Patent application number | Description | Published |
20090010751 | ANGLED ON-BOARD INJECTOR - A secondary flow system provides a compact injector cooling structure for turbine blades which includes an Angled On-board Injector (AOBI) that locates a metering throat at an inward angle relative to an engine centerline. The AOBI positions the metering throat at the inward angle relative to an engine centerline to communicate cooling airflow to an angled annular section of a turbine rotor disk coverplate. | 01-08-2009 |
20090016871 | Systems and Methods Involving Variable Vanes - Systems and methods involving vanes are provided. In this regard, a representative method for modifying the throat area between vanes of a gas turbine engine includes: directing a gas flow path of the gas turbine engine between a first vane and a second vane, wherein each of the first vane and the second vane has an outer surface and an interior; and emitting pressurized air from outlet ports communicating between the outer surface and the interior of the first vane, wherein the emitted pressurized air from the first vane modifies a throat area between the first vane and the second vane. | 01-15-2009 |
20090028698 | Systems and Methods Involving Aerodynamic Struts - Systems and methods involving struts are provided. In this regard, a representative system includes a gas turbine engine defining a gas flow path. The gas turbine engine comprises a strut extending into the gas flow path. The strut has an interior operative to receive pressurized air, an outer surface, and ports communicating between the outer surface and the interior of the strut, the ports are operative to receive the pressurized air from the interior and emit the pressurized air into the gas flow path such that an effective aerodynamic length of the strut along the gas flow path is increased. | 01-29-2009 |
20090074563 | SEAL FOR GAS TURBINE ENGINE COMPONENT - A gas turbine engine component includes a pressurized fluid source, an airfoil, and a seal member for selectively providing sealing at an end of the airfoil. The seal member includes a stowed position for non-sealing and a deployed position for sealing. The seal member is operatively connected with a pressurized fluid source for moving the seal member between the stowed position and the deployed position. | 03-19-2009 |
20090097966 | Gas Turbine Engines and Related Systems Involving Variable Vanes - Gas turbine engines and related systems involving variable vanes are provided. In this regard, a representative vane assembly for a gas turbine engine includes: a first inner diameter platform; a first outer diameter platform spaced from the first inner diameter platform; and a variable vane airfoil rotatably attached to and extending between the first inner diameter platform and the first outer diameter platform such that at least a portion of the vane airfoil extends beyond a periphery of at least one of the first inner diameter platform and the first outer diameter platform. | 04-16-2009 |
20090104022 | Gas Turbine Engine Systems Involving Gear-Driven Variable Vanes - Gas turbine engine systems involving gear-driven variable vanes are provided. In this regard, a representative gas turbine engine system includes: a ring gear assembly operative to be mounted within an engine casing; and a vane module having a first vane airfoil and a first gear, the first gear being operative to engage the ring gear assembly such that movement of the ring gear alters a position of the first vane airfoil. | 04-23-2009 |
20090142181 | Gas Turbine Engine Systems Involving Mechanically Alterable Vane Throat Areas - Gas turbine engine systems involving mechanically alterable vane throat areas are provided. In this regard, a representative vane for a gas turbine engine includes: a leading edge; a trailing edge; a suction side surface extending between the leading edge and the trailing edge; a cavity having an aperture located in the suction side surface; and a barrel located within the cavity and being moveable therein such that movement of the barrel alters an extent to which the barrel protrudes through the aperture. | 06-04-2009 |
20090148282 | 3D CONTOURED VANE ENDWALL FOR VARIABLE AREA TURBINE VANE ARRANGEMENT - A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing. | 06-11-2009 |
20090162192 | Variable turbine vane actuation mechanism having a bumper ring - A variable vane actuation assembly for gas turbine engines having rotatable stator vanes comprises an engine casing, a unison ring, a bumper ring, a radial spline connection and a plurality of bumper shims. The engine casing is configured to encase the rotatable stator vanes. The unison ring is disposed concentrically with the engine casing. The bumper ring is disposed concentrically between the engine casing and the unison ring. The radial spline connection extends from the engine casing and joins with the bumper ring to permit the bumper ring to float radially with respect to the engine casing, but prevent the bumper ring from rotating circumferentially with respect to the engine-casing. The plurality of bumper shims are positioned between the unison ring and the bumper ring to limit deformation of the unison ring. | 06-25-2009 |
20090208322 | Gas turbine engine systems and methods involving blade outer air seals - Gas turbine engine systems and methods involving full ring outer air seals are provided. In this regard, a representative blade outer air seal assembly for a gas turbine engine includes a continuous, annular seal body formed of ceramic matrix composite (CMC) material. | 08-20-2009 |
