Patent application number | Description | Published |
20090081025 | SEGMENTED COOLING AIR CAVITY FOR TURBINE COMPONENT - A component for a gas turbine engine has an airfoil with internal cooling channels for delivering air from a radially outer end of the airfoil toward a radially inner end of the airfoil. The cooling channels are separated from adjacent cooling channels by sets of at least two disconnected wall segments. | 03-26-2009 |
20090087306 | BLADE OUTER AIR SEALS, CORES, AND MANUFACTURE METHODS - A blade outer air seal (BOAS) casting core has first and second end portions and a plurality of legs. Of these legs, first legs each have: a proximal end joining the first end portion; a main body portion; and a free distal portion. Second legs each have: a proximal end joining the second end portion; a main body portion; and a free distal portion. | 04-02-2009 |
20090104025 | Gas Turbine Engines and Related Systems Involving Blade Outer Air Seals - Gas turbine engines and related systems involving blade outer air seals are provided. In this regard, a representative blade outer air seal assembly for a gas turbine engine includes: an annular arrangement of outer air seal segments defining an inner diameter surface; intersegment gaps located between the outer air seal segments, each of the gaps being located between a corresponding adjacent pair of the segments; and recesses spaced about the inner diameter surface, each of the recesses communicating with a corresponding one of the gaps. | 04-23-2009 |
20090148277 | Gas Turbine Engines and Related Systems Involving Blade Outer Air Seals - Gas turbine engines and related systems involving blade outer air seals are provided. In this regard, a representative blade outer air seal assembly for a gas turbine engine includes: an annular arrangement of outer air seal segments, each of the segments having ends, the segments being positioned in an end-to-end orientation such that each adjacent pair of the segments forms an intersegment gap therebetween, each intersegment gap being defined, at least partially, by a first recess and a first protrusion, the first protrusion being sized and shaped to be received by the first recess, one of the first recess and the first protrusion being located on an end of a first segment of an adjacent pair of the segments, another of the first recess and the first protrusion being located on an end of a second segment of the adjacent pair of the segments. | 06-11-2009 |
20090226300 | Passage obstruction for improved inlet coolant filling - A cooled gas turbine engine component includes a cooling passage, one or more cooling inlet apertures in flow communication with a coolant supply and a first end of the cooling passage, and a coolant flow obstruction inside the cooling passage between the one or more cooling inlet apertures and a second end of the cooling passage and configured to direct a portion of coolant from the one or more cooling inlet apertures toward the first end of the cooling passage. | 09-10-2009 |
20090301680 | BLADE OUTER AIR SEAL CORES AND MANUFACTURE METHODS - A blade outer air seal (BOAS) casting core has first and second end portions and a plurality of legs. Of these legs, first legs each have: a proximal end joining the first end portion; a main body portion; and a free distal portion. Second legs each have: a proximal end joining the second end portion; a main body portion; and a free distal portion. | 12-10-2009 |
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 |
20100186419 | HEAT TRANSFER AUGMENTATION IN A COMPACT HEAT EXCHANGER PEDESTAL ARRAY - A compact heat exchanger pedestal array for augmenting heat transfer in a machine is disclosed. The compact heat exchanger pedestal array includes a wall having first and second surfaces. The first surface faces a heated flow path and the second surface partially forms a flow path for cooling fluid. A plurality of pedestals extend from the second surface of the wall. At least one turbulator strip extends between adjacent pedestals. The turbulator strips and pedestals are operable for mixing the cooling fluid to increase heat transfer from the wall to the cooling fluid. | 07-29-2010 |
20100226762 | Structural members in a pedestal array - A turbine engine component has a flow path wall and a support wall. The turbine engine component has at least one cooling compact heat exchanger. Each cooling compact heat exchanger has a pedestal array and at least one structural member within the pedestal array for preventing modal crossing in operation range, for preventing panel bulging, and/or for connecting the flow path wall to at least one outer diameter support structure. | 09-09-2010 |
