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U.S. Senator Smith of Indiana ; After seeing Samuel Morse demonstrate the telegraph.
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| Number | Title | Issue Date |
| 5385013 | Aircraft gas turbine engine backbone deflection thermal control A gas turbine engine thermal backbone deflection control apparatus to counter the effects of backbone bending due to nacelle aerodynamic, thrust, and maneuver loads by introducing a controlled backbone counter-bending moment by applying an uneven temperat... | 01/31/1995 |
| 5369954 | Turbofan engine bypass and exhaust system A turbofan engine bypass and exhaust system has a double-hoop configuration in which a fan exhaust passageway comprises shells of a constant circular contour to resolve air pressure induced stresses and increase in bypass passageway area asymmetrically in... | 12/06/1994 |
| 5353865 | Enhanced impingement cooled components An improved heat transfer assembly includes a textured impingement surface and means for impinging cooling air directly upon the textured surface. A component includes a surface textured to increase convective heat transfer with minimal increase in resist... | 10/11/1994 |
| 5351476 | Nacelle cooling and ventilation system A nacelle cooling and ventilation system for an aircraft gas turbine engine which includes a chin scoop and duct assembly for directing air through the engine bay where it is exhausted into the engine exhaust through an exhaust shroud eductor. The nacelle... | 10/04/1994 |
| 5350279 | Gas turbine engine blade retainer sub-assembly A blade retaining sub-assembly for use in a gas turbine engine which includes at least one radially extending blade mounted in a dovetail slot of a rotatable annular disk. The sub-assembly prevents the blade from migrating from the dovetail slot in an axi... | 09/27/1994 |
| 5350200 | Tube coupling assembly A tube coupling assembly for use in connecting first and second fluid-carrying tubes comprising an annular sleeve member and an annular ferrule which are operably affixable to respective ones of the tubes. A tube connector and a coupling nut threadingly e... | 09/27/1994 |
| 5336044 | Blade containment system and method A blade containment system and method for use in a gas turbine engine having a plurality of blades mounted on a rotatable disk. The system comprises an annular casing in surrounding relationship with the blades and a plurality of panels, each having an in... | 08/09/1994 |
| 5333995 | Wear shim for a turbine engine A wear shim assembly is provided which includes a substantially U-shaped wear shim for protecting selected wear surfaces on the engine casing of a gas turbine engine. The wear shim advantageously simultaneously protects multiple surfaces of the engine cas... | 08/02/1994 |
| 5319922 | Aircraft gas turbine engine backbone deflection control A gas turbine engine backbone deflection control apparatus to counter the effects of backbone bending due to gust, thrust. and maneuver loads by introducing a controlled backbone counter-bending moment by applying controlled tensioning forces only between... | 06/14/1994 |
| 5320134 | Squeeze film shaft damper oil system A non-symmetrical circular row of oil inlets are located in a circular manifold surrounding a squeeze film space in a squeeze film damper. The oil inlets are directed radially inwardly from said manifold to open into the squeeze film space. Certain cluste... | 06/14/1994 |
| 5317877 | Intercooled turbine blade cooling air feed system A gas turbine engine having a compressor and an air-cooled turbine is provided with a cooling system for decreasing the temperature of the turbine cooling air. A heat exchanger, mounted on the compressor casing, receives a portion of the pressurized air w... | 06/07/1994 |
| 5316391 | Squeeze film damper seal Spring ring type seals are substituted for the usual piston ring seals in squeeze film dampers for bearings to provide more available space and location for oil plenums in the squeeze film space and a more constant and continuous circumferential oil seal.... | 05/31/1994 |
| 5313788 | Thrust reversing arrangement for a long duct mixed flow exhaust turbofan engine A thrust reverser for a long duct mixed flow fan jet engine having a nacelle formed by a fixed forward structure surrounding the fan, a rear fixed structure and a translatable inner and outer cowl therebetween, the nacelle surrounds the engine and forms a... | 05/24/1994 |
| 5302085 | Turbine blade damper A generally wedge-shaped vibration damper for rotor blades of a gas turbine engine has a pair of scrubbing surfaces and is loosely retained in a pocket incorporated in the rotor blade platform. The pocket is partly defined by a plurality of surfaces which... | 04/12/1994 |
| 5301957 | Expanding circumferential seal with upper-cooled runner A circumferential seal arrangement has one or more expanding carbon rings and a rotating runner concentric to and radially outside of the carbon rings. Cooling oil is injected directly onto the outer circumferential surface of the runner and also in the d... | 04/12/1994 |
| 5299914 | Staggered fan blade assembly for a turbofan engine A turbofan gas turbine engine fan stage having alternating relatively rugged, preferably hollow titanium, blades and staggered relatively less rugged, preferably composite, blades. The blades are staggered such that the leading edges of the rugged titaniu... | 04/05/1994 |
| 5285636 | Diagnostic drain mast for a gas turbine engine An improved drain mast assembly for a gas turbine engine is connected to an outer surface of a nacelle of the engine and has a plurality of liquid drain lines terminating within the assembly. The assembly comprises a plurality of liquid collection chamber... | 02/15/1994 |
| 5284012 | Nacelle cooling and ventilation system A nacelle cooling and ventilation system for an aircraft gas turbine engine which includes a chin scoop and duct assembly for directing air through the engine bay where it is exhausted into the engine exhaust through an exhaust shroud eductor. The nacelle... | 02/08/1994 |
| 5284347 | Gas bearing sealing means A gas bearing face seal assembly for a gas turbine engine having improved sealing characteristics. The assembly can include support means which concentrically position a face seal member with respect to a seal radius, while permitting translation of the f... | 02/08/1994 |
