Abstract: A real time variable laser beam spinner, wherein a manual or programmable actuator angularly displaces a mirror or optical flat during rotation in order to follow the instantaneous spin diameter requirements associated with a workpiece, whereby a variable effective spin diameter of the beam results without interrupting the work process.

Abstract: An extension is provided on an end of an article having internal passageways and having a directionally oriented microstructure by using the article end as a growth seed in a molten material compatible with material from which the article end is made. The extension is directionally solidified as integral with and as an extension of the article end and with a microstructure compatible with that of the article end.

Abstract: A gas turbine engine flow mixer includes at least one chute having first and second spaced apart sidewalls joined together at a leading edge, with the sidewalls having first and second trailing edges defining therebetween a chute outlet. The first trailing edge is spaced longitudinally downstream from the second trailing edge for defining a septum in the first sidewall extending downstream from the second trailing edge. The septum includes a plurality of noise attenuating apertures.

Abstract: A double annular combustor having concentrically disposed inner and outer annular combustors is provided with inner and outer domes. A one-piece cowl is provided upstream of the inner and outer domes in order to form a high pressure region. The one-piece cowl has an inner annular portion, an outer annular portion, and a radial middle portion connecting the inner and outer annular portions. The inner and outer annular portions include scalloped areas therein to facilitate insertion and removal of fuel tubes and nozzles. The cowl middle portion includes a shield to isolate the scalloped areas and the fuel tube from the high pressure region, thereby preventing leakage of air flow and consequential pressure loss from the high pressure region.

Abstract: In a gas turbine engine, fuel is supplied to a fuel metering valve which is connected to a shutoff valve. The shutoff valve supplies fuel to a manifold. Fuel flow between the manifold and main fuel nozzles is controlled by fuel staging valves while the pilot nozzle is connected directly to the manifold by a fuel line which may include an orifice. The orifice is designed to match the flow in the pilot nozzle with the flow in main nozzles when the fuel staging valve is on.

Abstract: An improved method of adaptive machining is disclosed which affords automatic blending between a machined surface and a complex variable contour forged surface. An adaptive postprocessor generates an adaptive NC part program from a conventional APT file which has the capability to modify the cutter tool path in real time during the machining cycle based on limited surface measurement data. Variable measurement data taken from each workpiece generates a unique toolpath adapted specifically to the contour of that workpiece being processed, obviating the subsequent need for time consuming manual grinding and smoothing operations between machined and forged surfaces.

Abstract: A disk attachment system for a high pressure turbine section of a gas turbine engine, the high pressure turbine section including a first stage disk and a second stage disk. The first stage disk includes a first conical aft shaft extending rearwardly from a bore of the first state disk and the second stage disk has a second conical aft shaft extending rearwardly from a bore of the second stage disk, and the second aft shaft is attached to the first aft shaft at a splined connection. The second aft shaft includes an arm having a mate face and pilot for centering the second stage disk relative to the first stage disk. Rotational energy from the second stage disk is transmitted through the first aft shaft to the first stage disk.

Abstract: A fluid channeling system includes a fluid ejector, a heat exchanger, and a fluid pump disposed in series flow communication The ejector includes a primary inlet for receiving a primary fluid, and a secondary inlet for receiving a secondary fluid which is mixed with the primary fluid and discharged therefrom as ejector discharge. Heat is removed from the ejector discharge in the heat exchanger, and the heat exchanger discharge is compressed in the fluid pump and channeled to the ejector secondary inlet as the secondary fluid In an exemplary embodiment, the temperature of the primary fluid is greater than the maximum operating temperature of a fluid motor powering the fluid pump using a portion of the ejector discharge, with the secondary fluid being mixed with the primary fluid so that the ejector discharge temperature is equal to about the maximum operating temperature of the fluid motor.

Abstract: A variable area bypass injector (VABI) seal for a variable cycle gas turbine engine includes a circumferentially segmented seal attached to the diffuser. Each seal segment is spring loaded to allow for different axial movement between circumferentially adjacent segments, and has a seat portion complimentary to a VABI valve conical surface for sealingly engaging the VABI valve when the VABI valve is in closed position. Additionally, the seal segments are shaped with a low aerodynamic profile and cooperate with the VABI valve conical surface, when the valve is in an open position, to provide an annular conic channel that keeps the bypass flow attached to the VABI valve and core flowpath walls as it is injected into the core gas stream.

Abstract: 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 chambers installed within the drain mast assembly with each of the chambers coupled in liquid receiving relationship with a respective one of the liquid drain lines. Each of the chambers collect drain liquid from a respective one of the drain lines. A valve extends from each chamber for selectively draining the collected liquid from each of the chambers for identifying drain lines having relatively high drain-rates. Each of the chambers is separately removable from the drain mast assembly in one form or all chambers may be simultaneously removed in another form of the invention. Each chamber further includes a transparent view window for visually determining a volume of liquid collected by the chamber.

