Class / Patent application number | Description | Number of patent applications / Date published |
415009000 | INCLUDING DESTRUCTIBLE, FUSIBLE, OR DEFORMABLE NON-REUSABLE PART | 54 |
20080199301 | Fan Case Reinforcement in a Gas Turbine Jet Engine - Described is reinforcement of a fan case in a gas turbine jet engine. In one embodiment, a containment ring and a heat resistance ring are shrink interference fit on the inside diameter of the fan case, the containment ring where the large fan blades turn, and the heat resistance ring where heated air from backfiring heats up the fan case. In one example, the containment ring is made of a super alloy to provide added strength to the fan case should a fan blade break, containing the fan blade within the fan case. The heat resistance ring is made of titanium or other suitable material. Additionally, one or more stiffener rings may be shrink interference fit on the outside diameter of the fan case. The containment ring and stiffener rings can reduce the flight weight of the fan case and lower the material costs, while increasing the containment strength of the fan case. Other embodiments are described and claimed. | 08-21-2008 |
20080232951 | Fan Case Reinforcement in a Gas Turbine Jet Engine - Described is reinforcement of a fan case in a gas turbine jet engine. In one embodiment, a containment ring and a hear resistance ring are shrink interference fit on the inside diameter of the fan case, the containment ring where the large fan blades turn, and the heat resistance ring where heated air from backfiring heats up the fan case. In one example, the containment ring is made of a sue alloy to provide added strength to the fan case should a fan blade break, containing the fan blade within the fan case. Also, the containment ring may extent forward of at least the leading edge of each fan blade and aft of at least the trailing edge of each fan blade. The heat resistance ring is made of titanium or other suitable material. Additionally, one or more stiffener rings may be shrink interference fit on the outside diameter of the fan case. The containment ring and stiffener rings can reduce the flight weight of the fan case and lower the material costs, while increasing the containment strength of the fan case. Other embodiments are described and claimed. | 09-25-2008 |
20080304953 | AUGMENTED VANELESS DIFFUSER CONTAINMENT - A containment system comprises at least one passage obstructer extending from a housing inlet cover through a diffuser passage and into a housing back cover. The passage obstructer includes a fastener portion, such as a bolt, and an obstructing portion extending from and integral to a shaft of the fastener portion. The diameter of the obstructing portion is less than the diameter of the shaft, allowing the obstructing portion to bend upon impact with a burst impeller fragment. | 12-11-2008 |
20090067979 | COMPOSITE CASE ARMOR FOR JET ENGINE FAN CASE CONTAINMENT - A gas turbine fan blade containment assembly includes a fan case having an inner surface surrounding a jet engine fan and an outer surface. Mounted on the inner surface and across a blade containing region of the fan case is a load spreader layer for initially receiving a point load from a fan blade release (a “blade-out event”). A band layer is mounted to an outer surface of the fan case for carrying at least a portion of a hoop tensile load on the fan case resulting from the blade-out event, and separator film layer is mounted between the outer surface of the fan case and the band layer to retard the formation of stress concentrations in the band layer. In one embodiment, the load spreader layer includes a plurality of circumferentially-arrayed load spreader layer segments. | 03-12-2009 |
20090067980 | Pressure relief arrangement for a pump - A pressure relief arrangement for a pump, which includes a pump housing assembly with a pumping chamber therein, is provided in the pump housing assembly of the pump and includes a section mounted for movement between a normal operating position and a venting position, further includes a shearing element adapted to retain the section in the normal operating position, the section being mounted such that upon pressure within the pumping chamber increasing to a specified level, the pressure acts on the section and the shearing element will fail thereby permitting movement of the section from the normal operating to the venting position. | 03-12-2009 |
20090110538 | GAS TURBINE ENGINE BLADE CONTAINMENT USING WIRE WRAPPING - A blade containment of a gas turbine engine comprises a casing defining an annular wall radially spaced from and immediately surrounding a plurality of blades radially extending from a rotor, and at least one layer of metal wires wrapped around and directly attached to the annular wall. | 04-30-2009 |