20110150636 | IN-SITU TURBINE BLADE TIP REPAIR - The tip portion of a blade of a gas turbine is repaired in-situ in the gas turbine without removing the blade from the turbine rotor disk. To facilitate the in-situ repair of the tip portion of the turbine blades, one or more access holes may be provided in the turbine shroud or blade outer air seal circumscribing the plurality of turbine blades extending radially outward from the turbine rotor dick. | 06-23-2011 |
20110203286 | 3D NON-AXISYMMETRIC COMBUSTOR LINER - A combustor liner with an input end and an output end includes an annular inner wall and an annular outer wall. At least one of the inner wall and outer wall is three-dimensionally contoured. The inner wall and the outer wall form a combustion chamber with the contours creating alternating expanding and constricting regions inside the chamber causing combustion gases to flow in the circumferential and axial directions. | 08-25-2011 |
20110236188 | BLADE OUTER SEAL FOR A GAS TURBINE ENGINE - A blade outer air seal for a gas turbine engine is provided. The blade outer air seal includes a body having an outer radial surface, an inner radial surface, and a plurality of cooling air apertures. The body extends between a forward edge and an aft edge. The inner radial surface includes at least one first seal section, at least one second seal section, and a riser extending radially between the first seal section and the second seal section. Each of the plurality of cooling air apertures extends between the outer radial surface and the riser, and each cooling air aperture has an exit configured to direct cooling air substantially parallel to the second seal section of the inner radial surface. | 09-29-2011 |
20110300342 | Ceramic Coating Systems and Methods - An article has a metallic substrate. The substrate has a first surface region and a plurality of blind recesses along the first surface region. The substrate has perimeter lips at the openings of the plurality of recesses and extending partially over the respective associated recesses. A ceramic coating is along the first surface region. | 12-08-2011 |
20120201662 | CORE RUNOUT CEILING FOR TURBINE COMPONENTS - A method of closing off a mold plug opening in a turbine component includes the steps of inserting a weld member into an opening to be closed, and to abut a necked portion within a passage leading from the opening. Heat is applied to the weld member, such that a surface of the weld member in contact with the necked portion liquefies, and such that the weld member adheres to the necked portion, closing off the opening. The weld member and application of heat are selected such that the entirety of the weld member does not liquefy, but remains in the opening, without ever having liquefied. A turbine component formed by the method is also disclosed. | 08-09-2012 |
20120292856 | BLADE OUTER SEAL FOR A GAS TURBINE ENGINE HAVING NON-PARALLEL SEGMENT CONFRONTING FACES - A blade outer air seal for a gas turbine engine includes an arcuate first seal segment and an arcuate second seal segment. The first seal segment extends circumferentially to a first confronting face. The second seal segment extends circumferentially to a second confronting face. The first confronting face is positioned adjacent the second confronting face defining a gap therebetween. The confronting faces are radially non-parallel at a first engine operating point where each seal segment has a first temperature distribution profile and a first pressure distribution profile. The confronting faces are substantially radially parallel at a second engine operating point where each seal segment has a second temperature distribution profile and a second pressure distribution profile, which second profiles are different than the first profiles. | 11-22-2012 |
20120319360 | PLUG ASSEMBLY FOR BLADE OUTER AIR SEAL - A plug assembly includes a cup which defines a cup portion and a cup anti-liberation portion along an axis, a wedge is mountable within the cup portion to at least partially radially expand the cup anti-liberation portion. | 12-20-2012 |
20120319362 | WINGED W-SEAL - A seal assembly has a first seal member, a second seal member, and a third seal member. The first seal member has a wear surface that contacts a first wall of the cavity at two sealing locations. The second seal member has a wear surface that contacts a second wall of the cavity at two sealing locations. The third seal member extends between and resiliently connects the first seal member to the second seal member. | 12-20-2012 |
20130017058 | BLADE OUTER AIR SEAL HAVING PARTIAL COATINGAANM Joe; Christopher R.AACI WethersfieldAAST CTAACO USAAGP Joe; Christopher R. Wethersfield CT USAANM Lutjen; Paul M.AACI KennebunkportAAST MIAACO USAAGP Lutjen; Paul M. Kennebunkport MI USAANM Mongillo, JR.; Dominic J.AACI West HartfordAAST CTAACO USAAGP Mongillo, JR.; Dominic J. West Hartford CT US - A blade outer air seal member includes a body that extends between two circumferential sides, axially between a leading edge and a trailing edge, and between a gas path side and a radially outer side opposite the gas path side. A ceramic coating is initially disposed on a portion of the gas path side outside of a blade rub area of the gas path side such that the blade rub area is bare with regard to any ceramic coating. | 01-17-2013 |
