Class / Patent application number | Description | Number of patent applications / Date published |
060797000 | For motor | 60 |
20080307795 | EXHAUST CASING HUB COMPRISING STRESS-DISTRIBUTING RIBS - An exhaust casing hub comprises a hub center ( | 12-18-2008 |
20090056343 | ENGINE MOUNTING CONFIGURATION FOR A TURBOFAN GAS TURBINE ENGINE - An engine mounting configuration reacts engine thrust at an aft mount. The engine mounting configuration reduces backbone bending of the engine, intermediate case distortion and frees-up space within the core nacelle. | 03-05-2009 |
20090064685 | DEVICE AND METHOD FOR MOUNTING A TURBINE ENGINE - A device and a method for mounting a turbine engine, e.g., a gas turbine system, are described, in which a rotor unit is mounted to rotate inside a stationary external housing, having at least two supports for taking up the weight of the turbine engine, these supports being arranged at a spacing from one another in an axial longitudinal direction in relation to the external housing and at one side being articulated directly or indirectly on the external housing and at the other being supported directly or indirectly on a base frame. At least one support provides at least one support face which is supported exclusively in partial regions on at least two support plate elements. The at least one support face of the support is in operational engagement with the base frame by way of the support plate elements. | 03-12-2009 |
20090120102 | TURBINE ENGINE FRAME HAVING AN ACTUATED EQUILIBRATING CASE - The turbine engine assembly has a frame and a turbine engine spool. A strut couples the frame to the spool and an actuator couples the strut to the frame. The actuator has a spring. | 05-14-2009 |
20090165463 | Fixing System for a Component of a Turbojet Pod - The invention concerns a fixing system for at least one component of a pod of a turbojet on an engine strut to which the pod is attached and comprising at least one coupling zone provided by the component capable of co-operating with at least one complimentary coupling zone provided by the strut, and fixing means for providing with complementary fixing means a rigid and detachable connection between said component and the strut. The invention is wherein the fixing means and the complementary fixing means are capable of slightly pivoting relative to each other, as well as relative to a corresponding pod. | 07-02-2009 |
20090183512 | MOUNTING SYSTEM FOR A GAS TURBINE ENGINE - A mounting system for a gas turbine engine includes a thrust ring and a linkage assembly. The linkage assembly is at least partially received by the thrust ring. The linkage assembly reacts at least a side load and a thrust load communicated from the thrust ring. | 07-23-2009 |
20090255271 | STRUCTURAL NACELLE - The present invention relates, on the one hand, to a nacelle ( | 10-15-2009 |
20100024435 | NACELLE FOR TURBOFAN - The nacelle of the invention includes an air-inlet front section, a middle section for encasing the fan of the turbofan ( | 02-04-2010 |
20100043450 | SYSTEM FOR ATTACHING AN ENGINE TO THE STRUCTURE OF AN AIRCRAFT, SUCH AS A SAIL WING AIRCRAFT - System for attaching an engine to the structure of an aircraft, such as a sail wing aircraft. The system includes an upper beam which is firmly fixed at its front end to a first frame mounted on the aircraft structure. The upper beam is in addition firmly fixed at its median part to a second frame located to the rear of the first frame. The engine is hooked beneath the upper beam. The system is orientated in relation to a longitudinal axis X, a transverse axis Y and a vertical axis Z. Two front engine attachment points are arranged symmetrically on either side of the vertical median plane of the engine. The front attachment points include a shaft ( | 02-25-2010 |
20100132376 | MID TURBINE FRAME FOR GAS TURBINE ENGINE - A mid turbine frame of a gas turbine engine includes an outer case which supports a spoke casing co-axially positioned therein. The spoke casing has load transfer spokes extending radially from an inner case and secured to the outer case. A load transfer device is provided to transfer load from the spokes to the outer case in addition to load transfer through a first group of fasteners securing the spokes to the outer case, thereby forming a secondary load transfer path from the spokes. The load transfer device includes an opening of the outer case into which at least some of the spokes are inserted. | 06-03-2010 |
20100132377 | FABRICATED ITD-STRUT AND VANE RING FOR GAS TURBINE ENGINE - A gas turbine engine mid turbine frame having an annular interturbine duct and vane ring assembly includes a duct having outer and inner duct walls of sheet metal interconnected by radial hollow struts of sheet metal and a vane ring is connected to the duct to provide the assembly. The interturbine duct and vane ring assembly may be provided within a mid turbine frame in a manner which is independent of a bearing load path through the mid turbine frame. | 06-03-2010 |