20090155044 | COMPOSITE CONTAINMENT CASINGS HAVING AN INTEGRAL FRAGMENT CATCHER - Composite containment casings including a body having an interior and a fragment catcher integrally joined to the interior of the body of the containment casing. | 06-18-2009 |
20090175714 | SECONDARY BLADE PORTION CONTAINMENT DEVICE - A device that deploys during a blade portion failure that encompasses the engine casing is provided to prevent damage caused by the failure. A blade containment device such as a flexible interwoven structure or a net encompasses the engine casing and the blade failure path, or is embedded in the engine casing, and deploys in the event of a blade failure, such as the breaking of an engine blade. The net deploys when the blade portion has failed and has started expanding along the blade failure path, and may include a number of links attached to one another. Upon impact with a broken blade portion, thus transferring the kinetic energy of the blade portion to the net, some or all of the links may break off from each other, thus allowing the net to deploy and dissipating the kinetic energy generated by the expanding broken blade. Consequently, the blade remains contained inside the net, and blade containment is improved. | 07-09-2009 |
20090214327 | Fan track liner assembly - A fan track liner within a rotor blade assembly | 08-27-2009 |
20100014956 | FLUID FLOW MACHINE FEATURING A GROOVE ON A RUNNING GAP OF A BLADE END - A fluid-flow machine has at least one row of blades | 01-21-2010 |
20100028129 | Fan casing for a gas turbine engine - A fan casing for a gas turbine engine has a fan track liner extending only over an upstream part of the fan blades, and the local stiffness and internal shape of the casing are arranged to promote the break-up of a released fan blade while permitting the leading edge region of the blade to pass through the fan track liner and be contained by the fan casing. This arrangement is particularly suitable for fan blades in which the stiffness and compressive strength are significantly higher in the leading edge region than in the remainder of the blade; for example, hollow metal fan blades or composite fan blades having a metal leading edge cap. | 02-04-2010 |
20100028130 | Fan casing for a gas turbine engine - A fan casing for a gas turbine engine has a fan track radially outward of the fan blades, and the fan track has sufficient strength and stiffness that, if a blade is released, it is broken up and deflected by the fan track rather than passing through to a containment system as in known arrangements. Optionally, a weakened region in the fan track may be provided, so that the leading edge portion of the blade will penetrate the fan track and be contained within the fan casing. This is particularly suitable for fan blades in which the stiffness and compressive strength are significantly higher in the leading edge region than in the remainder of the blade; for example, hollow metal fan blades or composite fan blades having a metal leading edge cap. | 02-04-2010 |
20100150696 | FAN CASING FOR A JET ENGINE - A fan casing ( | 06-17-2010 |
20100202872 | MULTILAYER SHIELDING RING FOR A FLIGHT DRIVING MECHANISM - A shielding ( | 08-12-2010 |
20100266384 | GAS TURBINE ENGINE CASING ASSEMBLY - High bypass ratio turbofan propulsion engines are designed with a two-step approach to surviving foreign object damage to the fan assembly. First, a containment system encircling the fan assembly to capture any part of a released fan blade in the event of damage occurring, and two in order to cope with the vibrations resulting from a rotating unbalanced fan assembly the support structure for the bearing of the rotating assembly is constructed with frangible parts to introduce a snubber gap to permit the rotating, unbalanced fan assembly and bearing to orbit thereby to reduce the resulting vibrations. However, in the case of very wide chord fan assemblies, the largest acceptable snubber gap is insufficient to reduce the induced vibrations. The present solution is to incorporate into the containment system, and behind a fan track liner encircling the fan blades, at least one severance member having a cutting edge that will impact the tips of the blades of an orbiting fan assembly thereby to trim the mass distribution of the fan blades in order to reduce the vibrations caused by the out of balance forces. | 10-21-2010 |
