Abstract: A double annular combustor having concentrically disposed inner and outer annular combustors including an inner dome having an inner portion and an outer portion, an outer dome having an inner portion and an outer portion, wherein the outer dome inner portion is connected to the inner dome outer portion, and a substantially annular centerbody disposed between the inner dome and the outer dome. The centerbody includes a plurality of structurally independent arcuate segments, wherein each centerbody segment is retained in position via an interference fit between a first flange of such centerbody extending downstream and a hook in the inner dome outer portion and/or via a clamping fit of a second flange of the centerbody extending upstream to a flange of the inner dome outer portion.

Abstract: A turbine airfoil includes a plurality of internal ribs joined to laterally opposite first and second sidewalls to define a pair of serpentine cooling circuits therein. A span rib extends longitudinally between a root and tip of the airfoil. And, slant ribs extend outwardly from opposite sides of the span rib to define respective portions of the serpentine circuits.

Abstract: A turbine airfoil includes a plurality of internal ribs joined to laterally opposite first and second sidewalls to define a serpentine cooling circuit therein. A span rib extends longitudinally between a root and tip of the airfoil. And, a slant rib extends obliquely to the span rib to define respective portions of the serpentine circuit longitudinally above and below the slant rib.

Abstract: A transfer tube system includes a transfer tube, a spring, a pair of opposing seats, and a pair of end assemblies that provide independent axial spring loading of the opposing seats. The spring loading assures continuous sealing contact regardless of dynamic loading, dimensional stack-up, or geometry change resulting from interfaced wear. The transfer tube end assemblies include a spherical or conical seat for mating with the transfer tube. Particularly, the transfer tube has spherical ends for seating in the transfer tube end assembly seats. The conical/spherical seats permit angular motion of interfacing components without lift off and therefore assures minimal leakage.

Abstract: A diagnostic trend analysis method is used to analyze engine trend data for aircraft engines. Appropriate trend parameters are calculated from raw trend data and wild points associated with the calculated trend parameters are eliminated. Abnormal shifts and changes are detected at the most recent point for each trend parameter. The abnormal shifts and changes in each trend parameter are then evaluated. The evaluation is used to filter out spurious symptoms and provide accurate maintenance recommendations for real engine trend shifts.

Abstract: A fan blade includes a metal airfoil having first and second opposite sides extending radially between a root and tip, and axially between a leading edge and a trailing edge. The airfoil further includes a plurality of pockets disposed in the first side and separated by corresponding ribs. A filler is bonded in the pocket, and is coextensive with the airfoil first side. Radial and diagonal ribs respectively intersect solely each other for selectively increasing torsional and bending stiffness to increase frequency margin between adjacent torsional and bending resonant modes of vibration.

Abstract: A racking system exhibiting controlled compound movement is disclosed. The racking system includes a bracket adapted for engagement to a structural support and a translational tray assembly supported by the bracket for linear and rotational movement relative to the bracket. The system also includes a first dampening member associated with the translational tray assembly for dampening the linear movement of the translational tray assembly relative to the bracket and a second dampening member associated with the translational tray assembly for dampening the rotational movement of the translational tray assembly relative to the bracket. The first and second dampening members ensure smooth, controlled motion as the translational tray assembly is rotationally and linearly moved.

Abstract: An aesthetically and functionally improved shroud for covering a grinder device while improving the consumer shopping experience. The shroud is formed of a faceplate with a first opening for receiving and directing items, such as coffee beans, to be ground to a grinder device and a second opening positioned to allow a consumer to place a bag under the opening in order to collect the ground coffee from the grinder. A funnel device is used in connection with the first opening to assist in directing the items to be ground into the grinder.

Abstract: A static seal includes first and second spaced apart walls having a gap therebetween for channeling a pressurized fluid. The first wall includes a recessed seat facing the second wall defined by spaced apart first and second faces joined together at a base. A seal insert is loosely disposed in the seat and is trapped therein by the first and second faces. The first and second faces are shorter than the insert to project a top of the insert above the seat and below the second wall for initially promoting flow of the fluid over the insert top to deploy the insert in abutting contact with both the second face and the second wall to seal the gap.

Abstract: A gas turbine engine carburetor includes a fuel injector having a plurality of circumferentially spaced apart fuel outlets. A plurality of air swirlers (24) are circumferentially spaced apart around the fuel injector (22), with each swirler having a fuel inlet (24b) disposed in flow communication with a respective one of the fuel outlets for receiving fuel therefrom. Each swirler includes a plurality of swirl vanes to swirl air for mixing with the fuel from the fuel inlets. The multi-swirler carburetor having a common fuel injector increases injection points for reducing NO.sub.x emissions.

Abstract: A gas turbine engine rotor blade includes an airfoil having a concave side wall and a convex side wall joined together at leading and trailing edges. Concave and convex tip walls extend from adjacent the leading edge along the respective concave and convex side walls to adjacent the trailing edge and are spaced apart to define a tip cavity therebetween. A hole or channel is disposed in a trailing edge tip region connecting the tip cavity to the trailing edge for channeling cooling fluid through the trailing edge tip region.