20100132378 | HYDRAULIC SYSTEM FOR TRANSMISSION OF FORCES BETWEEN AN AIRCRAFT TURBOPROP AND AN ATTACHMENT DEVICE - This invention relates to a force transmission system ( | 06-03-2010 |
20100162726 | Mobile platform system for a gas turbine engine - A system for moving an auxiliary component of a gas turbine engine is disclosed. The system may have a mobile support platform configured to support the auxiliary component during operation of the gas turbine engine. The system may further have at least one guide assembly operably connected to the mobile support platform and configured to guide movement of the mobile support platform. The system may also have a drive assembly operably connected to the mobile support platform and configured to impart movement of the mobile support platform between an elevated position and a lowered position. | 07-01-2010 |
20100275614 | STRUCTURAL REINFORCEMENT STRUT FOR GAS TURBINE CASE - A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions. | 11-04-2010 |
20100287950 | SUPPORT LINKS WITH LOCKABLE ADJUSTMENT FEATURE - A cam-type apparatus is included in a support link between outer and inner cases of gas turbine engines for centering the cases one to another. The cam-type apparatus is lockable to allow locking an adjusted position of the cam-type apparatus. | 11-18-2010 |
20110048029 | TURBOMACHINE CORE COUPLING ASSEMBLY - A coupling assembly for an engine core of a turbomachine is provided. The coupling assembly comprises a duct having a substantially circular shape and surrounding the engine core, and a plurality of coupling struts, each coupling strut extending only in a substantially vertical direction relative to the direction of gravity when the engine core is at a rest position with zero pitch and zero roll, each of the plurality of coupling struts coupling the engine core to the duct. | 03-03-2011 |
20110146299 | ANNULUS FILLER ASSEMBLY FOR A ROTOR OF A TURBOMACHINE - An annulus filler assembly for a rotor of a turbomachine, the assembly comprising: an annulus lid ( | 06-23-2011 |
20110154831 | AIRCRAFT ENGINE ASSEMBLY COMPRISING A TURBOJET ENGINE WITH REINFORCING STRUCTURES CONNECTING THE FAN CASING TO THE CENTRAL CASING - An aircraft engine assembly including an annular structure surrounding a central casing and mechanically connected to the central casing by the intermediary of a mounting mechanism. To each of the first and second engine mounts is associated a reinforcing structure forming a shear plane, fixedly connected: in an area of the annular structure at a first anchoring point; in an area of the fan casing at a second anchoring point; and in an area of a structural arm or of the intermediate casing at a third anchoring point. The structure extends along a radial imaginary plane passing through an anchoring point of the mount on the fan casing. | 06-30-2011 |
20110197595 | ENGINE ASSEMBLY FOR AN AIRCRAFT COMPRISING ATTACHMENTS FOR ENGINES OFFSET BELOW ON THE FAN FRAME - An aircraft engine assembly including an attachment mechanism of a turbojet onto a rigid structure of a mounting strut, including a first, second, and third forward engine attachment for taking up thrust loads brought onto the fan frame, and arranged such that the third attachment passes through a first diametrical plane of the turbojet, the first and second attachments being disposed on one side and another of the first plane. The first and second forward engine attachments are respectively brought to the fan frame at two points, situated beyond the second diametrical plane of the turbojet, orthogonal to the first diametrical plane, with respect to the third attachment. | 08-18-2011 |
20120111023 | SUPPORTING STRUCTURE FOR A GAS TURBINE ENGINE - A supporting structure for a gas turbine engine includes at least one annular member, and a plurality of circumferentially spaced elements that extend in a radial direction of the annular member and that are connected to the annular member. At least one of the circumferentially spaced elements has an airfoil shape in cross section. The annular member includes at least two substantially flat panel segments that are arranged side by side in a circumferential direction of the annular member. The panel segments are connected to each other in a connection region that extends along facing end parts of the two panel segments. The airfoil shaped element is connected to the annular member at the connection region. A mean camber line of the airfoil shaped element at least along a portion of its length is inclined in relation to an axial direction of the annular member, and the connection region at least along a portion of its length is inclined in relation to the axial direction of the annular member. The inclined portion of the connection region is directed substantially in parallel to the inclined portion of the mean camber line of the airfoil shaped element. A gas turbine engine including a supporting structure of the above type is also provided. | 05-10-2012 |