20100329843 | PANEL FOR SUPPORTING ABRADABLE MATERIAL IN A TURBOMACHINE - A panel for supporting abradable material in a turbojet, the panel comprising a rigid support for fastening to an inside wall of a fan casing and having one face covered in a laminated structure carrying a layer of abradable material, the laminated structure comprising sheets of fibers embedded in a polymer, and comprising an upstream portion covered by the abradable material and a downstream portion that extends beyond the abradable material, the thickness of the downstream portion being greater than the thickness of the upstream portion and being capable of withstanding ice impacts. | 12-30-2010 |
20110038706 | TURBINE SECTION ARCHITECTURE FOR GAS TURBINE ENGINE - A turbine section of a gas turbine engine is described, which includes an aftmost rotor extending, an aftmost stator located upstream of the aftmost rotor, and a second to last aftmost rotor located upstream of the aftmost stator. The second to last aftmost rotor being spaced apart a first axial distance from the aftmost stator. A turbine exhaust case is located downstream of the aftmost rotor and includes an inner radial wall and an outer radial wall defining a main gas path duct downstream of the aftmost rotor. The turbine exhaust case being axially spaced apart from the aftmost rotor a second axial distance that is greater than the first axial distance. | 02-17-2011 |
20110076132 | CONTAINMENT CASING FOR AN AERO ENGINE - A containment assembly for a turbo fan engine, has a casing arranged in use around a rotatable fan, to form a duct for the fan and a liner element disposed on an interior surface between the casing and blades of a rotatable fan. The liner element includes a body portion mounted in a recess in the casing and a wall portion arranged to form part of an inner wall of the duct. The wall portion and the body portion being attached and defining a containment cavity therebetween for containment of a detached fan blade fragment in use, wherein the wall portion has a moveable portion movable between a first configuration in which it lies substantially flush with the inner wall of the duct, and a second configuration in which it provides an opening through which a fan blade fragment can enter the containment cavity. | 03-31-2011 |
20110081227 | IMPACTOR CONTAINMENT - An impactor containment system including a laminate material, the laminate material having a face sheet, a cellular filling providing a crushable layer one side of which layer is arranged on the face sheet, and a stiff backing layer arranged on other side of the crushable layer, wherein the face sheet is provided with zones of weakness. | 04-07-2011 |
20110217156 | CONTAINMENT CASING - A containment casing is provided comprising a radially outer layer; an intermediate energy absorbing layer, and a retention framework for retaining an aerofoil blade in the event of detachment of whole or part of the blade. The retention framework is distributed axially and circumferentially along the casing and extends substantially radially inwardly at least partially through the intermediate energy absorbing layer. | 09-08-2011 |
20120039703 | FRAGMENT CONTAINMENT ASSEMBLY AND METHOD FOR ADDING A FRAGMENT CONTAINMENT ASSEMBLY TO A TURBINE - A fragment containment assembly for a turbine is provided. The fragment containment assembly includes a plurality of bands disposed around a shroud of the turbine and positioned such that the shroud is disposed between blades of the turbine and the bands along radial directions outwardly extending from a shaft of the turbine. The bands include a material having a first modulus of toughness parameter that is greater than a second modulus of toughness parameter of the shroud at temperatures of at least 260 degrees Celsius. The bands are disposed around the shroud to prevent debris of the turbine from being released outside of the bands along the radial directions caused by failure of the turbine. | 02-16-2012 |
20120134774 | GAS TURBINE ENGINE BLADE CONTAINMENT ARRANGEMENT - A gas turbine engine blade containment arrangement comprises a casing, a first layer of cellular material arranged within the casing, a septum layer within the first layer of cellular material, a second layer of cellular material within the septum layer, a strong and ductile layer within the second layer of cellular material and a layer of abradable material within the strong and ductile layer. | 05-31-2012 |
20120219400 | VACUUM PUMP - A turbomolecular pump includes a drag pump unit constituted with a rotational cylinder portion disposed at a rotor and a fixed cylinder ( | 08-30-2012 |
