Class / Patent application number | Description | Number of patent applications / Date published |
137150100 | HIGHSPEED FLUID INTAKE MEANS (E.G., JET ENGINE INTAKE) | 60 |
20080271787 | Isentropic compression inlet for supersonic aircraft - Embodiments of the invention relate to a supersonic inlet employing relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Using supersonic inlets in accordance with the invention also demonstrated reductions in peak sonic boom overpressure while maintaining performance. | 11-06-2008 |
20090107557 | Low shock strength inlet - 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. | 04-30-2009 |
20090165864 | Supersonic inlet - The present invention includes a supersonic inlet having a converging portion and a diverging portion operable to diffuse engine airflow from supersonic speeds to subsonic speeds. A physical throat includes a fixed flow area at a fixed location is between the converging and diverging portions of the inlet. A fluidic injector injects pressurized fluid into the inlet to form a variable effective throat within the inlet and improve the off design efficiency of the inlet. | 07-02-2009 |
20090255589 | TURBINE ENGINE FOR AIRCRAFT - According to the invention, the internal wall of the air intake ( | 10-15-2009 |
20100051112 | INTAKE CONE FOR A GAS-TURBINE ENGINE - An intake cone for a gas-turbine engine has an essentially conical body | 03-04-2010 |
20100258199 | INTAKE CONE IN A FIBER COMPOUND MATERIAL FOR A GAS-TURBINE ENGINE - The intake cone for a gas-turbine engine is wound in one piece from fiber compound material with fiber layers crossing one another. It is provided with a fiber compound belt, wound in the circumferential direction of the intake cone, in the connecting area with a mounting flange, which is of segmented design and thus features reduced circumferential stiffness, of a metallic retaining ring attached to a fan rotor disk. The intake cone is easily manufacturable with almost constant wall thickness and in high quality, can reliably be subjected to non-destructive testing and, in combination with the mounting flange, which is flexible in the radial direction, ensures safe connection of the two components despite the different thermal and elastic behavior of the respective materials. | 10-14-2010 |
20100276007 | CAMBERED AERO-ENGINE INLET - An inlet of a nacelle for channeling inlet airflow to a fan of a gas turbine engine includes a forward lip and an inner surface. The forward lip extends around a centerline axis of the engine and is adapted to accommodate a flow angle of incoming airflow. The inner surface extends from the forward lip along the centerline axis of the engine to adjacent the fan. The inner surface has a first profile above the centerline axis of the engine and a second profile below the centerline axis of the engine. The first profile and the second profile are adapted to define an inlet centerline axis that extends below the centerline axis of the engine at a face of the fan. | 11-04-2010 |
20110197973 | INLET SECTION OF AN AIRCRAFT ENGINE NACELLE - A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange includes an acoustic inner barrel having a forward edge and an aft edge, an outer shell having a nose lip portion with a trailing inner edge, and an outer barrel portion having an aft portion. The nacelle inlet also includes an aft attachment flange configured to attach the inlet to the forward flange of the engine fan case, and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft attachment flange. The forward edge of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft attachment flange. | 08-18-2011 |
20110214747 | NACELLE WITH AN ADAPTABLE OUTLET SECTION - The present invention relates to a jet engine nacelle ( | 09-08-2011 |
20110220217 | AIR INLET OF AN AEROENGINE HAVING UNDUCTED PUSHER PROPELLERS - An air intake for an aeroplane engine of type with unducted propellers, which intake can be connected by a pylon to a fuselage of an aeroplane, a local length of the air intake, measured parallel to the axis of the engine between a point on a leading edge of the air intake and a transverse plane situated at an inlet impeller of the engine compressor, is longer in a region of the air intake connected to the pylon and shorter in a region of the air intake opposite the pylon. | 09-15-2011 |
20110220218 | TURBOJET ENGINE NACELLE - The invention relates to a nacelle ( | 09-15-2011 |
20110284095 | TURBOJET ENGINE NACELLE - The invention relates to a turbojet engine nacelle ( | 11-24-2011 |
20110290333 | METHOD FOR MANUFACTURING A STRUCTURE WITH CELLULAR CORES FOR A TURBOJET NACELLE - The invention relates to a method for manufacturing a structure with cellular cores ( | 12-01-2011 |
