子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | STRUCTURAL ELEMENT OF AN AIRCRAFT PART AND METHOD FOR MANUFACTURING A STRUCTURAL ELEMENT | PCT/EP2016071835 | 2016-09-15 | WO2017046250A3 | 2017-06-15 | TODOROVIC PREDRAG; KUBISCH THOMAS |
| The invention relates to a structural element (101) of an aircraft part, in particular an aircraft engine part, with at least partly a double-curvature shape, comprising a plurality of sets of fibers (11, 12, 13) in textile fabric structure (1), wherein in at least one region (15) of the structural element (101) the number of fibers in one direction is reduced per area in a flattened out state of the textile fabric structure (1). It also relates to a method for manufacturing a structural element (101). | ||||||
| 182 | PLATED POLYMER NOSECONE | PCT/US2014045985 | 2014-07-09 | WO2015017095A3 | 2015-04-09 | ROACH JAMES T; KLING COLIN J; COOK GRANT O III; MCPHAIL JAMES J; BUGAJ SHARI L; O'BRIEN JAMES F; DEHLAVI MAJIDULLAH; SMITH SCOTT A; RADER MATTHEW R; TURNER MATTHEW A; XU JINQUAN |
| Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure. | ||||||
| 183 | NACELLE SCOOP INLET | PCT/US2013055935 | 2013-08-21 | WO2014077922A3 | 2014-07-31 | ZYSMAN STEVEN H |
| A scoop inlet for use in a gas turbine engine nacelle has a scoop inlet, and a tab extending forwardly of the scoop inlet. The scoop communicates with a downstream flowpath. The tab has at least one opening at a location upstream of the scoop inlet. A nacelle and a gas turbine engine are also disclosed. | ||||||
| 184 | UNITIZED ENGINE NACELLE STRUCTURE | PCT/US2011030202 | 2011-03-28 | WO2011123392A2 | 2011-10-06 | THRASH PATRICK J; MILLER DAVID MICHAEL |
| An inner barrel structure for an engine nacelle. The inner barrel structure includes an inner skin, a truss core disposed with respect to the inner skin to define a plurality of cavities, and a plurality of septa respective disposed in the cavity. | ||||||
| 185 | FLUID-COOLING DEVICE FOR A TURBINE ENGINE PROPULSIVE UNIT | PCT/FR2010050996 | 2010-05-21 | WO2010136710A2 | 2010-12-02 | BULIN GUILLAUME; STOLTE RALF-HENNING |
| The invention relates to a fluid cooling device (1) for the propulsive unit of an aircraft of the so-called propfan type, comprising a compressed air intake (11) at the air compressor of the turbine engine (8), an air seam (13) capable of conveying the collected compressed air to a cooler (14), means for conveying the heat of the lubricant to the cooler, said cooler (14) comprising a matrix body (15) provided with a plurality of pipes (20) for a coolant, said pipes (20) extending along a first so-called inner surface (17) up to a second so-called outer surface (16) of the matrix body (15), such that the collected compressed air serving as a coolant can pass through the matrix body (15), the matrix body (15) of the cooler (14) forming a portion of the outer skin (6) of the propulsive unit, as well as a blade assembly (18) extending from the outer surface (16) towards the outside of the propulsive unit, and oriented mainly parallel to the air flow direction (X) when the aircraft is in flight. | ||||||
| 186 | LOW SHOCK STRENGTH INLET | PCT/US2008081055 | 2008-10-24 | WO2009085380A3 | 2010-07-29 | CONNERS TIMOTHY R |
| Embodiments of the invention relate to a supersonic inlet having a cowl lip configured to capture the conic shock and exhibit a zero or substantially zero cowl angle. The inlet may be configured to employ a relaxed isentropic compression surface and an internal bypass. The nacelle bypass may prevent flow distortions, introduced by the capture of the conic shock, from reaching the turbomachinery, thereby allowing the cowl angle to be reduced to zero or substantially zero. Such a cowl angle may reduce the inlet's contribution to the overall sonic boom signature for a supersonic aircraft while allowing for an increase in engine pressure recovery and a subsequent improvement in generated thrust by the engine. | ||||||
| 187 | INTEGRATED INLET DESIGN | PCT/US2009059996 | 2009-10-08 | WO2010059301A3 | 2010-07-22 | HOWARTH GRAHAM; CALDER DAVID P |
| A nacelle assembly (12) and a method for assembling the same is provided. The nacelle assembly (12) includes an inner barrel (38) and an outer structure (40) comprising a highlight (42) and an outer aft section (44), wherein the highlight (42) is defined by a forward end of the outer structure (40), wherein the outer aft section (44) includes a point (45) defined by a maximum diameter (36) of the nacelle assembly (12), wherein the nacelle assembly extends at least between the highlight (42) and the point (45). | ||||||
| 188 | AERODYNAMIC ELEMENT OF AN AIRCRAFT, COMPRISING A SET OF PROTRUDING ELEMENTS | US16239730 | 2019-01-04 | US20190210714A1 | 2019-07-11 | Mathias Farouz-Fouquet |