20120167592 | MOUNTING SYSTEM FOR A GAS TURBINE ENGINE - A mounting system for a gas turbine engine includes a mounting linkage assembly and a tangential link positioned generally transverse to the mounting linkage assembly. The mounting linkage assembly reacts at least a thrust load. The tangential link reacts at least a vertical load, a side load, and a torque load of the gas turbine engine. | 07-05-2012 |
20120227415 | POSITIONING ARRANGEMENT FOR COMPONENTS OF A PRESSURE VESSEL AND METHOD - The positioning arrangement comprises at least one pair of complimentary rounded recesses, each recess being provided on the mating face of the corresponding component. One ball is positioned between each pair of complementary recesses. | 09-13-2012 |
20120260669 | FRONT CENTERBODY SUPPORT FOR A GAS TURBINE ENGINE - A front center body support for a gas turbine engine includes a front center body section, a bearing section and a frustro-conical interface section, the frustro-conical interface section between the front center body section and the bearing section. | 10-18-2012 |
20120324907 | MOUNTING ASSEMBLY - A mounting assembly for attaching a ducted fan gas turbine engine that includes an intake, a propulsive fan, a fan case surrounding the fan, and a core engine. The air intake is attached to the front of the fan case such that loads acting on the air intake are transmitted to the fan case. The mounting assembly includes: a support structure extending in an axial direction of the engine and having a rearward region adapted to attach to the aircraft; and a load distribution ring coaxial with and rearward of the fan case, adapted to join to the fan case, and joined to a forward region of the support structure. The support structure and the load distribution ring are adapted such that the primary load path for the loads transmitted to the fan case by the air intake is through the load distribution ring and the support structure. | 12-27-2012 |
20130014515 | LINK BETWEEN THE EXHAUST CASING AND A STRUCTURAL RING OF THE FAN DUCT OF A JET ENGINEAANM Bellabal; Francois RobertAACI FontainebleauAACO FRAAGP Bellabal; Francois Robert Fontainebleau FRAANM Seize; GuilhemAACI Corbeil EssonnesAACO FRAAGP Seize; Guilhem Corbeil Essonnes FRAANM Vincent; Thomas Alain ChristianAACI PalaiseauAACO FRAAGP Vincent; Thomas Alain Christian Palaiseau FR - An assembly including an outer ring of an exhaust casing, a structural ring of an external duct of a fan channel and of a two-flow jet engine that is concentric relative to the outer ring of the exhaust casing, and at least one first and second linking arm or rod forming a hyperstatic link by being attached by one end to the outer ring of the exhaust casing and, by the other end, to the structural ring. The link formed by the first linking arm or rod is configured to break when a predetermined load is exceeded, and the second linking arm or rod is configured to form a force-transmission path between the rings when the link is broken. | 01-17-2013 |
20130019609 | GAS TURBINE ENGINE SYSTEMS INVOLVING I-BEAM STRUTS - Gas turbine engine systems involving I-beam struts are provided. In this regard, a representative strut assembly for a gas turbine engine includes a first I-beam strut having first and second flanges spaced from each other and interconnected by a web, the first strut exhibiting a twist along a length of the web. | 01-24-2013 |
20130067931 | GAS TURBINE ENGINE ASSEMBLIES INCLUDING STRUT-BASED VIBRATION ISOLATION MOUNTS AND METHODS FOR PRODUCING THE SAME - Embodiments of a gas turbine engine assembly including a strut-based vibration isolation mount are provided, as are embodiments of a method for producing such a gas turbine engine assembly. In one embodiment, the gas turbine engine assembly includes a gas turbine engine and a vibration isolation mount. The vibration isolation mount includes, in turn, at least one three parameter axial strut having a first end attached to the gas turbine engine and having a second, opposing end configured to be attached to the airframe. The three parameter axial strut is tuned to minimize the transmission of vibrations from the gas turbine engine to the airframe during operation of the gas turbine engine. | 03-21-2013 |
20130074517 | GAS TURBINE ENGINE MOUNT ASSEMBLY - A forward mount assembly for connecting a pylon to an intermediate case of a gas turbine engine, the forward mount assembly includes a forward mount platform, a wiffle tree assembly, and first and second A-arms. The platform is connected to the pylon and is disposed adjacent the intermediate case. The wiffle tree assembly is connected to the forward mount platform through a first ball joint. The first A-arm is connected to a first side of the intermediate case and the second A-arm is connected to a second opposing side of the intermediate case. The first and second A-arms are mounted to the forward mount platform and are mounted to opposing ends of the wiffle tree. The aforementioned arrangement allows the first and second A-arms to react a thrust load at the intermediate case substantially parallel to a centerline axis of the gas turbine engine. | 03-28-2013 |
