Abstract: A rotatable turbine frame includes annular outer and inner bands having a plurality of circumferentially spaced apart struts extending therebetween. An annular drive shaft is fixedly joined to the inner band for transmitting output torque therefrom, and the struts are backwardly radially inclined relative to the direction of rotation of the frame so that gas flow between the struts tends to straighten the inclined struts to effect a compressive load component therein.

Abstract: A cast article having a reinforced structural composite core is disclosed. The cast article includes a structural element which is embedded in the otherwise cast metal article. The structural element is comprised of a metal matrix composite structural core. It includes a plurality of reinforcing fibers within a metal matrix. The fibers are generally a non-metallic material such as a ceramic which degrade at a temperature below the melting temperature of the cast metal comprising the article. The metal matrix composite structural core is encased with a sheath. The sheath, attached to and completely surrounding the core, is made of the same metal as the cast metal article. In a preferred embodiment, the article is a titanium alloy strut for a gas turbine engine.

Abstract: A method of assembling a turbine frame assembly for use in a gas turbine engine includes the step of disposing the outer casing in a generally concentric relationship with an annular inner hub and a plurality of circumferentially spaced apart and radially extending struts attached to the hub. The method further includes inserting at least one cam alignment tool through one of a plurality of casing mount holes and into a corresponding one of a plurality of clevis base mount holes, with the clevis being attached to an outer end of a first one of the struts. The cam alignment tool is rotated to cam the strut relative to the casing to align the casing mount holes with the clevis mount holes. The clevis base is then fastened to the outer casing and the cam alignment tool is removed.

Abstract: An improved blade containment structure including a projectile shield having a braided ballistic fabric is disclosed. The braided fabric includes ballistic strands arranged in a preferred orientation and is effective for increasing the ability of the fabric to contain projectiles and absorb energy therefrom. The braided ballistic fabric provides substantial improvement in performance over conventional woven ballistic fabrics.

Abstract: A flap and seal positioning apparatus for centering adjacent longitudinally extending seals and flaps in the divergent section of an aircraft gas turbine engine axisymmetric vectoring nozzle and for equidistantly spacing the flaps during vectoring. The positioning apparatus provides a plurality of pivotably interlinked levers, preferably linked by universal joints, rotatably mounted on and about centering posts extending radially outward from the backs of the divergent flaps and seals. In one embodiment the flap levers have separate arms that are rotatably linked by a double hinge joint at their common centering post such that the arms rotate freely about an axis parallel to the divergent flap. Another embodiment provides the seal lever with a means to translate freely along its axis of rotation coincident with the centering post upon which it is mounted and has a two part centering post with an inner piston that slides within an outer cylinder.

Abstract: An apparatus for securing a bracket to a fixed member, the fixed member and the bracket each having at least one opening therethrough, where the apparatus includes a bolt having a threaded body and a head at a first end of the threaded body, where the bolt head abuts against a first surface of the fixed member, a nut threadably engaged to a second end of the threaded body, and a spacer positioned between the fixed member and the nut having an opening therethrough, the spacer having a flared portion at a first end which engages the bracket opening, wherein the threaded body of the bolt is positioned through the bracket opening, the spacer opening and the fixed member opening and secured together by the nut.

Abstract: A blade containment system is disclosed which includes an annular casing positioned radially outward of the blades and in surrounding relationship therewith, the annular casing including a plurality of composite tapes bonded to the outer or inner radial surfaces thereof, wherein the composite tapes limit the propagation of cracks and holes formed in the annular casing.

Abstract: An article having a substrate is protected by a thermal barrier coating system. An interfacial layer contacts the upper surface of the substrate. The interfacial layer may comprise a bond coat only, or a bond coat and an overlay coat. The interfacial layer has on its upper surface a preselected, controllable pattern of three-dimensional features, such as grooves in a parallel array or in two angularly offset arrays. The features are formed by an ablation process using an ultraviolet laser such as an excimer laser. A ceramic thermal barrier coating is deposited over the pattern of features on the upper surface of the interfacial layer.

Abstract: A method of image processing is provided for generating an image of an object in a computer X-ray tomography apparatus having an X-ray source and a detector. The method desirably permits relatively coarse spacing between adjacent detector views and correspondingly lowers exposure to X-ray radiation while maintaining a high resolution image. The method includes the step of acquiring actual detector data for multiple views of the object. After actual detector data is acquired for adjacent views of the object, the actual detector data from these adjacent views is interpolated to obtain virtual detector data between the adjacent views as though a virtual detector had been placed therebetween. The actual detector data and the resultant virtual detector data is then mapped into Radon space. The process is repeated until Radon space is sufficiently filled with actual detector data and virtual detector data to permit image reconstruction.

Abstract: A wall adapted for use in a gas turbine engine between a first and a hotter second fluid includes a first side over which is flowable the first fluid, and an opposite second side over which is flowable the second fluid. An elongate notch includes a forward surface extending inwardly from the second side and is disposed in flow communication with a plurality of longitudinally spaced apart holes extending inwardly from the first side. The notch also includes an aft surface extending from the forward surface to the wall second side which is inclined at an acute discharge angle relative to the second side. The holes are disposed at an acute discharge angle relative to the second side for discharging the first fluid into the notch, and the notch discharge angle is smaller than the hole discharge angle for discharging the first fluid from the notch along the second side.