20090257875 | PLATFORMLESS TURBINE BLADE - A turbine blade rotor assembly is disclosed for a gas turbine engine. The assembly includes a rotor having nickel alloy turbine blades secured thereto. Each of the blades includes a root and an airfoil. The roots are supported by the rotor. A ceramic matrix composite platform separate from the turbine blades is supported between each pair of the turbine blades adjacent to the airfoils. In another example, the airfoil includes a perimeter. A shroud having an aperture receives the airfoil with a single shroud substantially surrounding the airfoil at the perimeter. In one example, the turbine blade includes high and low pressure sides opposite one another that extend from a tip to a root. The airfoil is free from any protrusions extending from the high and low pressure sides on a portion of the blade axially outward from the root. | 10-15-2009 |
20100226760 | TURBINE ENGINE SEALING ARRANGEMENT - An example turbine engine sealing arrangement includes a blade array rotatable about an axis. The blade array has a plurality of blades extending radially from the axis. A control ring is circumferentially disposed about the blade array. A plurality of tiles are secured relative to the control ring and configured to establish an axially extending seal with one of the blades. | 09-09-2010 |
20100247293 | VARIABLE AREA TURBINE VANE ARRANGEMENT - A ring vane nozzle for a gas turbine engine according to an exemplary aspect of the present disclosure includes a multiple of fixed turbine vanes between an inner vane ring and an outer vane ring and a multiple of rotational turbine vanes between the inner vane ring and the outer vane ring, each of the rotational turbine vanes rotatable about an axis of rotation. | 09-30-2010 |
20100284816 | AIRFOIL ATTACHMENT - A rotor blade for a gas turbine engine includes an airfoil that extends in span between a tip and a root opposite from the tip. The root includes a plug, a looped portion that surrounds the plug and a clamp. The clamp contacts only a portion of the looped portion on an opposite side of the looped portion from the plug. | 11-11-2010 |
20100290898 | KNIFE EDGE SEAL ASSEMBLY - A seal assembly for a gas turbine engine is provided that includes a seal support member, at least one knife edge seal blade member, and at least one cooling member. The seal support member is configured for rotation within the gas turbine engine around an axial centerline of the engine. The support member has a thickness extending between a first surface and a second surface. The blade member extends outwardly from the first surface of the support member. The blade member has a central portion that extends between a base end and a distal knife edge end. The base end is attached to the first surface of the seal support member. The cooling member extends outwardly from the second surface, and is oppositely aligned with the blade member. | 11-18-2010 |
20110182726 | AS-CAST SHROUD SLOTS WITH PRE-SWIRLED LEAKAGE - A system for forming a seal slot in a shroud assembly has a first element having a longitudinally extending slot and a second element having a longitudinally extending slot for receiving a portion of the first element. The first element has a pair of opposed surfaces and the second element has a pair of opposed surfaces which are oriented at an angle to the surfaces of the first element. The second element may have a planar portion and a curved portion adjacent the planar portion for forming a slot which allows a flow of fluid to exit the slot at a desired angle. | 07-28-2011 |
20120275898 | Blade Clearance Control Using High-CTE and Low-CTE Ring Members - An engine has a blade stage and a circumferential array of blade outer air seal segments. A support ring carries the blade outer air seal segments. The support ring has a low-CTE member and a high-CTE member intervening between the blade outer air seal segments and the low-CTE member. | 11-01-2012 |
20130000314 | VARIABLE CYCLE TURBINE ENGINE - A gas turbine engine comprises a high spool, a low spool and an intermediate spool. The high spool comprises a high pressure turbine coupled to a high pressure compressor. The intermediate spool comprises an intermediate pressure turbine coupled to a ducted fan. The low spool comprises a low pressure turbine coupled to an open-rotor propeller. A variable area turbine section positioned between the intermediate pressure turbine and the low pressure turbine variable turbine section is configured to vary an expansion ratio across the intermediate pressure turbine to control rotational speeds of the low spool and the intermediate spool. | 01-03-2013 |
20130004325 | HYBRID PART MADE FROM MONOLITHIC CERAMIC SKIN AND CMC CORE - A hybrid part for use in a gas turbine engine has a platform and an attachment feature. The platform and an exterior portion of the attachment feature are formed from a monolithic ceramic material. A ceramic matrix composite material is located adjacent interior portions of the platform and the attachment feature and is bonded to the monolithic ceramic material. | 01-03-2013 |
20130004326 | CMC BLADE WITH INTEGRAL 3D WOVEN PLATFORM - A method of forming a component for use in a gas turbine engine includes the steps of forming an airfoil/root assembly; creating a platform assembly structure having an opening; inserting the airfoil/root assembly into the opening; and bonding the platform assembly structure to the airfoil/root assembly to form the component. | 01-03-2013 |
20130022469 | Turbine Rotor Non-Metallic Blade Attachment - In an engine disk and blade combination, the metallic disk has a plurality of first blade attachment slots and a plurality of second blade attachment slots circumferentially interspersed with each other. There is a circumferential array of a plurality of first blades. Each first blade has an airfoil and an attachment root. The attachment roots are respectively received in associated said first attachment slots. There is a circumferential array of second blades. Each second blade has an airfoil and an attachment root. The attachment roots are respectively received in associated said second slots. The first blades and second blades are non-metallic. The first blades are radially longer than the second blades. The first slots are radially deeper than the second slots. | 01-24-2013 |