Abstract: An aircraft engine mount includes a mounting platform fixedly joinable to an aircraft pylon, and a cooperating mounting ring fixedly joinable to an aircraft engine. The platform includes a pair of spaced apart lugs defining therebetween a failsafe slot. The mounting ring includes an inner flange fixedly joinable to the engine, and an outer flange extending from the inner flange into the failsafe slot. A pair of side links are pivotally joined to the outer flange and at least one of the lugs to carry loads therebetween. A failsafe pin extends across the failsafe slot and is fixedly joined to the lugs. A clearance hole is provided in the outer flange for receiving the failsafe pin and providing a failsafe alternate loadpath between the mounting ring and platform upon failure of the links to carry loads.

Abstract: An aircraft engine mount includes a mounting platform fixedly joinable to an aircraft pylon, and a cooperating mounting ring fixedly joinable to an aircraft engine. The platform includes four lugs arranged in forward and aft pairs. Four links are arranged in forward and aft pairs pivotally joined at opposite ends thereof to respective ones of the four lugs and to the mounting ring. The four links are symmetrically arranged both circumferentially and axially to carry both thrust loads and in-plane vertical and side loads between the mounting ring and mounting platform with failsafe redundancy.

Abstract: A swirler is provided for mixing air from a compressor and fuel from a fuel injector for discharge into a dome of a gas turbine engine combustor. The swirler includes a tubular ferrule for coaxially receiving the fuel injector. A plurality of circumferentially spaced apart swirl vanes are fixedly joined coaxially with the ferrule. An outlet tube is fixedly joined coaxially with the swirl vanes in flow communication therewith for receiving air from the swirlers and fuel from the fuel injector. An annular collar is fixedly joined around the outlet tube and has a convex spherical outer surface. An annular mounting flange for mounting the swirler to the combustor dome has a concave spherical inner surface disposed coaxially around the collar outer surface in a sliding fit therewith to define a ball joint for allowing relative rotation therebetween for self-aligning the fuel injector with the swirler.

Abstract: A fan blade includes a metal airfoil having first and second opposite sides extending longitudinally between a root and a tip, and laterally between a leading edge and a trailing edge. The airfoil further includes a plurality of fine striations spaced laterally apart between the leading and trailing edges in the airfoil first side, and extending longitudinally between the root and the tip. A viscoelastic filler is bonded in the striations for damping torsional vibrations of the airfoil.

Abstract: A gas turbine engine including air cooling and compressing means configured so that, in one embodiment, cool air from the cooling and compressing means is supplied to the combustor for cooling the combustor and then, after cooling at least a portion of the combustor, for mixing with fuel in the fuel injector, is described. In one form, the combustor includes a flowpath in flow communication with cool air supplied by the cooling and compressing means. The air flows through the flowpath from an aft portion to an outlet located at the fuel injector. The cooling air, after having cooled walls of the combustion chamber, mixes with fuel in the fuel injector. Mixing the high pressure air from the cooling and compressing means with the fuel in the fuel injector facilitates dispersion of fuel from the fuel injector into the combustion chamber, and also aids in increasing the fuel/air energy shear gradients.

Abstract: A superalloy component having a substrate article of a superalloy, and a strengthenable coating covering at least a portion of the substrate article. The coating exhibits thermal barrier characteristics and when cured formed a ceramic material. The component may further include a fiber layer between the substrate article and the coating, and the coating may be reinforced with fiber and the ceramic may be imbedded with inorganic particles. The coating is a foam obtained by reacting an admixture of (a) a silane polymer, (b) a silicone-vinyl resin and (c) a catalyst. The article is preferably a turbine blade. The component is useful as a gas turbine element.

Abstract: A tube coupling assembly has independent primary and secondary sealing elements. The coupling assembly includes first and second coupling members which define a fluid passage therethrough. The coupling members are arranged relative to one another so as to define a contact seal therebetween. An annular fluid path extends between the contact seal and the fluid passage, and a seal element, such as an O-ring is disposed in said fluid path. Accordingly, the seal element is always in contact with, and thus cooled by, the fluid in the passage. The coupling assembly also includes a coupling nut disposed over a portion of one of the coupling members and threadingly engaging the other coupling member to retain the coupling members together. A plurality of resilient fingers is provided on one of the coupling members, and a plurality of grooves is formed in the coupling nut. The fingers are received in the grooves so as to oppose rotational displacement of the coupling nut from its assembled position.

Abstract: A nozzle for dispensing fluids with suspended solid particulates without experiencing permanent partial or total clogging is provided. The nozzle is made from a elastomeric material and has a dome-shaped tip. The dome-shaped tip has a slit that provides an elongated orifice which generates a fan-type spray pattern while allowing solid particulates to pass through the nozzle without permanent clogging. The slit is normally maintained closed at rest and provides precompression and shut-off functions. Several versions of the nozzle are described, such as a one-piece nozzle and a nozzle insert. Additionally, the nozzle can be attached to a manually actuated pump device and be used as a spray delivery system.