| Entries |
| Document | Title | Date |
|---|
| 20080290191 | Integral composite rocket motor dome/nozzle structure - An integral composite rocket motor nozzle. The novel nozzle includes a first layer of a first reinforcement material, a second layer of a second reinforcement material, and a common matrix material surrounding the first and second reinforcement materials such that the reinforcement materials and matrix material form a single integral composite structure. In an illustrative embodiment, the first reinforcement material includes graphite fibers for providing structural support, and the second reinforcement material includes glass or quartz fibers for providing thermal insulation on a first side of the first layer. The nozzle may also include a third layer of a third reinforcement material for providing thermal insulation on a second side of the first layer. In a preferred embodiment, the first layer is shaped to form an integrated dome and nozzle structure. | 11-27-2008 |
| 20080315012 | Method and System for Regulating Internal Fluid Flow Within an Enclosed or Semi-enclosed Environment - The present invention features a fluid flow regulator that functions to significantly influence fluid flow across the surface of an object, as well as to significantly effect the performance of the object subjected to the fluid. The fluid flow regulator comprises a pressure recovery drop that induces a sudden drop in pressure at an optimal pressure recovery point on said surface, such that a sub-atmospheric barrier is created that serves as a cushion between the molecules in the fluid and the molecules at the object's surface. More specifically, the present invention fluid flow regulator functions to significantly regulate the pressure gradients that exist along the surface of an object subject to fluid flow. Regulation of pressure gradients is accomplished by selectively reducing the pressure drag at various locations along the surface, as well as the pressure drag induced forward and aft of the object, via the pressure recovery drop. Reducing the pressure drag in turn increases pressure recovery or pressure recovery potential, which pressure recovery subsequently lowers the friction drag along the surface. By reducing or lowering friction drag, the potential for fluid separation is decreased, or in other words, attachment potential of the fluid is significantly increased. All of these effects may be appropriately and collectively phrased and referred to as optimization of fluid flow, wherein the fluid flow, its properties and characteristics (e.g., separation, boundary layer), and relationship to the object are each optimized. The present invention is specifically applicable to wings, wing-like structures (e.g. stabilizers and rudders), and diffusers. | 12-25-2008 |
| 20090121046 | APPARATUS AND METHOD FOR REDUCTION OF JET NOISE FROM TURBOFAN ENGINES HAVING SEPARATE BYPASS AND CORE FLAWS - An exhaust flow system for use with a turbofan jet engine that provides separate fan flow and core flow streams that are not mixed. The system includes a fan nozzle and a primary flow nozzle. The primary flow nozzle includes a downstream edge portion that is either beveled with one or more beveled surfaces, or that contains a curving edge surface or a combination of a beveled edge and a curved edge to help direct noise generated by the jet engine upwardly away from a ground surface during take-off and landing procedures. The primary exhaust nozzle can also be orientated with an elongated lip portion thereof formed by the beveled edge surface such that the lip portion is orientated between a top dead center and a bottom dead center position, to thus help direct noise away from a cabin area of a fuselage of a mobile platform during cruise conditions. | 05-14-2009 |
| 20090266911 | SHOWERHEAD FOR CHEMICAL VAPOR DEPOSITION AND CHEMICAL VAPOR DEPOSITION APPARATUS HAVING THE SAME - A showerhead for chemical vapor deposition (CVD) includes a head storing reaction gas flowing thereinto and feeding the stored reaction gas to a reaction chamber, and at least one support member passing through and coupled with the head and the reaction chamber so as to support the head. | 10-29-2009 |
| 20100032497 | Nozzle with guiding elements - A nozzle includes first guiding elements ( | 02-11-2010 |
| 20100044466 | GRID THRUST REVERSER COVER COMPRISING A SEAL SUPPORT AND ASSOCIATED SEAL - This grid thrust reverser cover comprises a seal support and a seal mounted in this support by means of two fastening lugs, this seal being capable of interacting with a diversion edge of this thrust reverser. At least one of the said lugs is turned up and the said support has a section matching that defined by the said lugs. | 02-25-2010 |