20110303302 | NACELLE COMPRISING AN AIR ENTRANCE IN A CAP - An aircraft nacelle includes an outside wall ( | 12-15-2011 |
20110308634 | TURBOJET NACELLE HAVING A REMOVABLE AIR INTAKE STRUCTURE - A turbojet engine nacelle, including an air intake structure for directing an airflow towards a fan of the turbojet engine, a middle structure attached to the air intake structure for surrounding the fan of the turbojet engine, the air intake structure including an inner panel attached to the middle structure and defining a fixed structure with the middle structure, and an outer panel including an air intake lip at the end thereof opposite the middle structure, the outer panel being longitudinally translatably movable relative to the inner panel. The nacelle further includes at least one rod having one end attached onto a flange of the air intake lip and a mechanism rigidly connected to the middle structure for securing and locking the other end of each rod by applying a traction force thereon. | 12-22-2011 |
20120018005 | COUPLING DEVICE FOR CONNECTING THE TWO HALF-SHELLS OF AN AIRCRAFT ENGINE NACELLE, AND NACELLE EQUIPPED WITH SUCH A DEVICE - Coupling device for connecting the two half-shells ( | 01-26-2012 |
20120031501 | Aviation engine inlet with tangential blowing for buzz saw noise control - The present patent disclosure presents a class of patent aviation engine inlets using tangential blowing airflow grazing over buzz saw lining surface to prevent buzz saw noise from propagation out of the engine inlet, to alleviate airport noise problem and to reduce airplane cabin noise level for passenger comfort. The robustness of the concept of tangential blowing in the improvement of the attenuation of buzz saw tones by buss saw lining is that, practically, the significant buzz saw tones are eliminated. | 02-09-2012 |
20120042958 | Jet engine intake guard - A jet engine air intake guard system wherein direct axial air flow into an engine during takeoff and landing may be temporarily closed off while air intake is provided laterally through screened air intake ports located on a cylindrical housing that extends forward of the conventional air intake cowling openings. | 02-23-2012 |
20120060938 | AIRCRAFT NACELLE COMPRISING A REINFORCED OUTER WALL - An aircraft nacelle includes a wall that delimits an inside pipe ( | 03-15-2012 |
20120090693 | ACOUSTIC PROCESSING PANEL, MORE PARTICULARLY ADAPTED FOR AN AIR INTAKE IN AN AIRCRAFT NACELLE - An acoustic treatment panel that is connected to an air intake of an aircraft nacelle, includes at least one acoustically resistive structure ( | 04-19-2012 |
20120090694 | AIRCRAFT NACELLE INCLUDING A REAR FRAME INCLINED TO THE REAR - An aircraft nacelle includes a lip whose surface contacts with the aerodynamic streams extends inside the nacelle by an inside wall that delimits a layer that empties at a power plant and outside of the nacelle by an outside wall, a first front frame connects the inside and outside walls, delimiting an annular pipe with the lip, and a rear frame connects the inside and outside walls at a junction zone between the inside pipe and power plant pipe, for a given cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle, a point A at the intersection between the rear frame and the inside wall, and a point B at the intersection between the rear frame and the outside wall, with B being offset toward the rear of the nacelle relative to A over more than 50% of the rear frame's periphery. | 04-19-2012 |
20120090695 | AIRCRAFT NACELLE INCLUDING AT LEAST ONE RADIAL PARTITION BETWEEN TWO CONDUCTS - An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels ( | 04-19-2012 |
20120097260 | AIRCRAFT COVER INCLUDING MEANS FOR LIMITING THE SCOOP PHENOMENA OF ELECTROMAGNETIC TYPE - An aircraft nacelle includes at its outside wall a cowl that can move relative to the rest of the nacelle so as to block or unblock an opening. The cowl includes an articulation relative to the rest of the nacelle and locking/unlocking elements distant from the upstream edge of the cowl that includes elements for limiting the appearance of scooping phenomena. The limiting elements include at least one electromagnetic torque, having one element integral with the rest of the nacelle and the other element integral with the cowl, with at least one of these two elements emitting a magnetic field that generates a force of attraction on the other element, and the surfaces of the two elements of the electromagnetic torque that are flattened against one another are arranged in planes having at least one component in the radial direction. | 04-26-2012 |