20130068415 | MOLD FOR CASTING A WORKPIECE THAT INCLUDES ONE OR MORE CASTING PINS - A mold for casting a workpiece that includes a casting shell, a casting core and casting pin that supports the core within the shell. The casting shell includes an interior shell surface. The casting core is located within the shell, and includes a sidewall extending between a first core surface and a second core surface. The casting pin includes an intermediate segment connected between a first support segment and a second support segment. The intermediate segment contacts the sidewall. The first support segment extends from the first core surface to a first side of the interior shell surface. The second support segment extends from the second core surface to a second side of the interior shell surface that is opposite the first side. | 03-21-2013 |
20130113168 | METAL GASKET FOR A GAS TURBINE ENGINE - A gasket assembly for a gas turbine engine includes a seal portion defining outer surfaces for providing sealing contact and a bias portion defining inner structures that are spaced apart from the seal portion for biasing the outer surfaces into sealing contact. The gasket further includes end portions disposed at ends of the seal portion that including a material thickness greater than a thickness of the bias portion. | 05-09-2013 |
20130216363 | SURFACE AREA AUGMENTATION OF HOT-SECTION TURBOMACHINE COMPONENT - An example turbomachine hot-section component protrusion extends away from a base surface of a hot-section component along a longitudinal axis. A radial cross-section of the protrusion has a profile that is non-circular. | 08-22-2013 |
20130266416 | COOLING SYSTEM FOR A TURBINE VANE - A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other. | 10-10-2013 |
20130323032 | BLADE OUTER AIR SEAL FOR A GAS TURBINE ENGINE - A blade outer air seal (BOAS) segment according to an exemplary embodiment of the present disclosure can include a seal body having a radially inner face and a radially outer face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face. At least one of the first mate face, the second mate face, the radially outer face and the radially inner face can include an inner wall having a ledge and an undercut passage radially inward from the ledge that extends uninterrupted along a length of the ledge. | 12-05-2013 |
20130323033 | BLADE OUTER AIR SEAL WITH CORED PASSAGES - A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook. | 12-05-2013 |
20130340966 | BLADE OUTER AIR SEAL HYBRID CASTING CORE - A hybrid sacrificial core for forming an impingement space and an internal cooling passageway network separate from the impingement space of a part may comprise a ceramic core having a first surface portion for forming the impingement space, and a refractory metal core that forms a plurality of passages of the internal cooling passageway network. | 12-26-2013 |
20140190175 | 3D NON-AXISYMMETRIC COMBUSTOR LINER - A combustor liner with an input end and an output end includes an annular inner wall and an annular outer wall. At least one of the inner wall and outer wall is three-dimensionally contoured. The inner wall and the outer wall form a combustion chamber with the contours creating alternating expanding and constricting regions inside the chamber causing combustion gases to flow in the circumferential and axial directions. | 07-10-2014 |
20140212263 | AIRFOIL WITH VARIABLE PROFILE RESPONSIVE TO THERMAL CONDITIONS - An airfoil includes an airfoil body having a first section and a second section that differ by coefficient of thermal expansion. The second section is arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions. | 07-31-2014 |
20140248115 | Active Clearance Control System with Zone Controls - An ACC system and method of using such for changing a turbine blade to BOAS gap on an aircraft engine is disclosed. The ACC system may comprise a first ring, a first supply line and a first flow control assembly. The first ring may be configured to substantially encircle a portion of a case assembly that is disposed around an aircraft engine turbine. The first ring may include a plurality of segments that each define a chamber, an inlet port and a plurality of outlet ports. At least a portion of the outlet ports may be configured to be disposed adjacent to the case. The first supply line may be operatively connected to a first segment of the plurality of segments. The first flow control assembly may be operatively connected to the first supply line and configured to meter the flow of cool air into the first segment. | 09-04-2014 |