Patent application number | Description | Published |
20090013695 | Floatwell Panel Assemblies and Related Systems - Floatwall panel assemblies and related systems are provided. A floatwall panel assembly includes a panel formed of porous ceramic material, the porous ceramic material exhibiting a porosity gradient along at least one of a length, a width and a depth of the panel, the panel lacking a substrate, formed of a material other than porous ceramic material, for supporting the porous ceramic material. | 01-15-2009 |
20090101787 | Gas Turbine Engine Systems Involving Rotatable Annular Supports - Gas turbine engine systems involving rotatable annular supports are provided. In this regard, a representative support assembly for a gas turbine engine includes: a rotatable member having a first end located about a first annulus; and a stationary member located about a second annulus; the first end of the rotatable member being rotatably coupled with the stationary member, with at least a portion of the first annulus being coextensive with at least a portion of the second annulus, the first end being operative to rotate locally with respect to a corresponding portion of the stationary member. | 04-23-2009 |
20090169368 | BLADE OUTER AIR SEAL - A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. The body comprises a metallic member and a ceramic member. The ceramic member and metallic member are joined along the base portion with the ceramic member inboard of the metallic member. | 07-02-2009 |
20100077764 | Structures with adaptive cooling - Disclosed are exemplary structures with adaptive cooling and methods of adaptively cooling structures. A liner is affixed to a support and the liner deflects away from the support when exposed to a localized hot spot in a hot fluid stream. The liner deflection creates a chamber between the liner and support, allowing cooling air to impinge against the liner, thus mitigating the effects of the hot spot. By providing impingement cooling only where needed, the amount of air needed for cooling is reduced. | 04-01-2010 |
20100176185 | WELDING REPAIR METHOD FOR FULL HOOP STRUCTURES - A unique heat treat method for relieving stresses caused by a repairing weld joint in a full hoop part heat treats locally, at the location of the weld joint, and at a diametrically opposed location. By providing the diametrically opposed heat treat location, the present invention relieves stresses caused by the weld joint, without creating any additional residual stress in the weld joint. | 07-15-2010 |
20100178165 | WELDING REPAIR METHOD FOR FULL HOOP STRUCTURES - A unique heat treat method for relieving stresses caused by a repairing weld joint in a full hoop part heat treats locally, at the location of the weld joint, and at a diametrically opposed location. By providing the diametrically opposed heat treat location, the present invention relieves stresses caused by the weld joint, without creating any additional residual stress in the weld joint. | 07-15-2010 |
20100266391 | MECHANICAL ATTACHMENT OF CERAMIC OR METALLIC FOAM MATERIALS - A thermal barrier includes a thermal barrier member having at least one material selected from a metal foam or a ceramic foam. The thermal barrier member includes an attachment section for securing the thermal barrier member with a corresponding attachment section of a support. | 10-21-2010 |
20110185737 | COMBUSTOR LINER SEGMENT SEAL MEMBER - A combustor liner segment seal member is provided that includes a center section, a forward flange, and an aft flange. The center section includes a base surface, a gas path surface, a forward side surface, and an aft side surface. The forward flange extends outwardly from the forward side surface, and includes a width, a height, a shell side surface, and a liner side surface. The aft flange extends outwardly from the aft side surface, and includes a width, a height, a shell side surface, and a liner side surface. | 08-04-2011 |
20110185740 | COMBUSTOR LINER SEGMENT SEAL MEMBER - A combustor for a gas turbine engine is provided that includes a support shell, a forward liner segment, an aft liner segment, and a seal member. The support shell has an interior surface, and exterior surface, and a plurality of impingement apertures disposed within the shell. The forward liner segment and aft liner segment are attached to the inner surface of the shell. The forward liner segment has an edge surface extending between a face surface and a back surface, and a seal shoulder. The aft liner segment has an edge surface extending between a face surface and a back surface, and a seal shoulder. The forward liner segment and the aft liner segment are separated from one another by a gap. The seal member is disposed within the gap. At least some of the plurality of impingement apertures disposed within the shell are aligned with the seal member and oriented to direct cooling air to impinge on the seal member. | 08-04-2011 |
20120125005 | CERAMIC COMBUSTOR LINER PANEL FOR A GAS TURBINE ENGINE - A combustor assembly includes a support structure and at least one combustor liner panel selectively attached to the support structure. The combustor liner panel includes an uncooled ceramic portion, a cooled ceramic portion and a support that receives the cooled ceramic portion. | 05-24-2012 |
20120210719 | CERAMIC COMBUSTOR LINER PANEL FOR A GAS TURBINE ENGINE - A combustor assembly includes a support structure and at least one combustor liner panel selectively attached to the support structure. The combustor liner panel includes an uncooled ceramic portion, a cooled ceramic portion and a support that receives the cooled ceramic portion. | 08-23-2012 |
20120317984 | CELL STRUCTURE THERMAL BARRIER COATING - A combustor component of a gas turbine engine includes a thermal barrier coating on a substrate, the thermal barrier coating defines a multiple of cells. | 12-20-2012 |
20120324894 | STRAIN TOLERANT COMBUSTOR PANEL FOR GAS TURBINE ENGINE - A combustor component of a gas turbine engine includes a substrate with a cold side, a central core section and a hot side, the cold side and the hot side have a porosity different than the central core section. | 12-27-2012 |
20130000309 | SYSTEM AND METHOD FOR ADAPTIVE IMPINGEMENT COOLING - An adaptive cooling structure comprises a mounting support, a liner, and a spacer. The mounting support has a coolant aperture for directing cooling air through the support. The liner has a first surface facing away from the mounting support and a second surface facing towards the support. The liner is coupled to the mounting support, and the spacer is positioned between the support and the liner. The positioning of the spacer creates a chamber between the mounting support and the liner, thus allowing the cooling air to impinge on the second surface of the liner. The liner wall is configured to deflect away from the mounting support to expand the chamber, thus allowing the cooling air to further impinge on the second surface of the liner. | 01-03-2013 |
20130019603 | INSERT FOR GAS TURBINE ENGINE COMBUSTOR - A combustor of a gas turbine engine includes a heat shield panel mounted to a support shell and an insert adjacent to the support shell and the heat shield panel. | 01-24-2013 |
20130136584 | SEGMENTED THERMALLY INSULATING COATING - A gas turbine article includes a substrate and a thermally insulating topcoat disposed on a surface of the substrate. The surface of the substrate includes a surface pattern defining first surface regions and second surface regions. The first surface regions include incubation sites that are favorable for deposition of the thermally insulating topcoat and the second surface regions are less favorable for deposition of the topcoat. The topcoat includes segmented portions that are separated by faults extending through the topcoat from the second regions. | 05-30-2013 |