Abstract: A method and apparatus for detecting defects in a structure formed of a honeycomb matrix bonded to a support surface including providing a probe body including means defining a fluid passage forming a supply port to an exterior surface of the probe body; connecting a pressurized fluid source to the fluid passage at a location distal from the supply port; placing the supply port in close proximity to a cell of the honeycomb matrix; supplying fluid from the compressed fluid source to the cell via the fluid passage; and monitoring a fluid pressure produced at a portion of the honeycomb matrix adjacent to the supply port to detect disbonds between the honeycomb matrix and support surface.

Abstract: A double ender powerplant including a first engine having a compressor for producing a downstream axial flow, a combustor, a turbine coupled to the compressor through a shaft, and means for attaching a load coupled to the shaft adjacent and downstream from the turbine; a second engine having a compressor for producing a downstream axial flow, a combustor, a turbine coupled to the compressor through a shaft, and means for attaching a load coupled to the shaft adjacent and upstream from the compressor; and, a generator coupled to each of the attachment means of the first and second engines.

Abstract: Evaporated ceramic coatings are prepared by furnishing an ingot of a ceramic material, treating the ingot to reduce sources of gas within the ingot, and evaporating the ceramic material in the ingot by melting the surface of the ingot with an intense heat source. The evaporated ceramic is deposited upon a substrate as the ceramic coating. The reduced gas content of the ingot decreases the incidence of spitting and eruptions from the molten surface of the ingot, thereby improving the quality of the deposited coating, and facilitating increases in evaporation rates and coatings process production rates.

Abstract: An augmentor screech suppressor for a gas turbine engine includes a screech suppressor liner mounted on a screech housing and an actuator for translating the screech suppressor liner axially forward and aft, with the actuator located outside the outer duct of the engine. In a preferred embodiment in a variable cycle gas turbine engine, a variable area bypass injector (VABI) valve with a circumferentially conical surface slopes into the screech suppressor liner surface and inner and outer crank arms transfer linear motion from the actuator through the outer duct wall, cooperating with idler arms to translate the screech suppressor housing, and thus the VABI valve and screech suppressor linear, axially between open and closed valve position.

Abstract: A coupling for joining a pair of conduits, one of the conduits having a flared end and the other of the conduits having a circumferential flange with a surface conforming generally for mating with the flared end of the one of the conduits. The coupling comprises a first annular ring positioned about the one of the conduits and having an inner diameter less than an outer diameter of the flared end and a radially inner surface adapted for engaging an outer surface of the flared end. A second annular ring is positioned about the other of the conduits and has an inner diameter less than an outer diameter of the circumferential flange and has a surface adapted for engaging a surface of the flange. A split ring circumscribes the first and second rings and has a radially inner, generally V-shaped groove for simultaneously overlapping both the first and second rings.

Abstract: Fatigue crack growth-resistant articles are made from powder metal or cast and wrought gamma prime precipitation strengthened nickel-base superalloy material, wherein a relatively high predetermined minimum strain rate, .epsilon..sub.min, is employed during hot working at or near the alloy's recrystallization temperature; or alternatively a relatively high strain level, .epsilon..sub.min, is employed during cold or warm working at temperatures below the alloy's recrystallization temperature. The worked articles are characterized by a uniform fine grain size, and grains which coarsen uniformly after heating at the supersolvus solutioning temperature, thereby alleviating non-uniform grain growth within the material.

Abstract: An article of manufacture has as its basic structure a piece of a titanium aluminide, such as gamma (TiAl) or alpha-2 (Ti3Al), desirably in the shape of an aircraft gas turbine component. A thermal barrier coating system overlies at least a portion of the surface of the piece of titanium aluminide. The thermal barrier coating system includes a metallic bond coat layer, preferably in the form of a layer of a nickel-based alloy no more than about 0.005 inches thick, that contacts the piece of titanium aluminide, and a ceramic thermal barrier coating layer, preferably a stabilized zirconia such as yttria-stabilized zirconia, overlying the bond coat.

Abstract: A vacuum centrifugally cast combustion liner suitable for use in a gas turbine engine operating at temperatures ranging from ambient up to about 1700.degree. F. is provided. The combustion liner is formed by centrifugally vacuum casting a precipitation hardened nickel-based superalloy having controlled, low amounts of aluminum and titanium. The combustion liner is characterized by a homogeneous grain structure having enhanced strength and creep resistance particularly at elevated temperatures. In addition, the preferred elemental composition, particularly the relatively small amounts of aluminum and titanium, enhance the weldability and overall manufacturability of the combustion liner.

Abstract: A FLADE aircraft gas turbine engine having a FLADE duct circumscribing a preferably variable cycle inner gas turbine engine and having a FLADE fan disposed in the FLADE duct and radially outward of and drivenly connected to a first fan disposed in a first fan duct of the inner engine. The annular inlet of the first fan duct is sized to receive essentially the full mass airflow of the engine at full power conditions with the annular FLADE duct inlet essentially closed off. The engine is further designed and operable to fully open the inlet of the flade duct at predetermined part power flight conditions and essentially close it at full power conditions such as take off. An infra-red (IR) radiation shielding apparatus is disposed in the exhaust duct of the engine to block infra-red radiation emitting hot metal surfaces of the engine from view through an exhaust outlet of the exhaust duct and is cooled by air flow from the FLADE duct.

Abstract: A combustor apparatus is provided for a gas turbine engine including a circumferential ring of injectors. A fuel manifold provides a source of fuel for the injectors. The combustor apparatus includes a plurality of first fuel flow paths between the manifold and all of the injectors. Fuel is provided to all of the injectors via these first flow paths. At least one second fuel flow path including an electronically switchable valve is coupled between the manifold and a selected one of the injectors to provide additional fuel thereto at certain times when special engine operating conditions, such as demand for initial ignition, crossfire and altitude relight are sensed.