Abstract: An air pump useful in pumping gases containing abrasive particles is disclosed. A housing is constructed with a primary flow channel centered around the pump axis and a secondary flow channel annularly surrounding the primary channel just inside the outer housing wall. Within the midsection of the pump a powered impeller rotating within an axially symmetric shroud accelerates air drawn from the primary flow channel causing it to be discharged through an annular shaped ejector nozzle into a suction chamber. Presence of the high velocity airstream in the suction chamber draws the contents of the secondary flow channel into the suction chamber. The entrained contents of the primary and secondary flow channels are carried into the diffuser where the velocity energy of the mixture is converted into pressure. The pressurized mixture is then discharged through the exhaust section.

Abstract: In a turbine rotor assembly wherein ceramic blades are secured to slots provided in the periphery of a metallic rotor disc, a metallic jacket is interposed between each blade root and disc slot, and ceramic potting material is, in turn, interposed between the metallic jacket and the ceramic blade root. The metallic jacket also includes locking means to prevent upstream or downstream axial movement of the blade in the disc slot, with the resulting assembly effectively isolating the ceramic root from high localized loads and permitting a more uniform stress distribution on the critical root load bearing surfaces.

Abstract: A work stand for rotably mounting an engine thereon during the initial construction of the engine, or for repair of the engine, includes two concentric rings which are disposed in upstanding relationship and are mounted on a base. The inner ring is rotably mounted within the outer ring and includes a plurality of axially extending arms which engage the engine. The latter is mounted in a generally horizontal disposition and is rotable with the inner ring whereby access to the engine is unobstructed from either the top or bottom of the engine, as well as along the entire length of the engine. A locking mechanism is provided between the inner and outer rings of the work stand for maintaining the engine at the desired angular attitude, and the engine is mounted such that its center of gravity is disposed adjacent the upstanding planes of the concentric rings.

Abstract: An engine wash spray apparatus is releasably connected to the leading edge of a gas turbine engine for dispersing a cleaning, rinsing, or preservative fluid to the air intake area of the engine and on into the engine's internal air flow path. The apparatus includes a manifold having a plurality of nozzles of specific configuration and specific spaced relationship to achieve a uniform spray pattern, with each nozzle issuing an elongated spray, the longitudinal axis of which is generally perpendicular to a radius of the engine inlet, and with the nozzles being arranged within the engine inlet to achieve the overlapping wash spray. The cleaning fluid is dispersed within the air flow path of the engine while the engine is cranked, whereby the fluid is carried through the entire engine flow path for cleaning of the engine components.

Abstract: The invention relates to a method of fabricating a torque sensor to which are applied strain gauges, with the torque sensor being adapted to be coupled between an engine and an absorption dynamometer for use in measuring the torque output of the engine. The subject process results in an integral assembly of two cylindrical rings interconnected by a plurality of elongated bars or beams to which the strain gauges are attached. During the process, a plurality of spaced holes are simultaneously drilled in the two identical, cylindrical rings, after which the rings and beams are assembled such that the rings are disposed in spaced relationship, and with the elongated beams extending between the rings. The beams are connected to the rings by electron beam welding so as to form an integral torque sensor assembly.

Abstract: A cylindrical type automotive barrier filter is adapted to be used in the inlet airflow of a gas turbine engine that is used in an agricultural aircraft. Air is drawn in through an inlet in the upper portion of the aircraft nose body without appreciable disturbance to the aerodynamic contours. The outlet of the filter is connected to a duct in a sealed relationship to direct the airflow to the engine inlet. The airflow passage is sealed by a connecting flange mounted on the filter to which the duct is connected. A longitudinally extending firewall is constructed to separate the filter and connecting duct from the turbine section of the engine. An emergency bypass door is provided to provide an inlet airflow in the event the filters become clogged. The bypass door is designed to provide particle separation of the incoming air.

Abstract: A support strut for gas turbine engines is disclosed which includes an internal wall employed as a lubricating oil duct and which is separated from the outer wall to form an insulating chamber which is closed at one end and which is sealed at the other end by means of a sliding seal member which bridges the open end of the chamber. The sliding seal preferably is secured to the outer strut wall and includes a sleeve portion in telescoping engagement with the interior wall of the oil duct.

Abstract: In a gas turbine engine an auxiliary airflow is provided to power accessories. This auxiliary airflow is obtained from a bleed aperture which is constructed immediately downstream of a diffuser vane in a cusp which is formed in the trailing edge of the vane to provide inertial separation. This high energy air from the diffuser is used as the primary airflow in an ejector to draw ambient air into the auxiliary airflow to lower the temperature of the bleed air. The ejector is constructed to automatically adjust the amount of ambient air according to the energy of the bleed airflow by means of a piston actuated spike mounted for sliding movement in the primary nozzle. The spike varies the volume of flow through the primary nozzle according to the pressure exerted by the airflow on the piston.

Abstract: This invention relates to apparatus which provides a positive flow of ambient air through the temperature sensor of the fuel control equipment used with a turbofan engine. The temperature sensing element of the fuel control unit is bathed in a continuously fresh sample of ambient air drawn in from the engine inlet by an air-jet pump that is powered by pressurized air bled-off from the bypass fan duct.

