Class / Patent application number | Description | Number of patent applications / Date published |
415134000 | INCLUDING THERMAL EXPANSION JOINT | 42 |
20090003993 | Ceramic matrix composite turbine engine vane - A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The shell includes a region having a depth-wise coefficient of thermal expansion and a second coefficient of thermal expansion transverse thereto, the depth-wise coefficient of thermal expansion being greater than the second coefficient of thermal expansion. | 01-01-2009 |
20090053042 | METHOD AND APPARATUS FOR CLEARANCE CONTROL OF TURBINE BLADE TIP - A gas turbine including a casing and a shroud ring, the gas turbine including an attachment device rigidly attached to the casing and at least one of the shroud ring and a duct attached to the shroud ring, wherein the device allows the shroud ring to expand and contract independent of the casing and provides limited net axial growth of the shroud ring. | 02-26-2009 |
20090155054 | WALL STRUCTURE FOR LIMITING A HOT GAS PATH - A wall structure for restricting a hot-gas path in a gas turbine or in a combustion chamber including a first wall segment having a first face, and a second wall segment having a second face. Each wall segment disposed adjacent to each other so as to define an inside of the wall segments and an outside of the wall segments. The first and second faces being disposed so as to form a gap leading from the inside to the outside. Each of the faces having a receiving groove. The wall structure further including a sealing element having a thickness and disposed in the receiving grooves so as to bridge the gap. The first face having a recess and the second wall segment having a projection that extends from the second face and protrudes into the recess in the first face. The projection having a conical cross section. | 06-18-2009 |
20090208326 | RIM SEAL FOR A GAS TURBINE ENGINE - The rim seal is positioned in an annular space between blades and a non-rotating adjacent structure in a gas turbine engine. The rim seal is connectable to the non-rotating structure and is made of an abradable material. | 08-20-2009 |
20110076137 | CASING COMPONENT - A casing component ( | 03-31-2011 |
20110081234 | GAS TURBINE ENGINE THERMAL EXPANSION JOINT - A thermal expansion joint apparatus includes an insert extending passages passing through respective first and second components to loosely restrain the first component between the second component and an enlarged head of the insert thereby allowing thermal expansion of the respective first and second components relative to each other. The insert is secured to the second component by a fastener which can be removed, for example, when the insert is to be removed from the engine. | 04-07-2011 |
20110236183 | BIMETALLIC SPLINE SEAL - A spline seal for a hot gas path component is provided. The spline seal may include a first metal layer and a second metal layer. The first metal layer may have a first volumetric thermal expansion coefficient. The second metal layer may be disposed adjacent the first metal layer and have a second volumetric thermal expansion coefficient. The second volumetric thermal expansion coefficient may be higher than the first volumetric thermal expansion coefficient. When the spline seal is exposed to a heat source, the first and second metal layers may deform to provide a seal between the hot gas path component and an adjacent hot gas path component. | 09-29-2011 |
20130051987 | TURBINE SHROUD SEGMENT WITH INTER-SEGMENT OVERLAP - A turbine shroud has a plurality of shroud segments disposed circumferentially one adjacent to another. Each segment has a flow restrictor projecting integrally from one end face thereof and overlapping a corresponding end face of a circumferentially adjacent segment. The overlap between the circumferentially adjacent segments restricts gas leakage through the inter-segment gap between adjacent shroud segments. | 02-28-2013 |
20130302148 | Expansion Seal - A turbine assembly can include a turbine wheel, a shroud component, a turbine housing, and an expansion seal that includes a lower lip, an upper lip, and a wall that extends between the lower lip and the upper lip and that is disposed between an outer seal surface of the shroud component and an inner seal surface of the turbine housing. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed. | 11-14-2013 |