20120224949 | TURBOMACHINE CASING ASSEMBLY - A turbomachine casing assembly including a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine, a second casing element located radially distal to the first casing element is provided. A void is provided between a radially proximal face of the first casing element and a radially proximal face of the second casing element, at the first end of the first casing element. The first end of the first casing element is located against a corresponding first end of the second casing element by an energy absorbing element, with the first casing element; including a cantilever. The cantilever is arranged in a region extending along the first casing element from the first end; and having a pivot axis at a mid portion thereof. | 09-06-2012 |
20130136577 | TURBOMACHINE CASING ASSEMBLY - A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine and a second casing element located radially distal to the first casing element, with a void being defined between the first and second casing elements. Each of the first and second casing elements includes, at a first end thereof, respective co-operating first and second interface portions. In the event that an aerofoil element becomes detached from the turbomachine and impacts the first casing element, the second interface portion; slides along the first interface portion and the first end of the first casing element enters the void. | 05-30-2013 |
20130149103 | BALLISTIC MATERIALS FOR ENHANCED ENERGY ABSORPTION AND FAN CASINGS INCLUDING THE SAME - Ballistic materials for enhanced energy absorption and fan casings for turbine engines including the same are provided. A hybrid ballistic material comprises a first ballistic fabric and at least one individual member woven through at least a portion of the first ballistic fabric. The fan casing comprises at least one layer of a first crushable material circumscribing a fan containment case. A ballistic material comprising a net-like ballistic material or the hybrid ballistic material circumscribes the at least one layer of the first crushable material. At least one layer of a second crushable material may circumscribe the ballistic material with the ballistic material disposed between the at least one layer of the first and second crushable materials. A containment covering is an outermost layer of the fan casing. | 06-13-2013 |
20130216353 | GUIDE APPARATUS FOR TURBOMACHINES - The invention relates to a guide apparatus for turbomachines, in particular for Francis or Kaplan turbines or pumps or pump turbines having a plurality of guide blades which can be actuated via in each case one link on a common adjusting member. Here, every guide blade or every second guide blade can be equipped with a bending element. A bending-failure link can have a screw connection and a bending body element. The screw connection is prestressed and is configured with a defined fracture cross section. The triggering force on the bending-failure link and the holding force after a fracture of the bending element can therefore be selected independently of one another. The guide blades are protected against damage by foreign bodies in the guide apparatus. | 08-22-2013 |
20130236291 | DEVICE FOR UNCOUPLING A BEARING CARRIER - A device for uncoupling a bearing carrier in a turbomachine, the bearing carrier including an upstream part and a downstream part including a plurality of upstream orifices respectively facing a plurality of downstream orifices. The uncoupling device includes rupture screws each passing through an upstream orifice and a downstream orifice, and at least a mechanism for double centering of a rupture screw with respect to the upstream orifice and to the downstream orifice respectively. The mechanism for double centering is independent of the upstream and downstream parts of the bearing carrier and of the rupture screw, and is configured to collaborate with the upstream part of the rupture screw such that when the rupture screw breaks, the upstream part carries with it the mechanism for double centering. A turbomachine can include such an uncoupling device. | 09-12-2013 |
20130336761 | TURBOMACHINE CASING ASSEMBLY - A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine, a second casing element located radially distal to the first casing element and one or more arcuate fence elements positioned between the first and second casing elements. Following impact of a detached fan blade, a radially outward movement of the first casing element causes the or each fence element to project into the air flow passing through the turbomachine. | 12-19-2013 |
