Quotables
"What can be more palpably absurd than the prospect held out of locomotives traveling twice as fast as stagecoaches?"
The Quarterly Review ; March edition, 1825
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 |
| 4899596 | Self-calibrating torque measuring system A universal torque measuring system for hollow drive shafts which automatically compensates for variations in wall thickness exhibited by different drive shafts having the same nominal dimensions. During a calibration procedure, the drive shaft is subject... | 02/13/1990 |
| 4802823 | Stress relief support structures and assemblies An improved design for a structure such as a turbine vane or blade subjected to extreme temperature levels and/or gradients resulting in extreme deformation stresses within the structure. The present structures comprise an interior skeletal support having... | 02/07/1989 |
| 4712372 | Overspeed system redundancy monitor A redundancy monitor is presented which makes operational checks on the electronic overspeed control system used on aircraft turbine engines. The monitor is a small and lightweight device that can be permanently installed on the engine. Its function is to... | 12/15/1987 |
| 4658110 | Method and apparatus for welding A laser beam is used to weld two or more overlapping layers of metal together. The beam is applied through tubular clamping elements which engage and squeeze the metal layers to be welded. By inserting an inert gas within the tubular elements, an oxygen-f... | 04/14/1987 |
| 4651521 | Convertible turbo-fan, turbo-shaft aircraft propulsion system A composite turbo-fan/turbo-shaft gas turbine engine system is provided wherein the fan is driven through a variable geometry torque coverter whose input is driven by the turbine power shaft supplied through a reduction gear. Actuation of the variable geo... | 03/24/1987 |
| 4645420 | Propeller control system A propeller control system, including a propeller governor, overspeed governor, and a bleed valve, is provided to control the flow of fluid under pressure from a pump to an hydraulically controlled, variable pitch propeller driven by a gas turbine engine.... | 02/24/1987 |
| 4644129 | Apparatus and method for edge welding sheet metal A laser welding apparatus and process is provided for edge welding sheets of metal to one another. The laser welding apparatus includes aligners to advance the edges to be welded into the laser beam. The apparatus includes first and second laser welders. ... | 02/17/1987 |
| 4642993 | Combustor liner wall A combustor liner wall is provided with an interior wall, an exterior wall and a honeycomb structure disposed therebetween. The honeycomb structure is formed with generally radially aligned cells. The cells are constructed to define alternate array of gap... | 02/17/1987 |
| 4643636 | Ceramic nozzle assembly for gas turbine engine A ceramic nozzle assembly for a gas turbine engine is provided. The assembly includes ceramic inner and outer shroud rings dimensioned to be concentrically disposed relative to one another. Recesses are provided in the outer circumferential surface of the... | 02/17/1987 |
| 4633057 | Laser welder fault detector A laser welder fault detector system, including a microphone and an associated electronic circuit operatively connected to a solenoid actuated ink jet, is provided to detect the formation of defective welds by an intermittently energized laser and to spra... | 12/30/1986 |
| 4627789 | Apparatus method for calibrating and setting compressor air bleed valve schedules A device is provided for indicating a fluid pressure and flow reversal. The device comprises a float tube in which a float is slideably disposed. An accumulator is disposed in communication with the float tube. The float tube is further in communication w... | 12/09/1986 |
| 4622050 | Air inlet filter for gas turbine engine An annular air filter is rotationally mounted within a plenum box, which in turn is securely mounted to the inlet end of a gas turbine engine. At least a portion of the annular air filter surrounds the inlet end of the engine. A motor is provided to rotat... | 11/11/1986 |
| 4613280 | Passively modulated cooling of turbine shroud A turbine engine is constructed to passively modulate the flow of cooling air into the shroud. Sealing rings are disposed relative to the cooling air inlets in the shroud such that pressure and temperature variations in the engine will cause the cooling a... | 09/23/1986 |