20140248130 | Seal Hook Mount Structure With Overlapped Coating - A seal is positioned radially outwardly of a compressor blade. The seal has a seal hook facing in a downstream direction. A seal mount has a mount hook for receiving the seal hook in a gap. The hook face in an upstream direction. The seal mount has an upstream portion extending from an upstream end into the gap. The mount hook extends into a web which extends in a downstream direction. A thermal barrier coating on the upstream portion of the seal mount extends to a downstream end. There is a thermal barrier coating on a radially inner surface of the mount hook, and along the web to a downstream coating end. An upstream end of the coating on the inner surface of the hook being formed axially upstream of the downstream end of the coating on the upstream portion. | 09-04-2014 |
20140248131 | PUSH ROD ARRANGEMENT FOR TURBINE SYSTEM - A turbine system with a push rod arrangement is presented. The turbine system includes a first turbine having a first rotor, a second turbine having a second rotor, a push rod coupled to a casing of the first turbine at a first end and to a casing of the second turbine at a second end wherein the push rod includes a device for controlling temperature. | 09-04-2014 |
20140286756 | DEVICE, SYSTEM AND METHOD FOR PREVENTING LEAKAGE IN A TURBINE - A turbine disk and blade assembly comprises a turbine disk including a plurality of disk posts extending radially therefrom and a plurality of disk slots between adjacent disk posts. The turbine disk is of a first material having a first coefficient of thermal expansion. The assembly further comprises a plurality of turbine blades. One of the turbine blades is received in each disk slot. The turbine blades are of a second material having a second coefficient of thermal expansion. The assembly further comprises a plurality of seal plates, wherein one of the seal plates is positioned in each disk slot radially inward of the turbine blade. The seal plates are of a material having a coefficient of thermal expansion substantially similar to that of either the disk posts or the turbine blade. | 09-25-2014 |
20140308113 | STRUCTURE AND METHOD FOR PROVIDING COMPLIANCE AND SEALING BETWEEN CERAMIC AND METALLIC STRUCTURES - A structure providing compliance and sealing between ceramic or ceramic composite (CMC) part and a metallic part has an interface component for centering the CMC part in the metallic part, thus reducing thermal stress motion of the CMC component. In gas turbine engine applications, the structure comprises a CMC blade track inserted in a clip placed within a metallic hanger. The clip provides for radial compliance and secures controlled leakage of cooling air required to ensure that acceptable temperatures are maintained for the metallic structures. A washer is positioned adjacent to the clip provide for axial orientation of the blade track. | 10-16-2014 |
20150010389 | PRESSURE CASING OF A TURBOMACHINE - The invention relates to a pressure casing, which includes a plurality of casing shells which are connected in a pressure-tight manner in a parting plane by means of a flange. The casing shells are pressed together with sealing effect in the parting plane in the region of the flange by means of at least one threaded bolt which extends in a through hole through the flange perpendicularly to the parting plane. Reduced temperature differences between the flange and the connecting bolts of the flanged joint are achieved by the at least one threaded bolt being charged with a heat transfer medium over a part of its length. The heat transfer medium is supplied via holes extending through the flange. | 01-08-2015 |
20150044032 | INTEGRATED STRUT AND VANE ARRANGEMENTS - In an integrated strut and turbine vane nozzle (ISV) configuration, lug/slot or tag/groove arrangements may be provided between an interturbine duct (ITD) of the ISV and a vane ring of the ISV such that struts of the ITD and associated vanes are angularly positioned to form integrated strut-vane airfoils, reducing mismatch at the integration. | 02-12-2015 |
20150125271 | PUMP SEAL WITH THERMAL RETRACTING ACTUATOR - A thermal actuator for a rotating shaft shutdown seal that has a piston with a portion of its axial length enclosed within a cylinder shell with a material, such as a fusible link that changes state or deforms above a given temperature, interposed between a closed end of the cylinder and one end of the piston. The piston is spring biased toward the material and moves toward the closed end of the cylinder when the given temperature is reached and the deformation or change of state of the material makes room for the piston to move toward the closed end. Movement of the piston is transferred through a piston rod to activate the seal. | 05-07-2015 |