| An aerodynamic element is provided with at least one set of protruding elements, each of the protruding elements is produced in the form of an elongate and profiled rib projecting from a surface of the aerodynamic element. The protruding elements are arranged at the surface of the aerodynamic element, one beside the other, being oriented substantially parallel to one another so that each of them generates a vortex, the set of vortices thus generated making it possible to reduce crossflow instability. | ||||||
| 189 | AIRCRAFT ENGINE HAVING AT LEAST ONE REVERSE THRUST SYSTEM ACTUATOR ARRANGED IN A GAS EXHAUST CONE | US15985646 | 2018-05-21 | US20180340493A1 | 2018-11-29 | Olivier CAZALS; Guillaume GALLANT |
| To reduce the size of an aircraft engine, an assembly is disclosed including a nacelle section, a gas exhaust cone positioned radially towards the inside in relation to the nacelle section and forming therewith an annular gas exhaust channel, and a reverse thrust system including moveable gas diversion elements for the gas flowing in the annular channel, at least one actuator and a transmission device linking the at least one actuator to the moveable gas diversion elements. Furthermore, the actuator is located inside the gas exhaust cone. | ||||||
| 190 | Aircraft engine nacelle | US15171306 | 2016-06-02 | US10131443B2 | 2018-11-20 | Howoong Namgoong |
| A gas turbine engine nacelle comprising an intake liner. The liner includes a plurality of cells. Each cell includes an open radially inner end in fluid communication with an interior side of the nacelle, and an open radially outer end in fluid communication with an exterior side of the nacelle. Each open end of each cell defines a respective cross sectional area. The intake liner further comprises radially inner and outer facing sheets overlying a respective radially inner and outer open ends of the respective cell. Each facing sheet defines at least one aperture overlying at least one cell, an overlying portion of the respective aperture having a smaller cross sectional area than the respective open end of the respective cell. | ||||||
| 191 | BIRD-STRIKE ENERGY ABSORBING NET | US15488279 | 2017-04-14 | US20180297713A1 | 2018-10-18 | Johann Steven Schrell |
| An energy absorbing arrangement may comprise an inner barrel comprising a centerline axis, an outer barrel, a webbing extending between the outer barrel and the inner barrel and configured to be offset from a nose lip by a distance, the webbing being folded together to form a plurality of folds, the plurality of folds being stitched together via a plurality of stitches, wherein the webbing is configured to absorb energy from an object in response to the object passing through the nose lip and applying a force to the webbing. | ||||||
| 192 | AERODYNAMIC DRAINAGE DEVICE | US15472088 | 2017-03-28 | US20180283217A1 | 2018-10-04 | Robert de Pau, JR.; Paul Brian Philipp; Samuel James Tutko; Fedor Kleshchev; Garrett Daniel Klovdahl |
| Drainage devices intended to prevent the reentry of drained fluids, the devices including a base having a contact surface for mounting over a drainage opening in an aerodynamic surface, a mast portion connected to the base and extending away from the contact surface of the base, and a top portion connected to the end of the mast portion, the top portion having a periphery that is greater than the periphery of the mast portion and including an exit port. The top portion may include a cantilevered fence portion extending upstream relative to the aerodynamic surface, and the drainage devices may be part of a system including a first opening and a second opening in the aerodynamic surface, the second opening upstream from the first opening, where a drainage device is mounted over the first opening and the cantilevered fence portion of the drainage device extends upstream toward the second opening. | ||||||
| 193 | Pressure relief door assembly | US14795392 | 2015-07-09 | US10060287B2 | 2018-08-28 | Angelica Dahmen |
| A pressure relief door (PRD) assembly includes a PRD frame, a PRD coupled to the PRD frame, a latch element configured to remain in a latched condition to maintain the PRD in a closed condition relative to the PRD frame and to assume an unlatched condition to permit the PRD to assume an open condition relative to the PRD frame in accordance with an occurrence of a burst duct event within the PRD frame and a retention element. The retention element is configured to automatically activate responsive to the PRD opening. The retention element includes an end disposable between the PRD and the PRD frame with the retention element automatically activated to provide positive interference to maintain the PRD in the open condition. | ||||||
