Abstract: A blade containment system for turbomachinery includes an annular casing having an interior surface with an abrasive surface texture that is capable of dulling sharp comers and edges of impacting fan blades so as to reduce the ability of the fan blade to pierce the containment casing. The textured surface can be produced by either a plurality of protuberances attached thereto or a plurality of sharp dimples formed therein. The protuberances can be in the form of sawtooth steps, sharp spikes or pieces of a hard material impregnated in the textured surface. In one preferred embodiment, the textured surface is formed on a plurality of tiles secured to the interior surface of the containment casing.

Abstract: A high flow interstage air extraction system for a gas turbine engine includes a 360 degree annular slot formed in a compressor stator casing by a first wall and a second wall. A plurality of baffle plates extend from the second wall to eliminate circumferential airflow. A plurality of stator vane platforms form at least a portion of the first wall. The annular slot results in large amounts of interstage compressor air being extracted from the compressor without adding length to the compressor and the engine.

Abstract: A turbine nozzle assembly includes a plurality of nozzle segments and a nozzle support for supporting the nozzle segments. Each nozzle segment includes an outer band, an inner band and at least two vanes disposed between the outer and inner bands. A retention flange extends radially inwardly from the inner band and has a first hole formed therein. The nozzle support includes a recess formed therein and a mounting flange extending therefrom. The mounting flange is disposed in contact with the retention flange and has a second hole formed therein. A pin is disposed in the first and second holes to position the flanges with respect to one another. A pin retainer is disposed in the recess and has a holding flange for retaining the pin in place. The nozzle support includes a substantially conical portion and an air seal integrally formed thereto.

Abstract: An interstage seal includes a seal pad attached to a backing strip. A plurality of tab springs are fixedly attached to the outboard side of the strip for engaging an inner band of the supporting stator sector.

Abstract: A fan blade includes a metal airfoil having first and second opposite sides extending radially between a root and a tip, and axially between a leading edge and a trailing edge. The airfoil further includes a pocket disposed in the first side having an elastomeric filler bonded therein. A panel is bonded to the filler along the pocket for allowing differential movement therebetween for damping vibratory response of the airfoil.

Abstract: A rotor blade includes an airfoil, an integral platform, and a dovetail integrally joined to the platform. The dovetail includes a neck extending between a pair of dovetail lobes configured to engage a complementary slot in a rotor disk. The dovetail includes an undercut extending between an outer face of the dovetail lobes and the neck for introducing a stress concentration thereat. The stress concentration relieves stress at the outer face at the expense of the neck for increasing the high cycle fatigue life of the blade.

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 brush seal includes a back plate against which an annular pack of bristles is disposed. A plurality of circumferentially overlapping shingle dampers engage in abutting contact the bristle pack for providing damping.

Abstract: A variable stator vane includes an airfoil having a threaded stem, a lever having a mounting hole receiving the stem, and a nut threadingly engaging the stem to retain the lever on the airfoil. A clearance is provided between the seat and lever during alignment therebetween to provide sufficient thread overlap between the nut and stem to permit engagement therebetween, with insufficient thread overlap being provided during misalignment to prevent threaded engagement therebetween.

Abstract: A gas turbine engine fan blade includes an airfoil and dovetail having an integral aluminum core and a fatigue resistant reinforcing sheath.

Abstract: An actuation system for variable stator vanes pivotally mounted in a casing includes a plurality of levers joined to the respective vanes. An actuation ring coaxially surrounds the casing adjacent to the levers. A plurality of circumferentially spaced apart ring guides are joined to the casing for guiding circumferential rotation of the ring. Respective slip joints are provided between each of the levers and the actuation ring for varying pivot length of the levers as the ring is rotated for effecting nonlinear vane actuation.

Abstract: An inter-rotor bearing assembly includes a first annular member having a circumferential inner surface and a second annular member having a circumferential outer surface. The outer surface is concentric to and disposed radially inward of the inner surface and a bearing is disposed between the surfaces. The bearing has an outer race fixedly attached to the first annular member along the inner surface, an inner race fixedly attached to the second annular member along the outer surface, and rolling elements disposed between the races. A low density high circumferential strength support ring is fixedly attached to the first annular member disposed concentrically outside of the inner race and is preferably made of a titanium matrix composite. The rolling elements may be cylindrical rollers having cylindrical rolling surfaces. The support ring may be fixedly attached around or integral with the first annular member.