20130074518 | GAS TURBINE ENGINE TIE ROD RETAINER - An assembly for use with a gas turbine engine includes a tie rod and a connector. The tie rod, which is for extending radially outwardly from a latitudinal axis of the gas turbine engine, has a hollow length having a longitudinal axis and a base having a width in parallel to the latitudinal axis. The base has a counterbore disposed therein and is wider than a width of the length. The connector, for attaching the base of the tie rod to a bearing assembly of the gas turbine engine, has a hollow body having a shaft removably attaching, at a first end portion thereof, to the counterbore. The shaft and the counterbore are disposed in parallel with the longitudinal axis. | 03-28-2013 |
20130125560 | LATERAL TURBOJET IMPROVED IN ORDER TO LIMIT THE DEFORMATION THEREOF - A turbojet includes an intermediate casing outer shroud connected to a front suspension and a primary structure connected to a rear suspension; the shroud and the primary structure are held in a coaxial relationship by arms with at least some of the arms being shaped and/or arranged to deform in response to thrust from the turbojet by creating a deforming torque between the shroud and the primary structure in opposition to opposing stress generated by the thrust. | 05-23-2013 |
20130160465 | GAS TURBINE ENGINE SYSTEMS - A gas turbine engine | 06-27-2013 |
20130186105 | ANISOTROPIC VIBRATION ISOLATION MOUNTING ASSEMBLY - An anisotropic vibration isolation mounting assembly includes at least two three-parameter vibration isolators each having a first end configured for attachment to a rotating member assembly or a rotating member assembly housing and each having a second, opposing end configured for attachment to the rotating member assembly housing where the first end is configured for attachment to the rotating member assembly or to a system interface member where the first member is configured for attachment to the rotating member assembly housing. The at least two three-parameter vibration isolators are tuned anisotropically to minimize the transmission of vibrations during operation of the rotating machine. | 07-25-2013 |
20130227963 | ASSEMBLY FOR ATTACHING THE HANGERS FROM WHICH AN AIRCRAFT PROPULSION UNIT IS SUSPENDED - An assembly is designed to attach hangers from which an aircraft propulsion unit is suspended. The propulsion unit is intended to be suspended from a structural element of the aircraft. The propulsion unit includes a turbojet engine having a longitudinal axis and the attachment assembly having a clevis mount for attaching the hangers to a casing of the propulsion unit. The clevis mount is fixed to the casing by means designed to form a connection between the clevis mount and the casing at the external periphery of the casing. | 09-05-2013 |
20130319002 | NACELLE BIFURCATION FOR GAS TURBINE ENGINE - A nacelle structure for a gas turbine engine includes a core engine nacelle disposed about an engine axis and an outer nacelle disposed about the core engine nacelle. A bifurcation extends between the outer nacelle and the core engine nacelle along a bifurcation axis extending between the outer nacelle and the core engine nacelle. The bifurcation includes at least one mounting surface that is disposed at a non-normal angle relative to the bifurcation axis. | 12-05-2013 |
20130327058 | DEVICE FOR SUSPENDING A TURBOJET ENGINE - A turbojet is suspended by attachments including hinged links. An attachment includes a support including three branches with passages through which a pin passes, the pin being oriented generally parallel to a direction that is tangential to a casing and being hinged to a central branch of the support by a ball joint. | 12-12-2013 |
20130327059 | DRAINING DEVICE - A draining device for draining a fluid from an aircraft engine support strut includes a suction arrangement having an inlet and extending along a longitudinal main axis to form a plenum chamber and a drain tube fluidly connected to the aircraft engine support strut and extending along the longitudinal main axis, the drain tube ending by an outlet, the outlet of the drain tube terminating within the plenum chamber of the suction arrangement. An air flow entering the inlet of the suction arrangement causes a low-pressure region to be created within the plenum chamber, substantially downstream the outlet of the drain tube. | 12-12-2013 |
