramic exhibiting patterned surface features, wherein a substrate supporting the layer of ceramic lacks the patterned surface features. | 04-16-2009 |
| 20090110536 | Blade outer air seal with improved thermomechanical fatigue life - A blade outer air seal for a gas turbine has an abradable coating with a substantially uniform thickness during service use. Prior to being placed in service, the abradable coating has a central portion with a greater thickness than leading and trailing portions. When placed in service, the blade outer air seal is positioned so that the central portion of the abradable coating with the greater thickness is located in a blade rub path of the turbine blades. As a result of abrasion in the blade rub path, the thickness of the central portion of the abradable coating is reduced so that it becomes substantially similar to the thickness of the leading and trailing portions. | 04-30-2009 |
| 20090110831 | METHOD OF SPRAYING A TURBINE ENGINE COMPONENT - A method of spraying a component involves disposing a component near a spray coating device. The component has a first mating feature that is formed as part of the component. A first mask is disposed over a portion of the component and has a second mating feature. The first mating feature is resiliently connected to the second mating feature. The component is then sprayed. | 04-30-2009 |
| 20090130424 | CLOSED PORE CERAMIC COMPOSITE ARTICLE - A composite article includes a substrate and a thermal barrier secured to the substrate. The thermal barrier includes a plurality of closed pores within a ceramic matrix. For example, the closed pores comprise 20 vol % to 80 vol % of the thermal barrier. | 05-21-2009 |
| 20090136345 | SEGMENTED CERAMIC LAYER FOR MEMBER OF GAS TURBINE ENGINE - A turbine seal member for use in a gas turbine engine includes a turbine seal substrate having a gas-path side and a ceramic layer disposed on the gas-path side that includes a plurality of mechanical indentations. | 05-28-2009 |
| 20090136740 | ARTICLE HAVING COMPOSITE LAYER - A composite article includes a substrate and a layer attached to the substrate. The layer includes a metal phase, a first ceramic phase, and a second ceramic phase. | 05-28-2009 |
| 20090274848 | IMPINGEMENT PART COOLING - This disclosure relates to a thermal spray coating system including a table that is configured to support a component. A spray torch is configured to direct a thermal spray at a component surface. A cooling device is arranged adjacent to spray torch and configured to be in close proximity to the component surface. The cooling device includes a manifold that is connected to an air supply. The manifold has a face with multiple impingement holes less than one-eighth inch (3.1 mm) in diameter that are configured to direct cooling air on the component surface. In one example, the diameter of the impingement holes is approximately 0.059 inch (1.5 mm) and provide cooling air at a velocity of at least 400 ft per second (122 meters per second). The face is arranged within one inch (25 mm) of the component surface, in one example. Accordingly, the above cooling device uses less air and yields more consistent results in thermal coating of the component. | 11-05-2009 |
| 20090304494 | Counter-vortex paired film cooling hole design - An apparatus for use in a gas turbine engine includes a wall defining an exterior face, a first film cooling passage extending through the wall for providing film cooling to the exterior face of the wall, and a second film cooling passage extending through the wall adjacent to the first film cooling passage for providing film cooling to the exterior face of the wall. The first film passage includes a first vortex-generating structure for inducing a vortex in a first rotational direction in a cooling fluid passing therethrough, and the second film passage includes a second vortex-generating structure for inducing a vortex in a second rotational direction in a cooling fluid passing therethrough. The first and second rotational directions are substantially opposite one another. | 12-10-2009 |
| 20090304499 | Counter-Vortex film cooling hole design - An apparatus for use in a gas turbine engine includes a wall defining an exterior face, a first film cooling passage extending through the wall to a first outlet along the exterior surface of the wall for providing film cooling, and first and second rows of vortex-generating structures. The first film cooling passage defines a first interior surface region and a second interior surface region. The first row of vortex-generating structures is located along the first interior surface region, and the second row of vortex-generating structures is located along the second interior surface region. The first and second rows of vortex-generating structures are configured to inducing a pair of vortices in substantially opposite first and second rotational directions in a cooling fluid passing through the first cooling passage prior to reaching the first outlet. | 12-10-2009 |
| 20100021716 | THERMAL BARRIER SYSTEM AND BONDING METHOD - A composite article includes a substrate, a ceramic member on the substrate and a ceramic bond coat for securing the substrate and the ceramic member together. A method of securing the ceramic member and the substrate together includes pyrolyzing a ceramic precursor, such as a ceramic powder, between the substrate and the ceramic member to form the ceramic bond coat. | 01-28-2010 |
| 20100136258 | METHOD FOR IMPROVED CERAMIC COATING - A method of manufacturing an article having a ceramic topcoat includes the steps of forming the ceramic topcoat on the article, heating the ceramic topcoat, and establishing a desired thermal gradient through the ceramic topcoat to induce segmentation cracking in the ceramic topcoat. | 06-03-2010 |
| 20100159149 | APPARATUS FOR REDUCING STRESS WHEN APPLYING COATINGS, PROCESSES FOR APPLYING THE SAME AND THEIR COATED ARTICLES - A process for applying a coating to an axially split component includes the steps of installing at least one expansion or contraction device to at least one half of an axially split component; expanding at least one half to change a radius and maintain a constant curvature of at least one masked piece; applying a coating to the half; and, removing at least one expansion or contraction device from at least one half. | 06-24-2010 |
| 20100247291 | GAS TURBINE ENGINE ARTICLE HAVING COLUMNAR MICROSTRUCTURE - A gas turbine engine article includes a substrate extending between two circumferential sides, a leading edge, a trailing edge, an inner side for resisting hot engine exhaust gases, and an outer side. A gaspath layer is bonded to the inner side of the substrate and includes a metallic alloy having a columnar microstructure. | 09-30-2010 |
| 20110027573 | Lubricated Abradable Coating - A coated article has a metallic substrate. A coating layer comprises at least 33% by volume ceramic, at least 5% by volume of a lubricant selected from the group consisting of hexagonal boron nitride (hBN), clay, graphite, and mixtures thereof. The coating layer lacks a metal phase of more than 5% by volume. | 02-03-2011 |
| 20110116920 | SEGMENTED THERMALLY INSULATING COATING - A gas turbine article includes a substrate, a plurality of geometric surface features that protrude from the substrate, and a thermally insulating topcoat disposed over the plurality of geometric surface features. The thermally insulating topcoat includes segmented portions that are separated by faults that extend through the topcoat from the geometric surface features. | 05-19-2011 |