20130336762 | BOLT-FASTENING STRUCTURE FOR TURBOMOLECULAR PUMP AND TURBOMOLECULAR PUMP THEREOF - A bolt fastening system for a turbomolecular pump wherein a first member is fastened in an axial direction with respect to a second member by multiple bolts arranged concentrically with respect to a rotor shaft center. The bolt-fastening system equipped with multiple pairs of non-penetrating pinholes arranged concentrically with respect to a rotor shaft center and formed opposing one another in respective opposing faces of the fastened first and second members, and equipped with pins provided for each pair of pinholes and inserted into the pairs of pinholes. When the size of a gap between a bolt and a bolt hole formed in the first member is Db, and a sizes of the gaps between the pins and the pinholes formed in the first and second members are Dp1 and Dp2, the gap sizes Db, Dp1, and Dp2 satisfy the equation Db≧(Dp1+Dp2). | 12-19-2013 |
20140072402 | WIND TURBINE - Wind turbine having a yaw system that comprises an annular gear, a plurality of motors, and a gear system having a gearbox and a pinion for each of the motors. Each of the gear systems is arranged to transmit a torque from the related motor to the annular gear. Moreover, at least one of the gear systems comprises a rotatable component having a frangible joint between a first part and a second part of the gear system. This joint is adapted to be broken once, during operation, the first part receives a torque from the annular gear that is greater by a predetermined amount than a torque received from the second part, said breaking of the joint causing the first part to be dragged by the annular gear independently from the second part. | 03-13-2014 |
20140072403 | CONTROL DEVICE OF POWER TRANSMISSION DEVICE - By a control processing of the sliding-mode control using a switching function configured from a first variable component, which is a deviation between an observed value and a desired value of a secondary power imparted to a secondary element ( | 03-13-2014 |
20140186154 | PUMP PRESSURE RELIEF SYSTEM - A pump features a casing assembly having a region through which high velocity fluid and solids circulate, a chamber where they do not, an aperture that allows a related-chamber to be in fluidic communication with the region, but not the circulating high velocity fluid and solids, and a corresponding aperture to allow the related-chamber to communicate with an external region outside the casing assembly; and a rupture disc received in the corresponding aperture to close the related-chamber subjects the related-chamber and the rupture disc to pressure contained within the region and to release pressure exceeding a predetermined relief pressure of the rupture disc from the related-chamber to the external region or location, and exhaust piping couple the rupture disc to provide a path for escaping vapor and solids to be directed to the external region or location where the energy can be dissipated. | 07-03-2014 |
20140255152 | FAN TRACK LINER DESIGNED TO YIELD NEXT TO FAN CASE HOOK - A containment system for a gas turbine engine includes a fan track assembly for use with a containment case. The fan track assembly includes a body of collapsible material that is positioned within a cavity of the fan case, and voids are provided for providing space in the event of a catastrophic blade failure. Various configurations of the fan track liner assembly are provided along with various mounting methodologies for securing the track liner assembly to the fan case of a gas turbine engine. | 09-11-2014 |
20140286748 | FAN CONTAINMENT CASE WITH THERMALLY CONFORMING LINER - A fan section of a gas turbine engine includes a fan containment case assembly includes an outer case of an aluminum alloy. The outer case extends circumferentially around an axial centerline. A thermally conforming liner assembly is located inwardly of the outer case. The thermally conforming liner assembly includes a circumferential liner of an aluminum alloy. A ballistic liner is located between the outer case and the thermally conforming liner assembly. | 09-25-2014 |
20140363270 | TURBINE CASING HAVING REINFORCEMENT ELEMENTS IN THE CONTAINMENT AREA - A turbine casing ( | 12-11-2014 |
20150016956 | COMPLIANT INTERMEDIATE COMPONENT OF A GAS TURBINE ENGINE - One aspect of present application provides an intermediate structure in a gas turbine engine. The intermediate structure is positioned between a first component and another component. The first component may be a composite component. The components may be interlocking. The intermediate structure may be load bearing. Also disclosed is a method using the intermediate structure. | 01-15-2015 |
20150016957 | CERAMIC COMPONENT FOR A TURBOMACHINE - A ceramic component for a turbomachine, the ceramic component ( | 01-15-2015 |