20140013771 | MID-TURBINE FRAME WITH THREADED SPOKES - A mid-turbine frame located in a gas turbine engine axially aft of a high-pressure turbine and fore of a low-pressure turbine includes an outer frame case, an inner frame case, and at least a first spoke connecting the outer frame case to the inner frame case. The first spoke includes a tie rod having a first threaded surface and a connector having a second threaded surface. The first and second threaded surfaces overlap partially but not completely. | 01-16-2014 |
20140047850 | ASSEMBLY FOR MOUNTING A TURBINE ENGINE TO AN AIRFRAME - An assembly is provided for mounting a turbine engine to an airframe. The turbine engine extends along an axial centerline and includes an engine core mount and an engine exhaust mount. The assembly includes a thrust pin linkage connecting and extending axially between a core thrust pin and an exhaust thrust pin. The core thrust pin is adapted to connect to the engine core mount, and the exhaust thrust pin is adapted to connect to the engine exhaust mount. One of the core thrust pin, the exhaust thrust pin and the thrust pin linkage is also adapted to connect to the airframe. | 02-20-2014 |
20140069107 | TURBOPROP ENGINE WITH COMPRESSOR TURBINE SHROUD - A turboprop engine including an annular outer case including a mount ring for attachment to an aircraft along a plane to transfer loads from a propeller and having an annular flange extending radially inwardly therefrom within the plane, an annular turbine support case received within the outer case and connected to the outer case only through a direct connection with the annular flange allowing a limited relative pivoting motion between the turbine support case and the mount ring, and a turbine section including a rotor closely surrounded by a shroud with an annular tip clearance being defined therebetween, the shroud being directly connected to and located by the turbine support case. A method of isolating a turbine shroud from propeller loads in a propeller engine is also disclosed. | 03-13-2014 |
20140075957 | FORMED GUSSETS FOR BRACKETS ON GAS TURBINE ENGINES - Disclosed is a bracket mount assembly for use in a gas turbine engine. The bracket mount assembly includes a communicating member, a mount, and a bracket. The bracket is supported by a static engine structure, and is mounted to the communicating member by way of the mount. Further, the bracket includes a first wall and a second wall, as well as a bend positioned there between, and the bend includes a gusset. The gusset provides a depression in the bend. The gusset and the bracket are made from a single piece of metal. | 03-20-2014 |
20140102114 | IN-LINE REMOVABLE HEAT SHIELD FOR A TURBOMACHINE SUSPENSION YOKE - Heat shield device for a means of suspending an engine from an aircraft, the said device comprising panels able to be fixed to the said means, at least one of the said panels extending radially in the direction of the axis of the engine, characterized in that it further comprises a component configured to be fixed to the said engine and comprising a groove shaped in such a way that the lower end of the said panel can be inserted into it. | 04-17-2014 |
20140130512 | TURBINE ENGINE ATTACHMENT STRUCTURE - An attachment structure for attaching a power plant including unducted propellers to a fuselage of an aircraft, the attachment structure being connected by first and second fasteners to respective front and rear spars penetrating into the fuselage and fastened to a carrier structure of the aircraft, and including a central longitudinal beam secured at its front end to a first frame, arranged in the plane of the front spar, that is secured at its rear end to a second rear frame, cantilevered out and arranged upstream from the unducted propellers, and that is secured to a third intermediate frame, arranged in the plane of the rear spar between the first and second frames. The first, second, and third frames are connected together by force-takeup beams, an assembly as constituted in this way forming a cradle for receiving the power plant via a standard attachment. | 05-15-2014 |
20140165590 | TURBINE HUB RETAINER - A retainer for a gas turbine engine includes a center body, a plurality of struts, and a ring. The plurality of struts are connected to and extend outward from the center body. The ring is connected to the plurality of struts and is positioned aft of the center body with respect to a direction of airflow through the gas turbine engine. | 06-19-2014 |
20140190180 | FAIRING OF A GAS TURBINE STRUCTURE - A gas turbine structure includes a first housing and a second housing, one of the first and second housings being located around the other of the first and second housings such that a core flow passage is obtained between the first and second housings. The gas turbine structure further includes an elongate structural member extending in a structural member direction from the first housing to the second housing and the gas turbine structure further includes a fairing circumferentially enclosing at least a portion of the structural member. | 07-10-2014 |