| 20100102144 | METHOD FOR ASSEMBLING END TO END TWO PARTS HAVING DIFFERENT THERMAL EXPANSION COEFFICIENTS AND ASSEMBLY THUS OBTAINED - In order to assembly together two parts ( | 04-29-2010 |
| 20100193605 | THERMALLY BALANCED AERO STRUCTURES - An aero structure includes inner and outer skins joined together by a core. The core has a different thermal conductivity than the inner skin to balance heat conduction therethrough. | 08-05-2010 |
| 20110174899 | NACELLE WITH A VARIABLE NOZZLE SECTION - The invention relates to a nacelle that comprises a fixed structure ( | 07-21-2011 |
| 20120160933 | STRUCTURING ASSEMBLY FOR AN EXHAUST NOZZLE - The invention relates to a structuring assembly ( | 06-28-2012 |
| 20120193447 | Lawn Sprinkler - A lawn sprinkler providing water distribution over an irregular or unique shaped water receiving area. The apparatus includes a water impeller, a first water regulator, a second water regulator, and a bypass channel. The sprinkler regulates the delivery of water according to the shape of the area to be irrigated, so that water is not wasted on adjacent areas which do not require irrigation. | 08-02-2012 |
| 20120228403 | ASSEMBLY FOR AN AIRCRAFT TURBOJET ENGINE COMPRISING A THRUST REVERSAL COWL - The invention relates to an assembly for a turbojet engine which includes a pylon ( | 09-13-2012 |
| 20120286066 | VARIABLE GEOMETRY TURBOMACHINE - Variable geometry turbomachine with a bearing housing, an adjacent turbine housing, a turbine wheel rotating in the turbine housing about a turbine axis; an inlet passage upstream of the turbine wheel between inlet surfaces of first and second wall members, one wall member moveable along the turbine axis to vary the inlet passage size; vanes across the inlet passage connected to a first wall member; an array of vane slots defined by the second wall member to receive the vanes for relative movement between the wall members; the second wall member comprising a shroud defining vane slots; the second wall member supported by a support member retained by a mounting feature; the mounting feature being one of the bearing housings, the turbine housing, or the actuation element; and the shroud is fixed to the support member so axial movement of the shroud relative to the support member is substantially prevented. | 11-15-2012 |
| 20130001321 | HYBRID EXHAUST COMPONENT - An exhaust includes a wall that has a first composite material having a first coefficient of thermal expansion and a second composite material having a second coefficient of the thermal expansion that is less than the first coefficient of thermal expansion. | 01-03-2013 |
| 20130020408 | Cable-Actuated Variable Area Fan Nozzle with Elastomeric Seals - An apparatus installed on an aircraft, comprising: a sleeve or duct having a trailing lip area; a plurality of petals arranged side by side with gaps therebetween, one end of each petal being attached or pivotably coupled to the lip area; and a plurality of elastomeric seals configured and disposed to close the gaps between adjacent petals. Each elastomeric seal comprises a first portion that moves with a portion of a first petal that is in contact therewith, a second portion that moves with a portion of a second petal that is in contact there, and a third portion which is stretched as the first and second petals move further apart from each other. Petal deflection is actuated by a system comprising a flexible member, a motor, a shaft driven by the motor, and an arm projecting from the shaft. One end of the flexible member is attached to the arm, the flexible member being movable to deflect the petals inward in response to a shaft rotation. | 01-24-2013 |
| 20130032643 | COMBUSTOR LEAF SEAL ARRANGEMENT - A substantially wedge-shaped sector nozzle includes a nozzle body having inner and outer arcuate segments connected by diverging radial side plates and a nozzle plate at an aft end of the nozzle body formed with an array of fuel orifices. One of the diverging radial side plates supports a radially-oriented leaf seal assembly adapted to seal against a flat plate of an adjacent similarly-shaped sector nozzle. | 02-07-2013 |
| 20130087635 | AIR INLET DUCT FOR A TURBOJET NACELLE - An air inlet duct and method for producing such for a turbojet nacelle, the air inlet duct including an upstream annular lip and a downstream outer annular structure. The upstream annular lip and the downstream outer annular structure are formed as a one-piece part made from composite material and the upstream lip is covered with a metal layer formed by electro-deposition or plastic forming. A turbofan engine can include such an air inlet duct. | 04-11-2013 |