20150139779 | GAS TURBINE ENGINE - A fan containment system comprising an annular casing element and a hook projecting in a generally radially inward direction from the annular casing element. A fan track liner is connected to the hook via a fastener. The fan track liner has a forward end proximal to the hook and a rearward end distal to the hook. A pivot member protrudes radially inward from the annular casing element and is arranged and positioned between the forward and rearward end of the fan track liner such that a forward portion of the fan track liner is pivotable about the pivot member, so that upon release of a fan blade the forward portion of the fan track liner pivots about the pivot member into a voidal region provided between the annular casing element and the forward portion of the fan track liner to encourage engagement of the hook with a released fan blade. | 05-21-2015 |
20150147156 | GAS TURBINE ENGINE - A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises a fan case having an annular casing element for encircling an array of fan blades and a hook projecting in a generally radially inward direction from the annular casing element. The fan containment system further includes an annular fan track liner comprising a plurality of adjacent arcuate fan track liner panels. Each of the plurality of fan track liner panels is connected to the fan case at the hook via one or more fasteners configured to permit movement of the fan track liner panel relative to the hook such that the fan track liner panel can pivot towards the annular casing element when a released fan blade impacts the fan track liner panel. | 05-28-2015 |
20150330247 | GAS TURBINE ENGINE - A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises an annular casing element for encircling an array of fan blades. An annular fan track liner is positioned substantially coaxial to the annular casing element. A hook projects in a generally radially inward direction from the annular casing element and is positioned axially forward of an array of fan blades when the fan containment system is fitted around said fan blades. Tabs protrude from the hook in a generally rearward direction and are spaced circumferentially along the hook. Fasteners connect the fan track liner to the tabs. The fasteners are configured so as to permit movement of the fan track liner towards the annular casing element when the fan track liner is impacted by a released fan blade. | 11-19-2015 |
20150345326 | FLOWPATH CARTRIDGE LINER AND GAS TURBINE ENGINE INCLUDING SAME - A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a containment case and a cartridge liner carried therein. A ballistic liner encircles at least a portion of the cartridge liner and is attached thereto. | 12-03-2015 |
20160003084 | THERMALLY CONFORMABLE LINER FOR REDUCING SYSTEM LEVEL FAN BLADE OUT LOADS - A fan case for a gas turbine engine includes a fan case surrounding a fan with fan blades. A liner is disposed between the fan case and the fan and is spaced a radial distance from the fan case. A torque stop is arranged between the fan case and the liner. A method for reducing fan case liner loads is also disclosed. | 01-07-2016 |
20160016645 | Breakaway Shaft - A drive pod of a watercraft such as a boat may be designed to break off the hull of the boat in the event of an underwater collision involving the drive pod. A shaft assembly that transmits power from the engine in the hull to blades or a jet in the drive pod is designed to break at a precise point so that seals in the hull and seals in the drive pod are protected from damage. The shaft assembly may include an axial blind hole with an undercut at a bottom of the blind hole. A pin may be inserted to reinforce the shaft above the undercut. | 01-21-2016 |
20160053632 | FAN CONTAINMENT CASES FOR FAN CASINGS IN GAS TURBINE ENGINES, FAN BLADE CONTAINMENT SYSTEMS, AND METHODS FOR PRODUCING THE SAME - Fan blade containment systems and methods for producing the same are provided. The fan blade containment system comprise a first ballistic material configured to be wrapped in overlapping layers around a fan casing to form a containment covering of a fan containment case for the fan casing. A plurality of patches comprised of a second ballistic material are configured to be loosely disposed between adjacent overlapping layers of the first ballistic material with each patch partially overlapping a circumferentially adjacent patch. | 02-25-2016 |
20160061049 | WEAR MONITOR FOR AN ABRADABLE LINER FOR A FAN OF A GAS TURBINE ENGINE - An abradable liner for a gas turbine engine fan stage, comprising: a plurality of abradable layers bonded together, wherein at least one visual indicator is embedded in the plurality of abradable layers | 03-03-2016 |