20120097261 | AIRCRAFT COVER INCLUDING MEANS FOR LIMITING THE SCOOP PHENOMENA OF PNEUMATIC TYPE - An aircraft nacelle includes at its outside wall a cowl moveable relative to the nacelle so as to block or unblock an opening. The cowl includes an articulation and locking/unlocking elements distant from the upstream edge of the cowl that include elements for limiting the appearance of scooping phenomena. The limiting elements include at least one lock integral with the rest of the nacelle or respectively the cowl that can occupy a locked state in which part of the lock interferes with the cowl or respectively the rest of the nacelle and prevents a deformation that includes a radial component of the cowl, and another free state in which the part no longer interferes with the cowl or respectively the rest of the nacelle and allows the opening movement of the cowl, with the switch from one state to the next being generated by a gas pressure variation. | 04-26-2012 |
20120118398 | TURBOMACHINE NOZZLE COWL HAVING PATTERNS WITH LATERAL FINS FOR REDUCING JET NOISE - An annular cowl for a turbomachine nozzle, the cowl including a plurality of patterns arranged to extend a trailing edge of the cowl and circumferentially spaced apart from one another. Each pattern has an outline of substantially polygonal shape with a base formed by a portion of the trailing edge of the cowl and at least one vertex that is spaced downstream from the base and that is connected thereto by lateral edges, and in each of its lateral edges, each pattern includes at least one fin, each fin being inclined radially relative to the pattern in a plane that is inclined at an angle lying in the range 0° to 45° relative to a radial direction. | 05-17-2012 |
20120118400 | LEADING EDGE STRUCTURE, IN PARTICULAR FOR THE AIR INTAKE OF THE NACELLE OF AN AIRCRAFT ENGINE - The invention relates to a structure of a leading edge ( | 05-17-2012 |
20120145254 | AIR INLET FOR AIRCRAFT PROPULSION UNIT HAVING A STRUCTURE RESISTANT TO EXCESS PRESSURE AND A PROCESS FOR REPAIRING AN AIR INLET OF AN AIRCRAFT PROPULSION UNIT - An air inlet for nacelle of an aircraft propulsion unit comprising an inner envelope provided with a plurality of orifices for passage of fluid passing through said envelope, and a lip connected to the upstream edge of said inner envelope, and having a portion devoid of orifices for passage of fluid with an axial span of between 20% and 90% of the span of said inner envelope, and a circumferential span α of between 60° and 150° about a longitudinal axis of said air inlet. | 06-14-2012 |
20120199212 | ISENTROPIC COMPRESSION INLET FOR SUPERSONIC AIRCRAFT - A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance. | 08-09-2012 |
20120204967 | Device For Ventilating A Compartment - A ventilation device for a compartment, preferably a compartment of an aircraft engine, the device including an air intake adapted to capture a flow of air outside the compartment, an air diffuser adapted to guide the air flow into the compartment, and an air distributor adapted to distribute the air flow within the compartment, the air distributor in this device being separated from the air diffuser, and being placed inside the compartment at a distance from the air diffuser | 08-16-2012 |
20120247571 | JET ENGINE NACELLE REAR ASSEMBLY - The present invention relates to a nacelle rear assembly ( | 10-04-2012 |
20130037122 | PRESSURE INFLUENCING ASSEMBLY FOR AN AIRCRAFT AUXILIARY SYSTEM - An exemplary pressure influencing assembly for an aircraft auxiliary system an inlet opening to an aircraft auxiliary system and an exhaust opening from the aircraft auxiliary system. Both the inlet opening and the exhaust opening face at least partially radially away from an axis. At least some of the inlet opening is circumferentially aligned with at least some of the exhaust opening relative to the axis. | 02-14-2013 |
20130042922 | AIR INLET ARRANGEMENT AND METHOD OF MAKING THE SAME - An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate. | 02-21-2013 |
20130081706 | AIR INTAKE WITH DOUBLE INLET DOOR - An APU air intake (AI) is disclosed having a foldable intake door ( | 04-04-2013 |
20130098471 | Aircraft nacelle comprising a hot air supply device for a panel combining acoustic and frost treatments - The object of the invention is an aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip annular channel within which hot air circulates, and a panel for acoustic treatment comprising, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure and one reflective layer as well as ducts for channeling hot air, at least one conduit with opening which opens into annular channel being provided for carrying hot air up to the panel for acoustic treatment, wherein opening is used for channeling hot air in direction which forms an angle β of less than 60° with hot air flow direction into annular channel. | 04-25-2013 |