| 20130175360 | HIGH-VOLUME, PART-CIRCLE SPRINKLER HEAD - A high-volume sprinkler head includes a barrel with a nozzle; a fixed portion and a relatively movable portion adapted for pivoting movement relative to the fixed portion. The barrel is mounted on an upper support base rotatable on a lower stationary base in opposite directions through an arc about a vertical axis. A fluid-operated actuator pivots the relatively movable portion of the barrel relative to the fixed portion of the barrel between first and second reaction angles that cause the barrel and the annular upper support base to rotate in opposite directions, about the substantially vertical axis, respectively, when a stream is emitted from the nozzle. A three-way valve in combination with adjustable stops on the stationary base may be used to pilot the actuator, with the adjustable stops determining the arcuate extent of the rotational movement of the sprinkler head. | 07-11-2013 |
| 20130206865 | METHOD FOR DEFINING THE SHAPE OF A TURBOMACHINE CONVERGENT-DIVERGENT NOZZLE, AND CORRESPONDING CONVERGENT-DIVERGENT NOZZLE - According to the invention, the method for defining the shape of a convergent-divergent nozzle of longitudinal axis L-L comprising a convergent part connected, at a throat, to a divergent part the downstream free end of which comprises scallops delimiting noise-reducing chevrons distributed in the circumferential direction, | 08-15-2013 |
| 20130233942 | ENGINE APPARATUS AND METHOD FOR REDUCING A SIDE LOAD ON A FLYING OBJECT - An engine apparatus is provided for a flying object, the engine apparatus including a combustion chamber having a throat region and a nozzle region, the nozzle region having a nozzle wall, wherein the nozzle region expands from the throat region towards an exit end relative to a combustion chamber axis, wherein the nozzle region has associated therewith a skirt having a skirt wall, the skirt being positioned downstream relative to the exit end and surrounding the exit end of the nozzle region, and wherein the skirt wall is at an acute angle away from the combustion chamber axis with respect to the nozzle wall, at least at the exit end of the nozzle region. | 09-12-2013 |
| 20140001284 | Panel for the acoustic treatment comprising hot air ducts and at least one stabilization chamber | 01-02-2014 |
| 20140001285 | NOZZLE, A NOZZLE HANGER, AND A CERAMIC TO METAL ATTACHMENT SYSTEM | 01-02-2014 |
| 20140061331 | DISCHARGE SYSTEM OF A SEPARATED TWIN-FLOW TURBOJET FOR AN AIRCRAFT, CORRESPONDING TURBOJET AND ASSOCIATED DESIGN METHOD - A discharge system of a separated twin-flow turbojet for an aircraft, supported by a suspension mast, is disclosed. The system includes a main nozzle delimited by an annular cowl with a slot of annular shape defining upstream and downstream portions of the cowl and which is traversed by the suspension mast. The downstream portion of the cowl of the main nozzle includes a first part extending downstream from the upstream portion of the cowl to a trailing edge of the main nozzle, on either side of the suspension mast along two predefined angular sectors; and a second part formed from an internal contour of the slot and having a trailing edge with a diameter smaller than that of the trailing edge associated with the first part of the downstream portion of the cowl. Connecting walls laterally connect the first and second parts of the downstream portion. | 03-06-2014 |
| 20140319242 | NOZZLE, STRUCTURE ELEMENT AND METHOD OF PRODUCING A NOZZLE - A nozzle, in particular an outlet nozzle of an aircraft jet engine, is formed with at least one nozzle wall. A turbulence-generating and/or vortex-generating structure is arranged on an inner face of the nozzle wall and projects radially inwardly from the nozzle wall. Alternatively, or in addition, a turbulence-generating and/or vortex-generating structure is arranged on an outer face of the nozzle wall and projects radially outwardly from the outer face. There is also described a structural element and a method of producing a nozzle. | 10-30-2014 |
| 20140332604 | Device for Fastening a Hollow Part - A fastener device for fastening a hollow part is made up of two mutually facing walls to at least one structural part. The device comprises a one-piece body of metal material presenting two main faces extending longitudinally between first and second ends of the body. Each main face includes a bearing portion in the vicinity of the first end of the body. The bearing portion is for being pressed against an inside surface of a respective one of the two walls of the hollow part, with each bearing portion including a fastener orifice for receiving a fastener member. The bearing portions are separated from each other by a slot extending from the first end of the body and over a determined depth within the body. | 11-13-2014 |