20130052030 | CERAMIC MATRIX COMPOSITE VANE STRUCTURE WITH OVERWRAP FOR A GAS TURBINE ENGINE - A vane structure for a gas turbine engine includes an airfoil section with a platform segment adjacent to a ring. An insert is adjacent to the platform segment and an overwrap is wound around the ring and the insert. | 02-28-2013 |
20130094951 | MID TURBINE FRAME (MTF) FOR A GAS TURBINE ENGINE - A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes a multiple of airfoil sections between an outer ring and an inner ring. A spring biased tie-rod assembly is mounted through at least one of the multiple of airfoil sections. | 04-18-2013 |
20130115089 | ROTATABLE COMPONENT WITH CONTROLLED LOAD INTERFACE - A rotatable component includes a first section and a second section that is located radially outwards of the first section with regard to an axis of rotation about which the sections are co-rotatable. These sections are attached together at a bonded interface. At a perimeter region of the bonded interface a perimeter portion of the first section has a first stiffness and a perimeter portion of the second section has a second stiffness that is greater than the first stiffness. | 05-09-2013 |
20130142660 | CERAMIC MATRIX COMPOSITE AIRFOIL STRUCTURE WITH TRAILING EDGE SUPPORT FOR A GAS TURBINE ENGINE - An airfoil for a gas turbine engine includes an aft trailing edge support between a pressure side and a suction side. | 06-06-2013 |
20130209240 | ADJUSTABLE BLADE OUTER AIR SEAL APPARATUS - An adjustable blade outer air seal apparatus includes a case structure that extends circumferentially, a support ring structure mounted radially inwards of the case structure and at least one blade outer air seal segment radially adjustably mounted relative to the support ring structure. | 08-15-2013 |
20130240304 | LOW CONDUCTIVITY BRAKE PAD - A multi-layer brake pad assembly includes a layer of friction material, a layer of thermal insulating material, and a backing plate. The thermal insulating material is a fiber reinforced ceramic matrix composite with a high fracture toughness and low thermal conductivity that is disposed between the friction material and the backing plate and restricts the heat flow transmitted through the backing plate into the hydraulic fluid during severe braking, thereby minimizing the onset of brake loss due to hydraulic fluid vaporization as a result of overheating. | 09-19-2013 |
20130323073 | ASSEMBLED BLADE PLATFORM - A method of making a platform of a blade includes the steps of creating two platform sections by solidifying a material with a fabric in a mold and positioning a band of fabric around the two platform sections to retain an airfoil and define a blade. The method further includes the step of bonding the two platform sections together by solidifying the material to define a platform of a solid material. The platform is not bonded to the airfoil. | 12-05-2013 |
20140014223 | WOVEN STRUCTURE AND METHOD FOR WEAVING SAME - An exemplary weaving method includes placing a first section of a fill fiber between warp fibers, forming a pick, moving a base to reposition the warp fibers, and placing a second section of the fill fiber between the warp fibers. | 01-16-2014 |
20140017072 | BLADE OUTER AIR SEAL WITH COOLING FEATURES - A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. At least one cooling fin is disposed on the radially outer face between the leading edge portion and the trailing edge portion. | 01-16-2014 |
20140023480 | RADIAL POSITION CONTROL OF CASE SUPPORTED STRUCTURE - A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. The supported structure includes a hook providing an annular recess. A support ring is received in the recess. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure. | 01-23-2014 |
20140133955 | CARRIER INTERLOCK - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an engine case, a rotor stage including a plurality of rotor blades, a plurality of carriers for supporting a plurality of blade outer air seals and an interlock formed between circumferential ends of a first adjacent carrier and a second adjacent carrier of the plurality of carriers. | 05-15-2014 |
20140186152 | BLADE OUTER AIR SEAL SYSTEM FOR CONTROLLED TIP CLEARANCE - A blade outer air seal system for a gas turbine engine includes a plurality of ring carriers made of a first material having a first coefficient of thermal expansion. A plurality of seal segments are carried, respectively, on the plurality of ring carriers. A ring member is carried in the plurality of ring carriers. The ring member is made of a second material that is different from the first material in composition. The second material has a second coefficient of thermal expansion such that the first coefficient of thermal expansion is 75-175% of the second coefficient of thermal expansion. | 07-03-2014 |
20140255174 | MANUFACTURE OF FULL RING STRUT VANE PACK - A vane assembly for a gas turbine engine is disclosed and includes a plurality of individual vane segments forming an annular ring. Each of the plurality of vane segments is formed of a ceramic matrix composite including at least one airfoil extending between an inner platform and an outer platform. An outer wrap is disposed about an outer periphery of the annular ring and over an interface between outer platforms of adjacent ones of the plurality of vane segments. | 09-11-2014 |
20150042023 | Hybrid Part Made From Monolithic Ceramic Skin and CMC Core - A hybrid part for use in a gas turbine engine has a platform and an attachment feature. The platform and an exterior portion of the attachment feature are formed from a monolithic ceramic material. A ceramic matrix composite material is located adjacent interior portions of the platform and the attachment feature and is bonded to the monolithic ceramic material. | 02-12-2015 |