| 4569196 | Lubrication system A lubrication system including a regulating valve and a bellows is provided for controlling the flow of lubricant from a source of lubricant under pressure to the gearbox and sump of an aircraft gas turbine engine as a function of the altitude at which th... | 02/11/1986 |
| 4566939 | Surface preparation of nickel base alloys for brazing A method is disclosed for the removal of undesirable oxides from the surface of nickel-base or nickel-iron base alloys containing oxidizable aluminum and/or titanium prior to brazing. The alloy is heated in air at an elevated temperature for a time suffic... | 01/28/1986 |
| 4541237 | Sub-idle speed control apparatus for an airplane turbine engine A sub-idle speed control apparatus for reducing the thrust of an airplane turbine engine is provided. The subject invention reduces the compressor discharge pressure measured by an existing pressure sensing means which proportionally reduces the fuel flow... | 09/17/1985 |
| 4514470 | Diffusion bonding between titanium base alloys and steels Disclosed is a novel three-layered metallic interlayer material which provides good diffusion bonding between titanium alloys and steel or between titanium alloys and nickel alloys. The interlayer is comprised of three separate layers of metals as follows... | 04/30/1985 |
| 4502275 | Compressor air bleed override control system A compressor air bleed override control system is provided to bleed interstage air from the compressor of an aircraft turbine engine under the conditions during which a compressor instability, such as surge, is likely to occur. The override system include... | 03/05/1985 |
| 4500038 | Powder feed system with recirculator for plasma spray apparatus A powder feed system with a recirculator is provided for a plasma spray apparatus so that spraying operations may be started and stopped abruptly. The subject system utilizes a pressurized gas to direct a powdered material from a powder feed hopper to the... | 02/19/1985 |
| 4477089 | Honeycomb seal for turbine engines An improved honeycomb seal is provided for turbine engines. The subject honeycomb structure comprises a plurality of identical rings. Each ring has a plurality of radially extending convolutions defining alternating ridges and valleys. The rings are fixed... | 10/16/1984 |
| 4470754 | Partially segmented supporting and sealing structure for a guide vane array of a gas turbine engine A nozzle of a gas turbine engine includes an array of radially extending guide vanes fixedly supported at their tip portions to an outer shroud, while the root portion of each vane is connected to a segment of a radially inner, segmented shroud. Each segm... | 09/11/1984 |
| 4470454 | Primary surface for compact heat exchangers A heat exchange apparatus is provided with a plurality of plates formed and stacked so at to provide heat transfer through the plates from a first gas to a second gas. The plates are of substantially identical configuration and size, each of the plates fo... | 09/11/1984 |
| 4470453 | Primary surface for compact heat exchangers A heat exchange apparatus having a plurality of plates through which heat is exchanged from a first gas to a second gas is provided with a plurality of plates having first and second opposing patterns. Each of the opposing patterns is provided with a plur... | 09/11/1984 |
| 4465427 | Air and oil cooled bearing package A combination air and oil cooled seal housing is provided which also utilizes trapped stagnant air as an insulator. The combination prevents coking of the oil supplied as a lubricant to the bearings and seals in the hot section of a turbine engine. Pressu... | 08/14/1984 |
| 4455821 | 101 Electronic fuel control ignition interlock A simple continuity circuit is provided interconnecting the connector bodies of a wiring harness which directs the signal from the computer control of a gas turbine engine to the fuel metering unit of said engine. The continuity circuit forms part of the ... | 06/26/1984 |
| 4454711 | Self-aligning fuel nozzle assembly A self-aligning fuel nozzle assembly is provided for maintaining the alignment of a swirler member and a fuel nozzle upon displacement of the combustor liner relative to the combustor housing of a combustion chamber assembly in a turbine engine. The self-... | 06/19/1984 |
| 4455121 | Rotating turbine stator Hot spots in the first stage turbine nozzles of small and medium sized engines are eliminated by spinning the nozzle assembly which consists of an annular hub circumscribed by a nozzle diaphragm having an inner and outer shroud ring between which are a mu... | 06/19/1984 |