Abstract: A method for quality assurance of a laser process and more particularly a laser shock peening process that uses a test coupon having a deflection formed by a laser firing. The test coupon is from a metallic strip having opposite first and second sides that generally define a plane of the strip and the strip includes a laser shock peened patch of the strip that has first and second laser shock peened surfaces on the first and second sides, respectively, first and second laser shocked regions having deep compressive residual stresses imparted by the laser shock peening extending into the strip from the first and second laser shock peened surfaces, respectively, and a deflection of a portion of the strip from a position of the portion before the laser shock peening. The deflection is formed by the laser shock peening such that at least a part and preferably substantially all of the deflection lies in the plane of the strip and the test coupon preferably includes an indicating means to indicate the deflection.

Abstract: A fluid cooled article having a protective coating on a surface, for example an air cooled gas turbine engine article having a Thermal Barrier Coating, includes through an article wall a fluid cooling passage, and typically a plurality of passages, having openings sized to maintain desired fluid flow, unobstructed by coating within the passage at an exit opening. The passage has a first or inlet opening, which establishes the amount of fluid flow through the passage, and a second opening through which the flow exits the passage through a wall surface on which the coating is deposited.

Abstract: A method of laser shock peening a gas turbine engine object continuously firing a stationary laser beam, which repeatably pulses between relatively constant periods, on a portion of the object with a low power laser beam, on the order of 3-10 joules, to vaporize material on the surface of a portion of a part made of a strong hard metal, such as a titanium alloy. Laser pulses around small laser beam spots, on the order of 1 mm in diameter, are used to vaporize material on the surface of the portion of the object with the pulses around laser beam spots formed by the laser beam on the surface and form a region having deep compressive residual stresses extending into the object from the laser shock peened surface. Flowing a curtain of water over the surface upon which the laser beam is firing while preferably moving the object until the laser shock peened surface is completely covered by laser beam spots at least once.

Abstract: A system and method for providing clean cooling air to a hot portion of a gas turbine engine is disclosed, where the engine includes a compressor. The system includes a turbocompressor (66) having a compressor section and a turbine section, wherein the compressor and turbine sections each have an inlet and an outlet. The system further includes a heat exchanger (64) having a first inlet and a first outlet for a first fluid flow providing cooling to the heat exchanger, the first inlet being in fluid communication with a low temperature fluid. The heat exchanger (64) also has a second inlet and a second outlet for a second air flow receiving cooling from the heat exchanger, the second inlet being in fluid communication with high temperature air from the engine compressor and the second outlet being in fluid communication with the inlet of the compressor section of the turbocompressor.

Abstract: A cospander for extending the high efficiency range of a turbine engine is described. A cospander, in one aspect, is a turbomachinery device including at least one stage wherein stator vane and rotor blade rows are continuously variable to an extent that each stage can be operated in compression, expansion, or null modes depending on the blade and vane angles at any specific operating point. Such a device placed ahead or within a typical compressor has the effect of reducing, increasing, or maintaining the through flow of the primary working fluid. Such flow variation control can be used to achieve the desired overall turbomachinery thermal efficiency improvements over a wider operating range than is otherwise possible. In one specific embodiment, for example, the cospander includes a variable stator vane and a variable pitch rotor blade in series flow relationship.

Abstract: An eddy current device for inspecting a component, such as a closed surface area of a gas turbine engine or the like, includes an eddy current array circuit having an active face for positioning on a surface portion of the component during an inspection operation and backing on a surface of the eddy current array circuit opposite to the active face. The eddy current array circuit and backing are disposed over the operating face and expandable sides of an extendible pin. The extendible pin has a slot formed therein with interior side edges which narrow toward the operating face of the pin at a predetermined slope. The expanding pin is positioned to cause the angled sides to mate while engaging the interior angled sides of the round or shaped hole to cause the exterior sides of the expandable pin to expand outwardly a greater distance as the pin is pushed deeper into the hole. This causes the eddy current circuit to conform with the shape of the surface to be inspected.

Abstract: A fuel manifold staging valve is provided for use with aircraft engines. A first set of fuel nozzles is associated with a primary manifold, and a second set of fuel nozzles is associated with a secondary manifold. The valve opens on the basis of a constant ratio of fuel flow divided by compressor discharge pressure. The valve detects fuel flow by sensing the pressure drop across the fuel nozzles. This pressure drop is biased by a spring and compared to the compressor discharge pressure. When the ratio is correct for the geometry of the valve, the valve begins to open, allowing fuel to flow to the secondary manifold and associated fuel nozzles.

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.