Bizarre Patents
Cloaking System Using Optoelectronically Controlled Camouflage
A Cloaking System designed to operate in the visible light spectrum, utilizes optoelectronics and/or photonic components to conceal an object within it.
PatentStorm News
Make the Most of Our Site
See this month's Top Inventors and Most Cited Patents.
Stay on top of the latest innovations by subscribing to an RSS feed.
Registered users: Manage your profile.
| Number | Title | Issue Date |
| 5732466 | Manufacturer of brush seals Excess length 20 of brush seal wires 14 is sheared off with a punch 30 and die 26. A true and accurate diameter 22 is formed. The wires can be ground to a final finish diameter 18 if desired.... | 03/31/1998 |
| 5581999 | Bulkhead liner with raised lip Bulkhead 14 is conical and therefore the surface of bulkhead liners 30 has a curved or arcuate surface 68. Raised lip 70 with planar surface 72 is adjacent and surrounded in each opening 20. Fuel nozzle guide 24 may be rotated against and sealed to the su... | 12/10/1996 |
| 5580183 | Gas turbine engine spline arrangement A hollow drive shalt (20) with external splines (26) and drives a hollow driven shalt (14) which has internal splines (32). The driven shalt (14) thickness is uniformly tapered in the spline area, while the drive shalt (20) has a constant thickness throug... | 12/03/1996 |
| 5577379 | Fuel nozzle guide retainer assembly Fuel nozzle guide 24 is threaded to fuel nozzle guide retainer 26, entrapping bulkhead 14, bulkhead liner 30 and key washer 28. Internal tabs 74 lock within slot 76 in the threads of the fuel nozzle guide. External tabs 78 of the key washer are bent into ... | 11/26/1996 |
| 5542246 | Bulkhead cooling fairing Cooling air flow from behind bulkhead liner segments 30 and from behind float wall panels 42 is guided as flow 50 over the hot surface of the bulkhead liner segments by fairing 44. The fairing is secured between a shell (38,40) and a float wall panel 42, ... | 08/06/1996 |
| 5524438 | Segmented bulkhead liner for a gas turbine combustor Truncated pie shaped bulkhead liner sections 60 are each divided into two liner segments 62. The division occurs adjacent fuel nozzle opening 20. Upstream extending lips 71, 75 and 77 abut the bulkhead 14. Cooling air passes through cooling flow openings ... | 06/11/1996 |
| 5516257 | Aircraft fan containment structure restraint Woven fiber ballistic fabric (22) of multiple layers surrounds an isogrid support structure (20). A cuff portion (38) has shorter warp threads than the major portion (3) and also is impregnated with epoxy resin. A diameter restrains the fabric from aft mo... | 05/14/1996 |
| 5511376 | Axisymmetric vectoring nozzle A convergent/divergent nozzle (14) has five trains of flaps. Each train is comprised of an inboard (26) and outboard (20) convergent flap, an inboard (48) and outboard (44) divergent flap and an external flap (62). The five external flaps (62) maintain th... | 04/30/1996 |
| 5486091 | Gas turbine airfoil clocking The first stage of vanes (16) and second stage of vanes (24) each contain the same number of vanes. The second stage vanes are located such that the wake flow (38) from the first stage vanes falls on or near the leading edge, after passing through the sta... | 01/23/1996 |
| 5485723 | Variable thickness isogrid case A light weight isogrid containment structure has minor concessions to weight in order to achieve efficient manufacture oversize flanges are permitted in skin thickness interface zones so that manufacture may be accomplished with fewer milling tools and to... | 01/23/1996 |
| 5462403 | Compressor stator vane assembly The arcuate vane support segments (26) each carry a plurality of vanes (28) and have a pair of axially extending feet (38). These feet do not slide axially into a groove, but move radially against an arm (22) of the "T" shaped air seal. The casing ring 62... | 10/31/1995 |
| 5461866 | Gas turbine engine combustion liner float wall cooling arrangement When second shell section 18 diverges with respect to first shell section 16, the second liner panel 50 is located with a changing spacing from the shell. The liner is close to the shell at the upstream edge 68, and farther from the liner at the downstrea... | 10/31/1995 |