20130118599 | NACELLE - A nacelle is configured to be coupled to an underside of a wing so as to form a clearance space therebetween. The nacelle includes at least a first cowling which at least partially defines an inlet of the nacelle and which at least partially defines an outlet of the nacelle. The first cowling can include a unitary portion that extends continuously from the inlet to the outlet. The first cowling can also include a flattened surface. | 05-16-2013 |
20130199621 | AIRCRAFT, PROPULSION SYSTEM, AND INLET WITH SUPERSONIC COMPRESSION - Embodiments of an inlet, aircraft, and propulsion system includes an inlet spike with a compression surface configured to decelerate air flow from supersonic speed to subsonic speed before the air flow enters a cowling throat and diffuser section of the propulsion system. | 08-08-2013 |
20130199624 | GAS TURBINE ENGINE NACELLE - A method of designing a nacelle for a gas turbine engine includes defining an initial geometry for the nacelle, pivoting, at each of one or more positions on a highlight and in a plane of a respective longitudinal section, a front portion of a section of an intake lip lying in the respective longitudinal section about the highlight, and obtaining an altered geometry for the nacelle by adjusting surfaces of the intake neighbouring the pivoted front portion to smoothly blend the surfaces of the pivoted front portion to unadjusted surfaces of the intake further removed from the pivoted front portion. | 08-08-2013 |
20130220435 | NACELLE - A nacelle includes at least a first cowling which at least partially defines an inlet of the nacelle and which at least partially defines an outlet of the nacelle. The first cowling can include a unitary portion that extends continuously from the inlet to the outlet. The nacelle also includes a second cowling that at least partially defines the inlet and which translates relative to the first cowling. The nacelle can include a third cowling that at least partially defines the outlet and translates relative to the first cowling. | 08-29-2013 |
20130284279 | AIR INTAKE SYSTEM FOR AN AIR VEHICLE - A missile comprises a propulsion system, a passageway for delivering air to the propulsion system and a ducting element associated with the passageway. The ducting element has a ducting surface for ducting air into the passageway, and the ducting element is rotatable, about an axis that is aligned, or more preferably co-axial, with the axis of the passageway, from a stowed position in which the ducting surface is received in the passageway, to a deployed position in which the ducting surface protrudes from the passageway to duct air into the passageway. | 10-31-2013 |
20140026974 | PROCESS OF MANUFACTURING A TURBOJET ENGINE NACELLE PART - A method for manufacturing a nacelle air intake lip including a plurality of components includes the following steps. The first step is positioning, inside a mold, two components within a set of fibrous layers encompassing all or part of the components so that a preform is formed. Next step is performing impregnation of the obtained preform to obtain molding of the nacelle air intake lip. | 01-30-2014 |
20140083518 | STRUCTURAL ELEMENT OF AN AIR VEHICLE AIR INTAKE COMPOSED OF AN ARRAY OF PASSAGES WITH A HEXAGONAL CROSS SECTION - An air vehicle powered by a gas turbine engine, particularly, but not exclusively, an air vehicle having a blended wing body includes a gas turbine engine disposed in the body of the vehicle including an inlet face. An inlet channel having a convoluted geometry is configured such that air flow incident on the inlet face during operation is disordered. A structural element associated with the inlet channel and locate upstream of the inlet face is provided. The element is configured to modulate air flow, at least partially, to improve flow ordering in the incident air. | 03-27-2014 |
20140130889 | AIR INLET STRUCTURE FOR TURBOJET ENGINE NACELLE - The present disclosure relates to an air inlet structure for a turbojet engine nacelle. The air inlet structure has a stationary internal wall to be attached to one element of a mid-section of the nacelle, and a longitudinal external wall extended by an air inlet lip connected to the stationary internal wall. In particular, one portion forming the air inlet lip is provided with depressurizing openings for a part of the air inlet lip. | 05-15-2014 |