20160010481 | GAS TURBINE SPINDLE BOLT STRUCTURE WITH REDUCED FRETTING FATIGUE | 01-14-2016 |
20160123187 | HEATSHIELD ASSEMBLY WITH DOUBLE LAP JOINT FOR A GAS TURBINE ENGINE - A heat shield assembly for a gas turbine engine includes a first heat shield segment defined about an axis and a second heat shield segment defined about the axis. A double circumferential lap joint is defined between the first heat shield segment and the second heat shield segment. | 05-05-2016 |
20160177768 | BLADE TIP CLEARANCE SYSTEMS | 06-23-2016 |
20160251982 | METHOD AND SYSTEM FOR A CERAMIC MATRIX COMPOSITE SHROUD HANGER ASSEMBLY | 09-01-2016 |
415135000 | Resilient | 6 |
20080199307 | Flexible, high-temperature ceramic seal element - A ceramic seal element ( | 08-21-2008 |
20110033282 | CHARGING DEVICE, MORE PREFERABLY EXHAUST GAS TURBOCHARGER FOR A MOTOR VEHICLE - The invention relates to a charging device, such as an exhaust gas turbocharger for a motor vehicle, with a shaft carrying a compressor wheel, with a fixing device for fixing the compressor wheel on the shaft, with at least one component fixed on the shaft together with the compressor wheel by the fixing device. It can be achieved that heat expansion of the compressor wheel through the expansion coefficient (α | 02-10-2011 |
20130028713 | SEAL FOR TURBOMACHINE SEGMENTS - In one embodiment, a system includes a seal having a first sealing end portion, a second sealing end portion, and an intermediate portion between the first and second sealing end portions, wherein the seal has at least one metering hole configured to control a leakage flow across the seal. | 01-31-2013 |
20130323027 | EXPANSION JOINT AND STEAM TURBINE SYSTEM INCLUDING THE SAME - An expansion joint that is provided between a steam turbine outlet and a condenser inlet, including: an upstream baffle tube that has one end secured to an upstream fixing end and the other end as a free end, and forms a steam channel; a downstream baffle tube that has one end secured to a downstream fixed end and the other end as a free end, the free end being relatively movable outside the free end of the upstream baffle tube; and a flexible cylinder that is formed of a non-metal material using a resin sheet, and deformable while airtightly surrounding the baffle tubes. | 12-05-2013 |
20140314547 | ATTACHMENT APPARATUS FOR CERAMIC MATRIX COMPOSITE MATERIALS - A first ceramic matrix composite structure having a first flange with a first aperture, and a second structure having a second flange with a second aperture are clamped together by a fastener and spring assembly. The second flange is in contact with the first flange and the apertures of the first and second flanges align with each other. A threaded fastener having a thermal expansion rate that is different than the thermal expansion rate of at least one of the first ceramic matrix composite structure and second structure extends through the aligned apertures. The fastener includes a bolt, a nut, and a spring assembly that maintains a constant clamping pressure irrespective of the thermal expansion differences between the bolt and the first ceramic matrix composite structure and second structure. | 10-23-2014 |
20150050127 | AIR WITH INTEGRAL SPRING FOR A GAS TURBINE ENGINE EXHAUST DRIVE - A seal assembly for an exhaust duct section of a gas turbine engine includes a multiple of springs that axially extend from a split hoop opposite a seal surface. | 02-19-2015 |
415136000 | Radially sliding | 7 |
20100284792 | TURBINE SHELL WITH PIN SUPPORT - A turbine is provided and includes a turbine shell including shrouds at multiple stages thereof, and constraining elements, disposed at least at first through fourth substantially regularly spaced perimetrical locations around the turbine shell, which are configured to concentrically constrain the shrouds of the turbine shell. | 11-11-2010 |
20130202418 | CLEARANCE CONTROL FOR GAS TURBINE ENGINE SECTION - A section of a gas turbine engine includes a case structure having a first coefficient of thermal expansion. A continuous, ring-shaped liner has a second coefficient of thermal expansion that is substantially different than the first coefficient of thermal expansion. A flexible leaf member operatively connects the liner to the case structure. The leaf member is configured to accommodate diametrical change in the liner throughout various fan section operating temperatures. | 08-08-2013 |