| 20150028129 | BICONICAL EXHAUST CONE FOR A CIVIL AVIATION JET ENGINE - A biconical exhaust cone for a civil aviation jet engine, this cone delimiting, on its outside, an annular exhaust stream of combustion gases and comprising an upstream frustoconical portion extending outward from upstream to downstream and a downstream frustoconical portion extending inward from upstream to downstream, wherein the downstream frustoconical portion comprises a segment which defines an outer annular surface of which one tangent, at any point along the longitudinal axis of the cone, is inclined by an angle greater than 40° and less than 90° with respect to this longitudinal axis. | 01-29-2015 |
| 20150083822 | INTEGRATING AFTER-BODY PARTS OF AN AEROENGINE - The invention relates to an aeroengine after-body assembly comprising an exhaust casing made of metal having a plurality of arms extending radially between an inner shroud and an outer shroud. The assembly comprises at least one axisymmetric part made of composite material extending between an upstream end fastened to said exhaust casing and a downstream end that is free. In accordance with the invention, the axisymmetric part has an annular portion at its upstream end, which annular portion includes a plurality of slots defining between them a plurality of resilient fastener tabs. Each slot co-operates with an arm of the exhaust casing, which further includes fastener parts attached to the resilient fastening tabs. | 03-26-2015 |
| 20150354501 | Non-Axisymmetric Exit Guide Vane Design - An exit nozzle section for an engine has an outer wall and an inner wall, and a plurality of exit guide vanes extending between the outer wall and the inner wall. Different ones of the exit guide vanes having different cambers in different regions of the exit nozzle section. | 12-10-2015 |
| 20150369172 | SERPENTINE BAFFLE FOR A GAS TURBINE ENGINE EXHAUST DUCT - A serpentine baffle for a liner assembly of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a wall that defines a serpentine shape and a multiple of tabs which extend from the wall. In a further embodiment of the foregoing embodiment, the wall and the multiple of tabs are formed from a single cross-shaped piece. In a further embodiment of any of the foregoing embodiments, wherein at least one of the multiple of tabs is located adjacent to a distal end of the wall. In a further embodiment of any of the foregoing embodiments, the multiple of tabs are perpendicular to the wall. | 12-24-2015 |
| 20160131083 | EXHAUST NOZZLE CENTER BODY ATTACHMENT - A ceramic turbine engine exhaust component, such as a ceramic matrix composite (“CMC”) exhaust center body may be positioned around a metallic attachment ring. The attachment ring may have a greater coefficient of thermal expansion than the CMC center body. A plurality of bolts radially-spaced around the circumference of the attachment ring may be inserted through apertures in the center body with a sliding fit, and may be coupled to the attachment ring. The bolts may slide within the apertures, allowing the attachment ring to thermally expand without applying extra loads on the exhaust center body due to the expansion. | 05-12-2016 |
| 20160138623 | METHOD FOR CONTROLLING A LIFTING JACK FOR AN AIRCRAFT ENGINE NACELLE, A JACK-TYPE LIFTING SYSTEM IMPLEMENTING THE METHOD AND THE THUS EQUIPPED NACELLE - The jack-type lifting system includes a valve for modifying a maximum force value of a lifting jack activated by a protrusion for determining a determined portion such as the beginning of the extension stroke of the lifting jack. Thanks to the modification of the maximum force value, a pressure source thus applies the full force of the lifting jack after a start-up stroke so as to protect a lock of a reverser cowl which has been forgotten during maintenance. | 05-19-2016 |
| 20160160797 | NOZZLE OF A TURBOMACHINE PROVIDED WITH CHEVRONS WITH A NON-AXISYMMETRIC INNER FACE - A nozzle of a turbomachine is provided with chevrons with a non-axisymmetric inner face. A cover for the nozzle of longitudinal axis L-L includes an internal wall having a section with a predetermined abscissa on the L-L axis defining, on the wall, a neck line. The cover has, downstream from the abscissa, indentations in the trailing edge of the cover delimiting chevrons distributed in the circumferential direction, in which, on the cover, from the abscissa the internal wall moves away radially towards the outside of the upstream tangent, to the top of an indentation, the outer wall of the cover moves towards the upstream tangent to the top of an indentation, and the internal wall moves away radially towards the inside of the upstream tangent, to the tip of a chevron. | 06-09-2016 |
| 20160169155 | DEVICE FOR CONNECTING TWO SEGMENTS OF A PROPELLING NOZZLE | 06-16-2016 |
| 20160175988 | METHOD TO IMMOBILIZE AN ENTRAPPED CONTAMINANT WITHIN A HONEYCOMB STRUCTURE | 06-23-2016 |
| 20160177872 | EXHAUST DUCT | 06-23-2016 |