| 5460489 | Turbine blade damper and seal A flexible seal (26) is located beneath blade platform (14) with end seals (28) in contact with adjacent platforms. A friction damper (34) formed of a flat slug of metal is supported only by the flexible seal (26) and in particular by the center section (... | 10/24/1995 |
| 5448829 | Hollow titanium blade manufacturing A titanium gas injection tube 18 is located within a counterbore (16) in the blade (10) halves which are to be bonded and formed. An internal stainless steel sleeve (24) is placed in the counterbore inside the titanium tube to resist bonding forces. An ex... | 09/12/1995 |
| 5431344 | Sliding throat gas turbine engine nozzle Exit area control panels 18 are supported for movement at an angle with respect to the nozzle axis 12. A varying exit area is formed as actuator 26 axially positions the panels 18. In each exit area control panel 18, there is slidably supported a throat a... | 07/11/1995 |
| 5431537 | Cooled gas turbine blade A hollow air cooled airfoil blade (10) castable with a single pull core and having internal trip strips (28) at the leading edge. Parallel ribs (16,18) extend from the pressure side (12) of the blade to the suction side (14). A parting line (32) passes th... | 07/11/1995 |
| 5419040 | Hollow fan blade fabrication Purge flow openings through chordwise ribs in hollow fan blades are formed by making partial circular cuts at the rib edges before diffusion bonding the blade halves. A full semi-circular section is used on the pressure side, but only a segment of a semic... | 05/30/1995 |
| 5413456 | Aircraft fan containment structure Isogrid structure (20) forms case (14) surrounding the fan blades. In the zones where blade penetration is anticipated, the ribs (38) of the lattice do not run circumferentially. The skin segments (48) are of different thickness in different zones, but do... | 05/09/1995 |
| 5411369 | Gas turbine engine component retention A split retaining ring 22 has deep internal scallops 26 which clear lugs 36 during installation while the ring fits within lip 40. The ring is opened with ridges 30 clearing lugs 36 while the ring is rotated. Shallow internal scallops rest on and lock wit... | 05/02/1995 |
| 5409349 | Turbofan containment structure Isogrid structure (20) forms case (14) surrounding the fan blades (12) of the turbofan. A ballistic fabric (22) surrounds the case. Containment zones (30, 32, 34) at the forward end have isogrid ribs (38) extending other than circumferentially. In the rea... | 04/25/1995 |
| 5407133 | Cooled thin metal liner A first metal sheet (34) has openings (46) in registration with depressions (40) in a second contacting metal sheet (36). Each depression has a downstream wall (42) at an angle of 24° from the plane of the sheets. A metering hole (56) in the depression a... | 04/18/1995 |
| 5402633 | Premix gas nozzle A premix gas nozzle has longitudinal tangential entrance slots to a cylindrical chamber. There is an axially increasing flow area toward the chamber outlet, with pilot fuel centrally introduced near the outlet. A lean mix low NOx fuel nozzle is thereby st... | 04/04/1995 |
| 5402632 | Method of surge detection The double derivative of the gas generator shaft (16) is sensed and compared to upper and lower limits to determine breaches of these limits within a first predetermined time, in which case a first potential surge condition is declared. The derivative of ... | 04/04/1995 |
| 5403071 | Method of brush seal tufting Wire is wound from spool 10 onto drum 15 where a multiple strand rope is formed and gripped at multiple locations. The gripped rope is cut into individual bundles, one end of each bundle being bonded to join the wires of the bundle together. The tufts may... | 04/04/1995 |
| 5396793 | Altitude gas turbine engine test cell The test cell has a pressure recovery pipe (26) receiving air from the tested engine (14). Excess air is inherently induced into the pipe. A source flow path for this excess air is provided from within the pipe (36) back to the entrance the pipe passing t... | 03/14/1995 |
| 5387081 | Compressor diffuser Compressor 14 of a gas turbine engine has a final centrifugal stage 18 discharging air into annulus 20. Diffuser 20 are straight and of frustoconical shape receiving air from the annulus. A side cut produces opening 38 in the side of each diffuser. Much o... | 02/07/1995 |