| 4452037 | Air purge system for gas turbine engine Apparatus is disclosed for automatically purging oil from the jets supplying lubricant to bearings and seals in a turbine engine after shutdown. To accomplish this task, pressurized air is tapped from the air plenum just downstream of the engine compresso... | 06/05/1984 |
| 4451200 | Air and oil cooled bearing package A combination air and oil cooled seal housing is provided which also utilizes trapped stagnant air as an insulator. The combination prevents coking of the oil supplied as a lubricant to the bearings and seals in the hot section of a turbine engine. Pressu... | 05/29/1984 |
| 4451431 | Molybdenum-containing high temperature coatings for nickel- and cobalt-based superalloys Disclosed are novel high temperature coatings which may be applied to turbine engine components to provide improved thermal fatigue resistance as well as improved oxidation and corrosion resistance. The compositions have one of the following general formu... | 05/29/1984 |
| 4444353 | Brazing filler metal composition and process Disclosed is a brazing filler metal composition comprising, by weight, about 3.0% to 4.0% chromium, about 1.0%-2.0% boron; about 2.0%-2.5% silicon; about 1.0%-2.0% iron; about 5.0%-6.0% phosphorus; a maximum of about 0.06% carbon and the remainder nickel.... | 04/24/1984 |
| 4442968 | Brazing filler metal composition and process Disclosed is a brazing filler metal composition comprising, by weight, about 8% to 11% chromium, 2.0%-3.0% boron, 3.0%-4.5% silicon, 2.5%-4.0% iron, 7.0%-9.0% tungsten, a maximum of about 0.06% carbon and the remainder nickel. Further disclosed is a vacuu... | 04/17/1984 |
| 4431050 | Stacked-plate heat exchanger made of identical corrugated plates Plates of identical configuration are formed of relatively thin material and are assembled in stacked construction pairs, with alternating patterns of different corrugations being provided between spaced openings in each plate. Alternate plates in each st... | 02/14/1984 |
| 4430907 | Throttle control linkage with non-linear output A linkage system is disclosed adapted to be connected between a pilot's input lever and an engine power output lever. The linkage system is operative to vary the displacement ratio characteristics between the input and output levers. More specifically, du... | 02/14/1984 |
| 4403912 | Integrated multiplane actuator system for compressor variable vanes and air bleed valve A linkage system for actuating the variable vanes and the air bleed valve of a gas turbine engine compressor in an intermittent sequence includes a single actuator and a linkage mechanism. The latter is formed of a first actuating linkage extending to the... | 09/13/1983 |
| 4398866 | Composite ceramic/metal cylinder for gas turbine engine A cylinder of a gas turbine engine is formed of a multilayered construction including a radially inner ceramic ring, the inner surface of which is juxtaposed to the tips of a turbine rotor, an intermediate arrangement of two annular ceramic rings that are... | 08/16/1983 |
| 4397431 | Fail-safe, anti-icing system for aircraft engines An actuating linkage is provided for use in an aircraft engine having a double door-type particle separator, anti-icing system installed within its air intake ducts. The actuating linkage interconnects the deflecting vane and the bypass door through a cou... | 08/09/1983 |
| 4394347 | Brazing filler metal composition and process Disclosed is a brazing filler metal composition comprising, by weight, about 8% to 11% chromium. 2.0%-3.0% boron, 3.0%-4.5% silicon, 2.5%-4.0% iron, 7.0%-9.0% tungsten, a maximum of about 0.06% carbon and the remainder nickel. Further disclosed is a vacuu... | 07/19/1983 |
| 4384727 | Circumferential ring seal assembly A ring seal assembly 20 is disclosed for reducing leakage about a part, such as a shaft or a piston cylinder having a surface of circular cross section. The assembly includes primary and secondary seal rings 22, 24, having radially inner and outer periphe... | 05/24/1983 |
| 4379121 | Brazing filler metal composition and process Disclosed is a brazing filler metal composition comprising, by weight, about 3.0% to 4.0% chromium, about 1.0%-2.0% boron; about 2.0%-2.5% silicon; about 1.0%-2.0% iron; about 5.0%-6.0% phosphorus; a maximum of about 0.06% carbon and the remainder nickel.... | 04/05/1983 |