20160069208 | COMPRESSOR, TURBINE AND TURBOCHARGER - A compressor for compressing a gas, the compressor comprising: a housing having an axial inlet and an annular outlet volute; an impeller wheel including a plurality of blades, the wheel being rotatably mounted within the housing between the inlet and outlet volute; the axial inlet being defined by a tubular inducer portion of the housing and the annular outlet volute being defined by an annular diffuser passage surrounding the impeller, the diffuser having an annular outlet communicating with the outlet volute; the housing having an inner wall defining a surface located in close proximity to radially outer edges of the impeller blades which sweep across the surface as the impeller wheel rotates; wherein the compressor housing incorporates at least one section comprised of a deformable, energy absorbing material arranged to deform and absorb energy generated as a result of impeller wheel failure. A turbine incorporating similar deformable, energy absorbing materials is also described, as are turbochargers incorporating such a compressor and/or turbine. | 03-10-2016 |
20160097299 | FAN TRACK LINER ASSEMBLY - A fan track liner assembly for a ducted fan engine which provides for ease of installation and replacement. The assembly includes a plurality of panels; and a plurality of fastening members which are arranged to secure the panels to the fan case of the engine, wherein: each fastening member has a base portion and an elongate arm member, and further wherein: the base portion has an attachment portion which is used to secure the fastening member to the fan case; and the arm member extends from the base portion, and each panel has slotted edge portions on opposing edges at one end of the panel which are each arranged to engage with respective arm members of fastening members on either side of the panel when the panel is assembled with the fastening members by sliding the panel onto the fastening members or vice-versa. | 04-07-2016 |
20160097300 | FAN TRACK LINER ASSEMBLY - A fan track liner assembly for ducted fan engine which provides for reduced strain and deformation of front of fan case in the event of a fan blade off event. Various assemblies are proposed. In one aspect, assembly includes fan track liner panel and plurality of fasteners which are arranged to secure panel to fan case of engine, wherein: a forward portion of panel includes hinged portion which operates as trapdoor to permit blade or blade fragment to pass through, and fasteners are arranged to fail in the event of blade or blade fragment passing through trapdoor causing panel to be displaced rearwards in fan case. Other aspects provide for reduced height of support on fan case for attaching fan track liner and for collapsible comb box. | 04-07-2016 |
20160130975 | COLLAPSIBLE SUPPORT STRUCTURE FOR A GAS TURBINE ENGINE - Described is a shaft support system for a gas turbine engine comprising: a rotatable fan shaft; first and second support structures extending in parallel from the shaft to a load bearing structure to provide radial location of the shaft within an engine casing, wherein the first support and second support structures include first and second respective mechanical fusible joints; wherein the first fusible joint is a two-stage fuse which partially fails within a first predetermined load range, the second fusible joint fails within a second predetermined load range which is different to the first load range, and the first fusible joint fully fails only when the second fusible joint has failed. | 05-12-2016 |
20160160678 | GROUND HANDLING SYSTEM FOR A COMPOSITE FAN CASE AND A METHOD OF USING THE SAME - The present disclosure relates generally to a system for handling a gas turbine engine fan case. The system includes a composite fan containment case including a case outer surface, a case inner surface, and at least one main case aperture extending from the case outer surface through the case inner surface, and at least one shear puck, the at least one shear puck including a shear puck protrusion; wherein the shear puck protrusion of each of the at least one shear pucks is disposed within a respective one of each of the at least one main case apertures. | 06-09-2016 |
20160201502 | INTEGRAL PART WEAR INDICATOR SYSTEM, METHOD AND APPARATUS | 07-14-2016 |
20160377090 | NACELLE INLET WITH EXTENDED OUTER BARREL - A nacelle inlet is provided for an aircraft propulsion system. This nacelle inlet includes an outer barrel, a bulkhead and a plurality of supports. The outer barrel extends around an axis and along the axis to an aft end. The bulkhead is within and connected to the outer barrel. An aft portion of the outer barrel projects axially aftward from the bulkhead to the aft end. The supports are disposed around the axis and next to the bulkhead. The supports are configured to support the aft portion of the outer barrel. | 12-29-2016 |
20170234329 | CONTAINMENT CASE TRENCH FILLER LAYER AND METHOD OF CONTAINING RELEASABLE COMPONENTS FROM ROTATABLE MACHINES | 08-17-2017 |