Abstract: A bellows sealed ball joint comprising an inner spherical shell, a bellows and an outer spherical shell. The inner spherical shell comprises a plurality of elongated non-spherical areas or indentations which receive a plurality of locking surfaces on the outer spherical shell. The inner and outer spherical shells can then be rotated with respect to each other a predetermined distance until the spherical locking surfaces on the outer spherical shell operatively engage concentric spherical locking surfaces on the inner spherical shell. Once the locking surfaces of the inner and outer spherical shells are in operative engagement, the bellows ball joint can pivot freely without becoming disconnected. A final joining seal is then made at each end of the bellows to prevent the spherical sections from unlocking and to provide a hermetic seal. In an alternate embodiment, the inner spherical shell is shown as having elongated slots in place of the non-spherical areas.

Abstract: A double annular combustor having concentrically disposed inner and outer annular combustors is provided with inner and outer dome plates. Each dome plate has an inner portion and an outer portion. A cowl structure having an inner portion, an outer portion and a middle portion is also provided. The cowl outer portion is connected to the outer dome plate outer portion, the cowl inner portion is connected to the inner dome plate inner portion, and the cowl middle portion is connected to the outer dome plate inner portion and the inner dome plate outer portion. at an outer end, an inner end, and a middle portion. Additionally, the inner and outer annular combustors may lie in distinct radial planes, whereby the dome plate of the downstream annular combustor includes a section extending upstream to the cowl middle portion.

Abstract: A method and system for machining a contoured surface of a part, such as a vane of a vane segment of a nozzle ring in a gas turbine engine. A plurality of original data points from the original surface of the vane are sensed. The system comprises an algorithm for creating a matrix of data and for generating a revised contour profile corresponding to the cross-sectioned contour of the vane for points which lie in a common plane. The original contour may have missing sections in its profile or may have areas where brazing material has been applied to the vane. The revised contour profile is adjusted in accordance with certain predefined parameters. The revised contour profile is also adjusted so that all of its points lie on or inside the perimeter shape defined by the original data points. All of the revised contour profiles associated with each cross-section of the vane is compiled to generate one machining contour.

Abstract: A combustor includes a dome assembly having radially outer and inner liners joined thereto and defining therebetween a combustion zone. The dome assembly includes at least one annular dome having a pair of axially extending first flanges between which are disposed a plurality of circumferentially spaced apart carburetors for discharging a fuel/air mixture into the combustion zone for generating combustion gases. An annular heat shield includes a pair of axially extending legs integrally joined to a radially extending face in a generally U-shaped configuration, with the face including a plurality of circumferentially spaced apart ports disposed concentrically with perspective ones of the carburetors for allowing the fuel/air mixture to be discharged therefrom through the heat shield.

Abstract: An apparatus and method for monitoring material removal from a workpiece by a beam of energy during a material processing operation are disclosed. A detector is positioned for sensing optical emissions from the workpiece caused by removal of material when an energy beam pulse is incident upon the surface of the workpiece. A computing circuit, algorithm or artificial neural network is provided for determining a quantity of material removed from the sensed optical emissions in real-time during the material processing operation. Analysis of the optical emission pulses caused by the material removal provides an indication of the efficiency of the material processing system and provides feedback for manual or automatic adjustment of material processing parameters during the material processing operation.

Abstract: 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 is enclosed so that effectively all of the cooling air entering the bay leaves the bay through the engine exhaust and is not dumped overboard, thereby adding to the effective thrust of the engine. An engine oil and generator oil heat exchanger is positioned in the cooling air duct into the bay so that the same air which cools the bay also cools engine and generator oil. The oil heat exchanger includes directional louvers which regulate and keep to a minimum the amount of cooling air and direct cooling air forwardly in the bay so that the entire bay area is cooled, and which can be shut as a fire control measure.

Abstract: A frame for a gas turbine engine includes an outer casing, an inner hub, and a plurality of circumferentially spaced apart struts extending radially therebetween. Each strut includes first and second sidewalls defining a radial passage therein, and an elongate damper is disposed in respective ones of the strut passages. Each damper is disposed in an interference fit laterally between the first and second sidewalls for maintaining contact therewith for effecting sliding friction to dampen vibration of the struts.

Abstract: 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 face seal with respect to a rotating sealing surface and radial growth of the seal member with respect to the housing. A clearance control ring means can be included to reduce and maintain radial clearance between the face seal member and a housing surface. The face seal member may be pressurized radially outwardly, and can include improved vent channel and vent passage means.

Abstract: The present invention provides a method and apparatus including a rotor mountable fixture for guiding a cutting tool powered by a hand held air motor to machine a gas turbine engine rotor without removing the rotor from its mountings in the engine. In one particular embodiment the fixture includes a root having the same contour as a blade root slot of a rotor, a base having a platform attached to the root, and a machining guide in the form of a bushing restrained in a guide slot operable to receive and guide a hand held air motor powered cutting tool for machining the rotor. The present invention provides an accurate means to machine a gas turbine engine rotor without removing the rotor from its mounting. In one particular embodiment a method for machining the rotor in the field is provided using a hand held air motor to power a machining tool to cut a blade damper pocket in the dovetail slot of a pressure compressor rotor.

Abstract: A rotor blade retention assembly includes a rotor blade having a dovetail mounted in a complementary axial dovetail groove in a rotor disk. A primary blade retainer retains the blade in the groove against axial movement in a first direction. A secondary blade retainer retains the blade in the groove after a predetermined travel of the blade in the first direction upon failure of the primary blade retainer to restrain the predetermined travel.