20140202169 | ASSEMBLY FORMED BY A TURBINE ENGINE AND A SYSTEM FOR ATTACHING IT TO AN AIRCRAFT STRUCTURE - In an assembly including a bypass turbine engine and an attachment system attaching the turbine engine to an aircraft structure, the attachment system includes a mast, at least two rear attachments connecting the mast to two rear attachment points of the turbine engine, and a rear covering covering the rear attachments and providing a streamlined fairing. The rear covering includes two side walls, each including a first portion extending along and in proximity of the mast and extending rearwards, and a second portion projecting sideways relative to the first portion towards its outside, to cover the rear attachments. Each second portion is substantially a bulge and is connected to the first portion along a curved connection line extending between front and rear points situated substantially level with an inner longitudinal edge of the first portion to minimize the impact on a flow of bypass stream leaving the bypass passage. | 07-24-2014 |
20140250916 | SYSTEM AND METHOD FOR ALIGNING A GAS TURBINE ENGINE - A system and method for aligning a gas turbine engine. The system and method includes installing an alignment mount, determining whether the gas turbine engine is aligned and/or in a sufficiently aligned condition, and modifying a vertical position of the gas turbine engine at the alignment mount in response. The alignment mount includes an engine attachment, a ground attachment, and an expansion member configured to allow the engine attachment and the ground attachment to move relative to each other and maintain a load path therebetween. | 09-11-2014 |
20140260322 | SUPPORT MECHANISM FOR HEAVY STRUCTURE - To provide a support mechanism for a heavy structure, capable of accommodating thermal deformation of component parts of a device operated under high temperature condition, a support mechanism for supporting the heavy structure by suspending includes a fast pulley fixed to an inner wall of a package that accommodates the heavy structure which is an object being supported, a movable pulley to function cooperatively with the fast pulley, a rope-like connecting member having one end connected with the structure and movably wound on the fast pulley and the movable pulley, a counterweight unit coupled to the other end of the connecting member and including a counterweight having adjustable weight to utilize the weight of the counterweight to support the heavy structure, and a suspending device in the counterweight unit to suspend and position the heavy structure at a position upwardly relative to a normal support position. | 09-18-2014 |
20140283529 | SUPPORTING DEVICE FOR GAS TURBINE AND GAS TURBINE WITH THE SAME - A supporting device for a gas turbine includes a base frame; a fixing member installed on the base frame so as to support one end of a gas turbine; and an absorbing member installed on the base frame so as to support the other end of the gas turbine. The absorbing member having lower stiffness than the fixing member so as to deform in first and second directions when the gas turbine thermally expands. | 09-25-2014 |
20140290269 | DUCT BLOCKER SEAL ASSEMBLY FOR A GAS TURBINE ENGINE - A seal system for a gas turbine engine includes a cover plate with a radial flange; a seal carrier adjacent the cover plate; an outer compliant seal supported by the seal carrier; an inner compliant seal supported by the seal carrier, the inner compliant seal engaged with the radial flange; and a spring between the cover plate and the seal carrier. | 10-02-2014 |
20140290270 | ATTACHMENT PYLON FOR A TURBINE ENGINE - A pylon for attaching a turbine engine, the pylon configured to connect the engine to a structural element of an aircraft. The pylon includes a streamlined profile defined by two opposite lateral faces and defined longitudinally between a leading edge and a trailing edge. On each of its lateral faces the pylon includes a series of deflectors that are transversely spaced apart from one another and that define between them convergent and curved channels configured to accelerate air streams flowing within the channels on aircraft takeoff or in flight to deflect the air streams towards a jet of the engine. | 10-02-2014 |
20140360206 | AIRCRAFT POWERPLANT - An aircraft propulsion power plant for use in an aircraft includes one or more core engines housed in an airframe of the aircraft, one or more secondary propulsion units, each of the one or more secondary propulsion units being removably attached to the airframe, and one or more power transmission means, each of the one or more power transmission means being configured to transmit mechanical power from the or each core engine to a corresponding one of the or each secondary propulsion unit when the or each secondary propulsion unit is attached to the airframe. | 12-11-2014 |