20140144519 | AIRCRAFT NACELLE COMPRISING A REINFORCED CONNECTION BETWEEN AN AIR INTAKE AND A POWERPLANT - An aircraft nacelle comprising a first duct secured to an air intake and a second duct secured to a powerplant, the first duct comprising an exterior surface and an end portion connected to the second duct. The nacelle includes a hollow section piece in contact with the exterior surface of the first duct which extends over at least part of the circumference of that end portion of the first duct that is connected to the second duct. | 05-29-2014 |
20140182697 | ADJUSTABLE SUPERSONIC AIR INLET - The invention relates to aeronautical engineering and, more specifically, to air intakes for supersonic aircraft propulsion systems. The technical result to be achieved by the invention consists in ensuring stable operation of the engine in all flight regimes up to the maximum Mach number of M=3.0 by adjusting the apex angle of stages of one of swept wedges and minimum area of the flow passage of the air intake. An adjustable supersonic air intake comprises an entrance in the form of a flow deceleration system—a supersonic diffuser ( | 07-03-2014 |
20140283921 | AIRPLANE - An airplane having at least one turbojet and means for taking at least a portion of the boundary layer ( | 09-25-2014 |
20140352795 | Jet Engine With Deflector - 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. | 12-04-2014 |
20140352797 | AIRCRAFT JET ENGINE - In various embodiments, a jet engine, as described herein, may include a fan case, a fan cowl, and an air inlet. Further, in various embodiments, at least one of the fan case and the fan cowl may be directly coupled to the air inlet. In addition, in various embodiments, the fan case, the fan cowl, and the air inlet may be manufactured as a single, unitary, engine part. | 12-04-2014 |
20140373927 | LOW SHOCK STRENGTH PROPULSION SYSTEM - A supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine is disclosed herein. A set of aerodynamic vanes may be used to shape a supersonic airflow within a bypass around an engine. The vanes may be capable of compressing the supersonic airflow into a subsonic airflow, direct the subsonic airflow around the engine, and then expand the subsonic airflow into a supersonic exhaust. The vanes may shape the airflow by reducing sonic boom strength, cowl drag, and airframe interference drag. | 12-25-2014 |
20150007895 | Splitter Nose with a Sheet That Forms a Surface to Guide the Flow and Acts as a De-Icing Duct - The present application relates to a splitter nose of an axial turbomachine configured to separate an annular flow into the turbomachine into a primary flow and a secondary flow, and including: a generally circular leading edge, an annular wall extending from the leading edge and bounding the secondary flow, and at least one duct for a de-icing fluid for the splitter nose extending substantially axially along the wall and opening out into the primary flow. The external surface of the wall is formed by a sheet bounding the de-icing duct. | 01-08-2015 |
20150007896 | AIR INLET STRUCTURE FOR A TURBOJET ENGINE NACELLE OF LAMINAR TYPE - An air intake structure for a turbojet engine nacelle includes an inner panel to be attached to a fan casing, and an external panel capable of a translational movement in a longitudinal direction of the nacelle. The external panel incorporates a portion of an air inlet lip able to provide a junction between the inner panel and the external panel, and each of the air inlet lip portion and the inner panel is equipped, at least in the region of a joining end, with an acoustic attenuation structure. In particular, at least one of the joining ends is equipped with a radial buffer able to come into contact with a corresponding joining flange exhibited by the other joining end when the external panel is in a closed position. | 01-08-2015 |
20150096627 | ENGINE MOUNTED INLET PLENUM FOR A ROTORCRAFT - One example of an engine mounted inlet plenum for a rotorcraft includes an inlet flange, an outlet flange and a plenum duct that connects the inlet flange and the outlet flange. The inlet flange, which defines an inlet to flow air into a barrier filtration system, is configured to be substantially aligned with a closed cowl door assembly of the rotorcraft. In some implementations, the plenum duct is configured to extend to an outer mold line (OML) of the rotorcraft such that the inlet flange is aligned with the OML. The outlet flange defines an outlet to flow air filtered by the barrier filtration system into an engine of the rotorcraft. The plenum duct allows air to flow from the inlet to the outlet. | 04-09-2015 |