20140093358 | PIN CONNECTOR FOR CERAMIC MATRIX COMPOSITE TURBINE FRAME - A connector between a first object having a first coefficient of thermal expansion and a second object having a second coefficient of thermal expansion has a slot attaching to the second object. The slot formed by an inner shell having a slot shape and a first portion that blends into an outer surface of the second object, the slot having an enclosed portion facing forward and an aft portion that is open. | 04-03-2014 |
20150071767 | CLEARANCE CONTROL SYSTEM FOR A ROTARY MACHINE AND METHOD OF CONTROLLING A CLEARANCE - A clearance control system for a rotary machine includes an outer casing including an outer casing main portion having a first radial thickness, wherein the outer casing is configured to expand at a first time rate of thermal expansion. Also included is an inner casing disposed between the outer casing and a rotary portion, the inner casing including an inner casing main portion having a second radial thickness that is less than the first radial thickness, wherein the inner casing is configured to expand at a second time rate of thermal expansion that is greater than the first time rate of thermal expansion of the outer casing. Further included is an inner casing leg configured to separate from an outer casing leg during expansion of the inner casing and configured to engage the outer casing leg during contraction of the inner casing. | 03-12-2015 |
20160003086 | GAS TURBINE ENGINE SPRING MOUNTED MANIFOLD - An arcuate panel for a thermal control assembly includes an arcuate panel base, at least one axially extending panel header sealingly attached to a radially outwardly facing surface of the panel base, a plenum therebetween, one or more spray tubes or channels depending radially inwardly from the panel base and in fluid communication with the plenum, and radially outwardly biasing spring means mounted on or attached to the radially inwardly facing surface of the panel base. The panel may include at least one set of clockwise and counter-clockwise hinge wings attached to clockwise and counter-clockwise ends of the panel base, axial positioning means, and circumferential positioning means. The axial positioning means may include a circular row of spring clips mounted on the panel base. A hoop of arcuate panels pivotably attached by hinges may encircle a portion of a casing compressing leaf springs against rings of the casing. | 01-07-2016 |
20160123172 | PASSIVE CONTROL OF GAS TURBINE CLEARANCES USING CERAMIC MATRIX COMPOSITES INSERTS - A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flowpath through the engine core. | 05-05-2016 |
415137000 | Stator vane in shroud ring opening | 1 |
20150330237 | Casing arrangement for a gas turbine - The present invention relates to a gas turbine casing arrangement having a gas turbine casing element ( | 11-19-2015 |
415139000 | Circumferentially spaced nozzle or stator segments | 9 |
20090016873 | Gas Turbine Systems Involving Feather Seals - Systems involving feather seals are provided. A representative vane assembly for a gas turbine engine includes: a first mounting platform having a first slot; a first airfoil extending from the first mounting platform; and a feather seal having opposing faces, a first side extending between the faces, and a first tab, the first tab extending outwardly beyond the first side; the first slot being sized and shaped to receive the feather seal including the first tab. | 01-15-2009 |
20100074729 | Compressible Ceramic Seal - A stack of substantially parallel ceramic plates ( | 03-25-2010 |
20100080692 | FAIRING SEAL - A fairing is disclosed, comprising a surface capable of bounding a fluid on the surface and a seal located at an edge portion on the fairing wherein the seal has at least one support flange and a contact face capable of engaging with an adjacent component to facilitate reducing a leakage of the fluid. A stator assembly is disclosed comprising a vane, a first fairing having a first seal and a second fairing having a second seal, wherein the first seal engages with an adjacent component to facilitate reducing leakage of a fluid in the stator assembly. | 04-01-2010 |