20150007580 | METHOD OF PRODUCING SUSPENSION FOR A STRUCTURE IN A TURBOJET ENGINE USING A HYPERSTATIC TRELLIS WITH PRE-STRESSED LINK ELEMENTS - The invention relates to a method of manufacturing an assembly comprising a first structure ( | 01-08-2015 |
20150047369 | FIXED TURBINE ENGINE RECEIVER PART COMPRISING AN ASSEMBLY FOR HOLDING ANCILLARY SYSTEMS IN POSITION INSIDE A FIXED HOLLOW SHAFT - The invention relates to a fixed turbine engine receiver part comprising a fixed hollow shaft for carrying ancillary systems of a turbine engine, centered on the turbine engine axis, turbine engine ancillary systems, an assembly for holding ancillary systems in position situated inside the fixed hollow shaft. The assembly for holding ancillary systems in position comprises at least one first ancillary system support ring, having an axis substantially parallel with the turbine engine axis, a first distance sleeve for holding the first ancillary system support ring in position, having an axis substantially parallel with the turbine engine axis, the first distance sleeve bearing against the first support ring, such that the first support ring comprises a plurality of mutually separated through holes, each through hole defining a passage for at least one ancillary system, each through hole being traversed by at least one of the ancillary systems of the turbine engine. | 02-19-2015 |
20150047370 | METHOD FOR HOLDING AN ADAPTER PIECE ON A TUBULAR HOUSING OF A TURBO ENGINE, AND CORRESPONDING ADAPTER PIECE AND HOLDING SYSTEM - An adapting part is designed to be held on a casing of a turbo-engine, partially covering the casing. The adapting part includes, in the extension of one of its axial ends, a first connector to engage with a first complementary connector associated with the casing to form a sliding connection. The adapting part also includes, at its other axial end, a second connector to be secured to a second complementary connector associated with the casing to form a rigid connection. | 02-19-2015 |
20150052909 | FUEL CONTROL MODULE GAS VENT MANIFOLD - A fuel control module including a gas vent manifold is disclosed. The gas vent manifold includes a first gas vent portion including a first gas vent connection and a second gas vent portion including a second gas vent connection. The gas vent manifold also includes a condensation portion extending between the first gas vent portion and the second gas vent portion. The gas vent manifold further includes a condensation drain port fluidly connected to the condensation portion. The gas vent manifold also includes a plurality of connection ports. Each connection port is configured to fluidly couple the gas vent manifold to a vent line of one or more pneumatic valves. | 02-26-2015 |
20150075177 | DEVICE FOR SUSPENDING A CASING, A TURBINE ENGINE AND A PROPULSION ASSEMBLY - The invention relates to a device ( | 03-19-2015 |
20150114006 | AIRCRAFT ENGINE STRUT ASSEMBLY AND METHODS OF ASSEMBLING THE SAME - An engine strut for providing fan hub frame structural support and monitoring an air flow within an aircraft engine includes an airfoil coupled to the aircraft engine and has a first portion and a second portion. The first portion is positioned upstream of the second portion with respect to the air flow. A shield is coupled to the engine and positioned between the first portion and the second portion. The shield includes a first side spaced from the first portion and defining a first flow path with the first portion. The shield further includes a second side spaced from the second portion and defining a second flow path with the second portion. At least one sensor is coupled to the aircraft engine and positioned in flow communication with the second flow path. | 04-30-2015 |
20150337732 | GAS TURBINE ENGINE MID TURBINE FRAME BEARING SUPPORT - A gas turbine engine includes a fan and a compressor section that is fluidly connected to the fan. The compressor includes a high pressure compressor and a low pressure compressor. A combustor is fluidly connected to the compressor section. A turbine section is fluidly connected to the combustor. The turbine section includes a high pressure turbine coupled to the high pressure compressor via a first shaft. A low pressure turbine is coupled to the low pressure compressor via a second shaft. A geared architecture interconnects between the second shaft and the fan. The gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). The low pressure turbine has a pressure ratio that is greater than 5, and the geared architecture includes a gear reduction ratio of greater than 2.5:1. | 11-26-2015 |
20160003154 | SUPPORT LINKS WITH LOCKABLE ADJUSTMENT FEATURE - A cam-type apparatus is included in a support link between outer and inner cases of gas turbine engines for centering the cases one to another. The cam-type apparatus is lockable to allow locking an adjusted position of the cam-type apparatus. | 01-07-2016 |
20160201510 | TURBINE ENGINE CASE ATTACHMENT AND A METHOD OF USING THE SAME | 07-14-2016 |