| 5380155 | Compressor stator assembly Stator vanes (22) are potted within pockets (38) in composite inner shroud sections (36). The pocket depth is only that required for bond strength and vane damping. Ribs (48) extend inwardly and are adhesively bonded to the seal support ring (32,34) which... | 01/10/1995 |
| 5378108 | Cooled turbine blade Turbine blade (10) has a plurality of trailing edge discharge openings (28) discharging cooling air. The blade trailing edge has an increasing thickness "E" toward the tip end (16). Discharge openings with the shortened pressure wall "L" have lesser dista... | 01/03/1995 |
| 5370312 | Gas turbine engine exhaust nozzle The spherical portions of two gimbal (18) mounted convergent flaps (26,28) have hub structures (24) of concentric hubs (54,56). A piston (38) within each hub carries an annular seal (36) which is urged into sealing contact with the spherical static struct... | 12/06/1994 |
| 5364029 | Axisymmetric convergent/divergent nozzle with external flaps The gas turbine engine nozzle has fifteen divergent flaps (18) secured to fifteen convergent flaps (14). Five external flaps (30), are each of a "V" shape, and surround the divergent flaps. The position of all flaps is adjustable (22) for varying the nozz... | 11/15/1994 |
| 5352091 | Gas turbine airfoil Tube 16 within airfoil 10 carries cooling air. Flow openings 28 in the tubes direct cooling air 29 against the airfoil inner surface 14. Protrusions 30 form extended surface in the form of segmented trip strips are located with segmented trip strips are l... | 10/04/1994 |
| 5350136 | Nacelle arrangement An inner cowl 30 is attached to outer cowling 26. When it is opened it rotates around hinge line extension 36. Latch band 38 has an arcuate upper link 44 secured to anchor 40. A lower link 50 circumferentially slides around the cowl on opening. The latch ... | 09/27/1994 |
| 5337452 | Sealed hinge arrangement Panels (10, 12, 16, 20) are joined on several hinge axes (14-22, 18-24), and may fold around either axis. A spherical ball (26) fits within a ball receiving socket (28) in the corner of each panel. Sealing against leakage, from one side of the panels to t... | 08/16/1994 |
| 5335489 | Gas turbine vectoring exhaust nozzle An exhaust nozzle has variable convergent flaps, ejector flaps, and short divergent flaps spaced inwardly from the ejector flaps, cooling air is introduced through the opening between the divergent and ejector flaps. When the nozzle is vectored, the size ... | 08/09/1994 |
| 5328098 | Thrust vectoring ejector nozzle The external flaps (32), which contain the ram air, continue to form a conical structure during vectoring. External flaps (32) are hinged to the unison ring (30) with ejector flaps (34) hinged to the external flaps. A scissors linkage ( 48 ) joins each ej... | 07/12/1994 |
| 5313786 | Gas turbine blade damper An integrated damper and windage cover 52 has a windage cover portion 56 cantilevered at the upstream end, free of contact with the blade platform 24, 32. The contact portion 54 is rigid and bears against the underside of the blade platform 24, spanning b... | 05/24/1994 |
| 5313038 | EDM drilling of low angle holes Low angle air directing slots in the tip of an airfoil are produced by forming an elongated electrode by forming notches on opposite sides of the electrode and performing electric discharge machine with the electrode. During machining the electrode is ori... | 05/17/1994 |
| 5307634 | Premix gas nozzle A premix gas nozzle has longitudinal tangential entrance slots to a cylindrical chamber. There is an axially increasing flow area toward the chamber outlet, with pilot fuel centrally introduced near the outlet. A lean mix low NOx fuel nozzle is thereby st... | 05/03/1994 |
| 5305609 | Seal assembly A fuel injector 14 passes through wall 10 to inject fuel into a hot supersonic air flow 12. Wedge seals 26, 28 seal against leakage in cooperation with injection air flow 37, being compressed within seal carrier 16. Face seals 30, 32 are compressed by cov... | 04/26/1994 |
| 5295773 | Self-locking pressed in insert arrangement Insert 16 has four radial slots 26 through shoulder 22 and wall 28. It is press fit within smooth hole 32 in case 10. Internal threads 24 are strained in the locking range 36 where bolt 18 is locked.... | 03/22/1994 |