20110135450 | CHAMFER-FILLET GAP FOR THERMAL MANAGEMENT - An apparatus and method is disclosed herein in which a heat-transfer fluid can be directed through a gap defined between a fillet and a chamfer. The apparatus includes a first member having a body portion and a flange portion projecting from the body portion. The flange portion extends along an endless path encircling an axis to define a receiving aperture. A fillet is defined at a junction of the body portion and an inner surface of the flange portion. The apparatus also includes a second member having a plug portion receivable in the receiving aperture. The plug portion includes a first surface operable to abut the body portion and limit movement of the plug portion into the receiving aperture. The plug portion also includes a second surface slidably engageable with the inner surface of the flange portion to guide movement of the plug portion into the receiving aperture along the axis. A chamfer is defined at a junction of the first and second surfaces such that a gap is defined between the fillet and the chamfer when the plug portion is received in the receiving aperture. The apparatus also includes at least one passageway extending at least partially through at least one of the first member and the second member. The at least one passageway extends between the gap and an opening spaced from the gap. The at least one passageway is operable to receive a heat-transfer fluid to transfer heat relative to the fillet. | 06-09-2011 |
20110236184 | Axial Compressor for a Gas Turbine Having Passive Radial Gap Control - An axial compressor for a gas turbine having passive radial gap control is provided. The axial compressor includes a guide vane support on which guide vanes are fastened so as to be arranged in a ring, wherein the vane tips of the guide vanes lie opposite a wall section. Thermal insulation is attached to the wall section in the section lying opposite the vane tips in order to equalize the expansion behavior of the guide vane support and the wall section, which by themselves react thermally in different manners, wherein the terminal insulation is matched in the heat input delay effect thereof to the wall section and to the guide vane support in such a way that the thermal expansion behavior of the guide vane support and the wall section is at least equalized over time during transient operation of the axial compressor. | 09-29-2011 |
20130236293 | SYSTEMS AND METHODS FOR AN IMPROVED STATOR - In an embodiment, a system includes a rotary machine. The rotary machine includes a rotor having a plurality of blades and a segmented stator having a plurality of stator segments arranged circumferentially about the plurality of blades. Each adjacent pair of first and second segments of the plurality of stator segments includes a recess extending circumferentially across an intermediate joint between the first and second segments. Furthermore, each recess includes at least one eccentricity control insert configured to mitigate eccentricity of an inner circumference of the segmented stator due to thermal expansion or thermal contraction of the segmented stator. | 09-12-2013 |
20140321984 | TURBINE THERMAL CLEARANCE MANAGEMENT SYSTEM - Systems and devices configured for active thermal control of turbine components are disclosed. In one embodiment, a thermal control system for a turbine includes: a thermal source shaped to connect to a turbine; a set of sensors disposed about the turbine and configured to obtain operational data from the turbine; and a computing device communicatively connected to the thermal source and the set of sensors, the computing device configured to regulate a thermal input of the thermal source to the turbine based on the operational data obtained by the set of sensors. | 10-30-2014 |
20140321985 | ROTOR TIP CLEARANCE - A method of characterising mechanical and thermal growth of a rotor tip clearance arrangement and a method of controlling such an arrangement. The characterisation method comprising constructing a finite element model and calibration cases; run the model for the calibration cases to obtain displacements; and calculating component growth therefrom. The growth is characterised and scaled for the operating conditions. The clearance is calculated in a time step from the growths and input to a control arrangement for subsequent time steps. | 10-30-2014 |
20140328672 | STATOR COMPONENT WITH SEGMENTED INNER RING FOR A TURBOMACHINE - A stator component of a turbomachine is composed substantially of at least one axially extending outer ring ( | 11-06-2014 |