20150114481 | Inlet System Having Dual Inlets - A method and apparatus for supplying air to a precooler. Air flow is created through a fan duct in an engine system. A first portion of the air flow is directed into a first inlet of an inlet system to feed a first half of the precooler. A second portion of the air flow is directed through the fan duct into a second inlet of the inlet system to feed a second half of the precooler. | 04-30-2015 |
20150129045 | NACELLE INLET CONFIGURATION - A nacelle inlet is provided for a turbo-fan engine for an aircraft. The nacelle inlet includes a lip skin having first and second pad-ups, an inner barrel including a forward flange and a bulkhead. The bulkhead, the lip skin and the inner barrel are attached together at mating surfaces. The bulkhead and the lip skin are attached together at mating surfaces. Each mating surface defines a surface geometry which approximates a developable surface having parallel ruling lines. The developable surfaces are formed by machining. | 05-14-2015 |
20150144201 | ENGINE INLET DUCT INSTALLATION - A method of securing two components to each other includes locating a mounting strip at a first mounting flange of a first component. The mounting strip is slidably affixed to the first component and includes a plurality of strip openings and a tightening ramp located at each strip opening of the plurality of strip openings. A second component is located such that a second mounting flange of the second component abuts the first mounting flange. A plurality of fasteners are located at the second mounting flange. A fastener of the plurality of fasteners extends through each strip opening of the plurality of strip openings. The mounting strip is slid in a direction to increase tension on the plurality of fasteners via an increasing height of the tightening ramp under a fastener head of the fastener, thereby securing the first mounting flange to the second mounting flange. | 05-28-2015 |
20150300254 | PROPULSION ENGINE - An air intake for an open rotor engine including a propulsive blade array having a plurality of blades each having a gas washed surface extending radially outwardly relative to an axis or rotation from a root end to a tip. Intake has first and second circumferential walls extending about axis of rotation at a location downstream of propulsive blade array. First and second walls are spaced in a radial direction to define an annular passage with opening having a height dimension extending a portion of the way along propulsive blade array span. Intake further includes an annular lip arranged about axis of rotation at a radial distance such that lip bifurcates the annular passage at a height which separates a boundary layer flow portion of intake flow from a remainder of intake flow. Lip may define a collection scroll for foreign object debris and cooling air for the engine. | 10-22-2015 |
20160039400 | MULTI-PASSAGEWAY ASPIRATOR - In one or more embodiments, an aspirator of a vehicle includes a body portion with an inlet and an outlet, and an arm portion connected to the body portion at a location between the inlet and the outlet, wherein a cross-section of the inlet includes an inner wall and an outer wall enclosing the inner wall. The outer wall may be spaced apart from the inner wall along an outer perimeter of the inner wall. The inner and outer walls may be concentric to each other. | 02-11-2016 |
20160076448 | AIR INLET ARRANGEMENT AND METHOD OF MAKING THE SAME - An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate. | 03-17-2016 |
137150200 | With condition responsive control means | 3 |
20110240137 | OVERPRESSURE HATCH INTENDED TO BE MOUNTED ON A WALL OF A TURBOJET ENGINE NACELLE - The invention relates to an overpressure hatch ( | 10-06-2011 |
20110259435 | JET ENGINE NACELLE EQUIPPED WITH A SYSTEM FOR MECHANICALLY INHIBITING A THRUST REVERSER - The present invention relates to a jet engine nacelle comprising a forward air inlet section, a mid-section intended to surround a jet engine fan, and an aft section equipped with at least one thrust reversal system comprising, on the one hand, means for deflecting at least part of an air flow of the jet engine and, on the other hand, at least one cowl ( | 10-27-2011 |
20160376987 | SUPERSONIC CARET INLET SYSTEM LEADING EDGE SLAT FOR IMPROVED INLET PERFORMANCE AT OFF-DESIGN FLIGHT CONDITIONS - An engine inlet for efficient operation at both design Mach number and off-design Mach numbers with an inlet having a caret configuration with rotatably extending effective leading edges on the inlet from a retracted position aligned with a nominal Mach number shock wave to an extended position aligned with an off-design Mach number shock wave. | 12-29-2016 |