| 5280736 | Engine shaft balance assembly A balancing assembly for a gas turbine hollow drive shaft is disclosed. The balance assembly includes an expandable balance weight carrier and a device for expanding the carrier inside the hollow drive shaft. In a preferred embodiment the carrier comprise... | 01/25/1994 |
| 5273249 | Slide joint bracket A support system for coupling elements of different temperatures while reducing thermal and dynamic stress. The support system couples a fuel manifold to a combustor in a gas turbine engine and includes first and second elongated brackets connected, respe... | 12/28/1993 |
| 5269133 | Heat exchanger for cooling a gas turbine A heat exchanger for cooling turbine components of a gas turbofan engine in which air to be cooled is directed along a first annular, radially extending path away from the engine and cooled by bypass air. The cooled air is returned to the engine along a s... | 12/14/1993 |
| 5263898 | Propeller blade retention system The invention concerns the mounting of propeller blades to a ring-shaped rotor. The blades are of the variable pitch type, and the shank of each blade extends through a respective hole in the rotor. Each hole contains an annular shelf which is fastened to... | 11/23/1993 |
| 5261790 | Retention device for turbine blade damper A generally wedge-shaped vibration damper for rotor blades of a gas turbine engine has a pair of scrubbing surfaces and is loosely retained in a pocket incorporated in the root cavity. The pocket is partly defined by a plurality of surfaces which orient t... | 11/16/1993 |
| 5261240 | Fuel shroud system with spherical ferrule/drain can interface A fuel shroud system has a chamber for draining leaked fuel. The chamber is partly defined by a drain can and a sealing ferrule having a spherical sealing ferrule/drain can interface. The spherical interface allows rotation of the drain can relative to th... | 11/16/1993 |
| 5259185 | Fuel drainage connector system for aircraft gas turbine A fuel drain can assembly positioned between the fuel manifold and the fuel nozzles of a gas turbine engine which utilizes detachable connectors rotatable into locking engagement without special tooling.... | 11/09/1993 |
| 5259234 | Calibration system for air metering bellmouths The present invention provides a system, including apparatus and method, using a National Bureau of Standards (NBS) traceable laser velocimeter for in situ calibration of a traversing static pressure probe used to determine a velocity distribution in an a... | 11/09/1993 |
| 5259724 | Inlet fan blade fragment containment shield A blade containment system for fan blades of a gas turbine engine includes a fan casing surrounding the fan blades and serving as a first blade containment structure and a second blade containment structure positioned axially forward of the fan casing wit... | 11/09/1993 |
| 5251985 | Squeeze film damper seal A conical spring ring oil seal at the ends of a squeeze film shaft damper replaces conventional internal piston ring seals to provide circumferential oil sealing of an annular squeeze film space in the damper.... | 10/12/1993 |
| 5242265 | Aircraft pitch change mechanism A system for changing pitch in aircraft propfans is disclosed, in which a motor, located at a stationary position, changes pitch of the blades by of a gear train. Three features of the system are that a feather brake can override the motor and drive the b... | 09/07/1993 |
| 5242033 | High power gear cooling system A cooling system for a high speed gear includes a plurality of passages extending through the gear and a hydraulic slip ring for delivering cooling fluid to the passages and for scavenging cooling fluid after it passes through the passages. The slip rings... | 09/07/1993 |
| 5239817 | Fire zone ventilation shut-off system A fire emergency ventilation shut-off system for an aircraft having at least one fire zone, includes at least one shut-off valve having an element disposed in an inlet of the fire zone, the valve element being movable between open and closed positions and... | 08/31/1993 |
| 5238365 | Assembly for thermal shielding of low pressure turbine A thermal seal and insulating assembly for the low pressure turbine stage of a gas turbine engine having an inner liner and an outer liner which are connected by a 360° ring. The ring serves to insulate a low pressure turbine case which is located radial... | 08/24/1993 |
| 5232012 | Fluid flow control device A spaced apart apertured dual diaphragm fluid flow control device utilizes one flexible overcenter diaphragm to sense a variance flow condition and flex over center into engagement with the other diaphragm where cooperative apertures in the diaphragms cut... | 08/03/1993 |
| 5232335 | Interstage thermal shield retention system An interstage thermal shield assembly for a gas turbine engine. The assembly includes an axially-extending thermal shield positioned between first and second stage disks to form a seal therebetween. The thermal shield includes complementary hook members s... | 08/03/1993 |
| 5232339 | Finned structural disk spacer arm A rotor disk assembly includes rotor disks and structural spacer arms adapted to transmit axial loads and bending moments between adjacent disks. The spacer arms include cooling fins for convective cooling of the spacer arms. The spacer arm is preferably ... | 08/03/1993 |
| 5228784 | Squeeze film damper composite ring seal A piston type ring which includes a continuous synthetic material O-ring concentrically mounted thereon in a groove in the outer circumference of the ring is utilized as a piston ring seal in a squeeze film damper.... | 07/20/1993 |
| 5226287 | Compressor stall recovery apparatus A compressor stall recovery apparatus senses a compressor stall condition and cuts off the supply of fuel to selected ones of the nozzles of the combustor until after the stall condition has abated.... | 07/13/1993 |
| 5226785 | Impeller system for a gas turbine engine An interstage thermal shield assembly for a gas turbine engine. The assembly includes an axially-extending thermal shield positioned between first and second stage disks to form a seal therebetween. The thermal shield includes complementary hook members s... | 07/13/1993 |
| 5224713 | Labyrinth seal with recirculating means for reducing or eliminating parasitic leakage through the seal A labyrinth seal for use in a gas turbine engine and placed between adjacently lying differently pressurized compartments where leakage may occur from the higher to the lower pressure compartment, the seal includes a stationary annular abradable shroud an... | 07/06/1993 |