| 194 | Rainbow Flowpath Low Pressure Turbine Rotor Assembly | US15439122 | 2017-02-22 | US20180238186A1 | 2018-08-23 | Brandon Wayne Miller; Thomas Ory Moniz; Monty Lee Shelton; Joel Francis Kirk; Jeffrey Donald Clements |
| The present disclosure is directed to a gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial centerline extended along the longitudinal direction. The gas turbine engine includes a low pressure (LP) turbine defining an outer flowpath. The outer flowpath defines a first outer flowpath radius at an upstream-most end of the LP turbine, a last outer flowpath radius disposed at a downstream-most end of the LP turbine, a middle outer flowpath radius disposed therebetween along the longitudinal direction. The middle outer flowpath radius is greater than the last outer flowpath radius. | ||||||
| 195 | AIR INTAKE STRUCTURE FOR AN AIRCRAFT NACELLE | US15892618 | 2018-02-09 | US20180230906A1 | 2018-08-16 | Alain PORTE; Jacques LALANE; Franck OUNDJIAN |
| An air intake structure for an aircraft nacelle including an air intake lip with a U-shaped cross section which is open towards the rear, with a rear end, an acoustic panel including an inner wall, wherein the air intake lip has at a rear end a contact surface oriented towards the inside of the air intake lip, in that the contact surface takes the shape of a bevel which points towards the rear and against which the inner wall is placed, in that at the point of the bevel, the inner wall runs on from the air intake lip and in that level with the contact surface, the air intake lip is fixed to the inner wall by first fasteners. The bevelled shape restricts the possibility of dust and water being halted in their progress and blocking up the air intake structure as a result. | ||||||
| 196 | FILAMENT WINDING PROCESS FOR FILLETS | US15429702 | 2017-02-10 | US20180229423A1 | 2018-08-16 | Bryan Thai |
| A fillet for a composite panel may be formed by pulling a prepreg slit tape from a spool and winding the slit tape into a fillet mold around the perimeter of a wheel. The tension, heat, and speed may all be adjusted during the winding process. A guide may guide the slit tape to specific locations in the fillet mold. The fillet may be removed from the wheel and coupled to the composite panel and cured. | ||||||
| 197 | Trailing edge core compartment vent for an aircraft engine | US14870401 | 2015-09-30 | US10040560B2 | 2018-08-07 | Robert H. Willie; Paul R. Tretow; David F. Cerra |
| A turbine engine nozzle can include a primary outer wall extending from an engine core area to an annular wall terminus that surrounds an engine tail cone, to form a core nozzle. The turbine engine nozzle also includes a single engine core cowl extending from the engine core area to an annular cowl terminus to form a core compartment vent nozzle. The core compartment vent nozzle exhausts air from a core compartment in a trailing edge between the single engine core cowl and the primary outer wall. | ||||||
| 198 | FLEXIBLE BAND ELECTRICAL COMPONENT MOUNTS AND METHODS | US15408190 | 2017-01-17 | US20180202313A1 | 2018-07-19 | Chris T. Jasklowski |
| Systems and methods are provided for a flexible band electrical component mount that includes a flexible band configured to receive one or more electrical components. The flexible band may be configured to couple to and/or wrap around at least a portion of an aircraft propulsor. The electrical components may be configured to output data from the aircraft propulsor and/or data related to operation of the aircraft propulsor. Such flexible bands may be configured to receive a plurality of electrical components and may be configured to wrap around the portion of the aircraft propulsor a plurality of times. | ||||||
| 199 | Jet engine with deflector | US14594747 | 2015-01-12 | US10024237B2 | 2018-07-17 | Michael J Kline |
| An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air. | ||||||
| 200 | AIRCRAFT ENGINE HAVING SEAL ASSEMBLY DEFINING AN ELECTRICALLY CONDUCTIVE PATH | US15404571 | 2017-01-12 | US20180195407A1 | 2018-07-12 | Richard KUDRNA; Mélanie BRILLANT |
| The aircraft engine can have an engine casing housing the engine, the engine casing having a shaft aperture; a shaft rotatably mounted to the engine casing, the shaft protruding from the engine casing through the shaft aperture; and a seal assembly extending between the engine casing and the shaft adjacent the shaft aperture, the seal assembly defining an electrically conductive path between the engine casing and the shaft. | ||||||
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