Abstract: A system, method, and program product is described that is constructed to establish a database of market information, relating to a target product and its competitors in the market. The database is processed to allow the user to establish a price for the target process based on customer perceived value and to display the processed information in several useful charts and tables for product value comparison, appraisal, and pricing.

Abstract: 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 monitor both the speed pickups that count the revolutions per minute that the turbine shaft is turning and at the same time maintain a check on the performance of the circuitry which processes the data. The monitor includes a latching type BITE indicator which signifies redundant status of the speed pickups and a lamp which lights to indicate any failure in the output circuitry of the overspeed sensor system. A momentary-on type switch activates self test circuitry within the redundancy monitor.

Abstract: 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-free weld zone may be obtained. The laser beam is deflected to create a substantially spiral-shaped weld pattern.

Abstract: 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 geometry of the torque converter provides a wide variety of operating modes including all power to the power output shaft and combinations in between.

Abstract: 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. Under normal operating condition, the propeller governor controls the pressure of the fluid supplied to the propeller, adjusting its pitch as needed to maintain constant speed operation. The overspeed governor prevents overspeeding of the propeller and engine in the event that the propeller governor becomes inoperative, and, in the event that both governors become inoperative, the bleed valve prevents sudden increases in fluid pressure, attendant with the failure, from adjusting the pitch of the propeller towards an overspeed position.

Abstract: 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 inner shroud ring and apertures extend through the outer shroud ring in register with the recesses. Vanes extend through the apertures in the outer shroud ring and are engaged by the recesses in the inner shroud ring. A ceramic outer support ring slides over the outer shroud ring to securely retain the vanes. Slots or recesses are provided in both the inner and outer shroud ring to prevent rotation of the nozzle in the engine.

Abstract: 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. The first laser welder is operative to eliminate the edge discontinuities and to effect an initial attachment of the edges to one another. The second laser welder provides a larger and stronger weld bead. The process includes first aligning the edges, second removing discontinuities therefrom and third laser welding the edges. The discontinuities preferably are removed by a laser apparatus with a rotating lens.

Abstract: 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 air inlets to be either fully opened, completely blocked by the sealing ring, or modulating therebetween in accordance with the cooling needs of the shroud.

Abstract: 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 the engine is operating. An override valve by-passes the regulating valve and cuts off flow of lubricant to the sump while assuming control of lubricant flowing from the source to the gearbox when a detent valve, operatively associated with the bellows, detects that either the regulating valve or the bellows is inoperative and permits the override valve to become operative.

Abstract: 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 sufficient to form on the alloy surface a bilayered film comprised of a first oxide top layer containing at least titanium or aluminum and a second layer beneath the first comprised of the alloy composition substantially depleted of aluminum and/or titanium. The surface of the alloy is cleaned to remove the first oxide layer whereupon the remaining surface is in condition for brazing.

Abstract: 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 to the engine. Hence, the engine speed is reduced resulting in a lower engine thrust. A switch activates the apparatus which closes a normally open valve in the existing pressure line between the compressor and the pressure sensing means and diverts the pressure through a by-pass line having a restrictor. The by-pass line is connected to the existing pressure line on the compressor side and the pressure sensing side of the normally open valve. A normally closed valve and a spring loaded valve respectively are connected to the existing pressure line and the by-pass line at the connection point nearest the pressure sensing means. When the apparatus is activated the normally closed valve is opened simultaneously with the closing of the normally open valve.

Abstract: 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: a nickel layer which is placed in contact with the steel or nickel alloys, a Group V-B metal layer which is placed in contact with the titanium alloy and a copper layer which is sandwiched between the nickel and the Group V-B metal layers.

Abstract: 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 includes an override valve control that is in communication with an altitude sensor to make the system operative above a preselected pressure altitude, but inoperative below the selected pressure altitude. The altitude sensor is in communication with the engine fuel control power lever, which is an indirect sensor of compressor speed, such that at speeds corresponding to a slow deceleration from a sufficiently high altitude, the compressor bleed value will rapidly open. The system further measures the rate of movement of the power lever so that small but sufficiently rapid movements of the power lever, which are sustained for a selected period of time, will also cause the compressor bleed valve to open quickly.

Abstract: 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 plasma spray applicator. A diverter valve is located intermediate the powder feed hopper and the plasma spray applicator and in close proximity to the plasma spray applicator for selectively diverting the powdered material toward or away from the plasma spray applicator. Powdered material diverted away from the plasma spray applicator is directed to a powder accumulator for subsequent reuse. The powdered material is kept in continuous motion during both spraying and diverting operations thereby avoiding the need to overcome inertia each time spraying operations are commenced.

Abstract: 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 fixedly arranged in abutting relationship to define a tubular honeycomb structure having an array of radially extending honeycomb cells. The resultant honeycomb structure is adaptable to both large and small diameter turbine engines. Furthermore, the individual cells of the honeycomb structure can be constructed to any width or depth.

Abstract: 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 plurality of sinusoidally varying surface strips and a plurality of spacing ridges between the surface strips, whereby the second gas flows in a generally sinusoidal path in a first direction along a first side of the first and second patterns between the first and second plates and the first gas flows in a generally sinusoidal path in a direction opposite the first direction along the other side of the first and second plates. The plurality of spacing ridges on the second pattern are disposed relative to the spacing ridges on the first pattern such that the spacing ridges on the second pattern lie along a line substantially in the middle of the surface strips of the first pattern, and vice versa.

Abstract: 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 formed with a central opening and an alternating arrangement of first and second surface patterns, ports being provided between the first and second surface patterns. The plates are stacked such that adjacent plates are rotated 180.degree. about a diametrical axis relative to each other and so as to place the ports and patterns in alignment, surface patterns of the first type from any of the plates being adjacent to surface patterns of the second type on a plate adjacent thereto to form a plurality of opposing pattern pairs.

Abstract: 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 segment is, in turn, connected via a slip fit inter-connection to a radially inner ring support structure of generally L-shaped configuration. A spring extends between the segment and the base of the L-shaped ring support for forming a flexible coupling between the inner ring and the segment, while the remaining portion of the ring support structure defines a pressure dam to reduce leakage through the flexible coupling connection. The segmented nozzle construction effectively reduces stress levels resulting from differential thermal excursions of the components of the nozzle under transient and steady state operation of the engine, while also minimizing leakage through the flexible coupling.

Abstract: 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. Pressurized air is introduced from the compressor into the inner structure support housing by means of hollow passages. The pressurized air absorbs heat as it traverses the passages in the structure. The oil supplied is connected to an annular shape cavity allowing the oil to be circulated therein and cool the seal support structure. Additional insulation is provided by cylindrically shaped trapped air shields surrounding the bearing package. Oil flowing through the structure can then properly lubricate the seals and bearings which support the turbine rotor stages within the housing assembly.

Abstract: 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 ignition exciter circuit and acts to de-energize the exciter when the wiring harness is not in place. This prevents ignition when the failure mode of the fuel metering unit is directing a fuel flow to the combustor which is excessive for safe start-up.