Abstract: A stepless variable stroke drive particularly suitable for a bicycle transmission has a crank driven input element comprising a carrier housing journaled for rotation on a spindle. Mounted within the carrier, journaled on individual axles, radially spaced to the spindle, are four planet gears which engage an output sun gear. Recessed into one side of each planet gear is a concentric channel whose outer circumference is constructed with ratchet teeth and whose inner circumference journals a crank ring having pawls for engaging the ratchet teeth. The ring also has a follower which engages a cylindrical cam channel fixed on and adjustable to various eccentricities relative to the spindle. As the carrier housing rotates, the crank ring follower engages the cam channel causing the crank rings to angularly oscillate at an amplitude proportional to the cam channel eccentricity.

Abstract: A turbine nozzle has a metal inner shroud that is joined to a metal outer shroud by a limited number of metal blades for structural purposes, and includes a plurality of air flow guidance vanes made of ceramic material and connected to the shrouds by spring clips. The composite structure allows the turbine nozzle to operate at higher temperatures with less cooling.

Abstract: A combining reduction and accessory gear box receiving power input from a multiple of gas turbine engines includes provisions for providing separate accessory drives for each engine used therewith, and an output drive that is driven by any number or all of the engines. Each gas turbine engine, as well as the gears associated therewith and its connection to the output drive, is totally independent of the other engines.

Abstract: A torque correlation ring is disclosed which forms a part of a test stand useful in measuring performance of aircraft turboshaft engines. The torque ring assembly comprises two annular rings separated from each other by four short equally spaced beams. One of the annular rings is fixedly attached to the frame of the test stand. The engine casing is attached to the second ring. Attachment is such that the engine is axially suspended within the annular rings with the propeller shaft on one side and the turbine exhaust on the other. Torque reaction forces on the engine casing stemming from supplying power to a propeller will be passed from the second annular ring to the frame mounted, first annular ring via the four beams. The magnitude of this torque is measured by means of strain gages mounted on each of the four beams. The electrically combined signal from the strain gages represent an accurate measurement of the torque forces being supplied to the propeller by the engine under test.

Abstract: An oil supply system for pumping oil to the main shaft bearings seals, accessory gears and splines of a gas turbine engine is provided with a bypass duct controlled by a valve programmed to dump excessive oil flow at engine idle. The valve diverts oil flow from the bearings to prevent a build-up therein. A check valve is placed in the main supply line to the bearings and is designed to stop oil flow after engine shutdown.

Abstract: A flow stabilizer is presented which equalizes the flow of fluid through the passageways of the channel diffuser used with a centrifugal type rotary compressor. Slots are formed in the sidewalls of the flow separating vanes in the diffuser. The slots open into cavities within the vanes. The multiplicity of cavities communicate by means of openings through the diffuser wall into a common closed manifold. The fluid interconnection between the multiplicity of passageways in the diffuser and the encircling common manifold increases the operating range of the compressor since pressure surges in one or more passageways are quickly equalized.

Abstract: This invention relates to apparatus which harmlessly purges all fluids which leak from the fittings of a turbofan aircraft engine. Purging is achieved by passing a low speed flow of ventilating air along the exterior walls of the engine combustor section. This is accomplished by enshrouding the engine core with a cylindrical cowl. A space between the cowl and the engine combustor makes an annular shaped cavity. Ports in the cowl allow air to be brought into the cavity from the bypass ducting of the engine. The rapidly moving volume of air thus brought in vaporizes any fuel which leaks into the cavity. The vaporized air/fuel mixture is then exhausted into the hot gas plume emitted from the rear of the core engine.

Abstract: A primary and a secondary of an inductive position sensor are connected by a capacitively coupling means. An output of the position sensor is connected to a level detector functioning as a failure indicator. The capacitive coupling of the primary and secondary of the inductive position sensor results in the output of the position sensor being above a minimum signal level at every position including the position at which the sensor output indicates zero or null position. When the sensor output falls below the minimum signal level, the level detector indicates failure.

Abstract: The disclosure illustrates a closed loop aircraft transmission test set comprising a variable speed DC motor driving a speed changing gear box whose output shaft is coupled to the input of the transmission under test, the main output shaft of the transmission being coupled to a DC generator load, the output of the generator being used to supplement the input electric power used to operate the DC driving motor thus assuring power drain from the supply busses is only the amount needed to overcome system friction and efficiency losses.

Abstract: A gas turbine engine is described in which a compressor, combustor and turbine are arranged in series flow relationship. The compressor discharge is outwardly angled. This pressurized air is then introduced into a toroidal combustion chamber of the combustor to create an annular vortex within which the combustion process is maintained. The hot gas stream generated is discharged from the combustion chamber to a centripital turbine which drives the compressor rotor. A portion of the pressurized air is introduced into the combustion chamber adjacent the hot gas stream discharge exit and in general flow opposition thereto, to dilute the hot gas stream and confine the combustion process within the combustion chamber, thereby minimizing the possibility of overtemperaturing the turbine. The combustor housing also defines the outer bounds of the hot gas stream flowing through the turbine. A power turbine converts a major portion of the energy of the hot gas stream to a motive shaft power output.

Abstract: A low pollution combustor is shown for controlling gas turbine pollutant emission, especially NO.sub.x. Fuel is injected and mixed with air upstream of the combustion zone. An axially movable baffle controls the air flow so that the fuel-air ratio is precisely controlled passing into the primary combustion zone. A baffle recirculation zone prevents overheating of the walls. Dilution air is provided downstream of the primary zone for temperature dilution of the gases and to inhibit further formation of nitrogen oxides.