Patents Represented by Attorney Jerome C. Squillaro
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Patent number: 5370499Abstract: A turbine airfoil has a mesh cooling hole arrangement which includes first and second pluralities of cooling holes extending between internal and external surfaces of an airfoil side wall at least at a pressure side and extending from an internal chamber to the airfoil exterior. The cooling holes of each plurality extend generally parallel to one another. The cooling holes of the first and second pluralities intersect so as to define a plurality of spaced apart internal solid nodes in the side wall having pairs of opposite sides interconnected by pairs of opposite corners. The spaced nodes define a multiplicity of hole portions of the cooling holes which extend between and along opposite sides of adjacent nodes and a plurality of flow intersections which interconnect the hole portions of the cooling holes and are disposed between the corners of adjacent nodes.Type: GrantFiled: February 3, 1992Date of Patent: December 6, 1994Assignee: General Electric CompanyInventor: Ching-Pang Lee
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Patent number: 5369954Abstract: A turbofan engine bypass and exhaust system has a double-hoop configuration in which a fan exhaust passageway comprises shells of a constant circular contour to resolve air pressure induced stresses and increase in bypass passageway area asymmetrically in the horizontal direction without substantially increasing the overall engine height.Type: GrantFiled: May 24, 1993Date of Patent: December 6, 1994Assignee: General Electric CompanyInventor: Alan R. Stuart
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Patent number: 5370427Abstract: An expansion joint for connecting first and second fluid-carrying pipes comprising first and second annular couplings which are operably affixable to respective ones of the pipes. In a preferred embodiment the couplings include cylindrical bores of substantially the same diameter disposed relative to one another to form a passage for providing flow communication between the pipes. An annular bellows extends between the couplings for accommodating relative axial movement and angular misalignment between the pipes and is disposed radially outward of the passage to capture any fluid leaking between the interfacing surfaces of the couplings. A second cylindrical bore of a first one of the couplings engages an outer spherical surface of the second coupling to allow the second coupling to pivot in a manner which accommodates angular misalignment between the pipes.Type: GrantFiled: January 10, 1994Date of Patent: December 6, 1994Assignee: General Electric CompanyInventors: James S. Hoelle, Ivan H. Peterson, Thomas G. Wakeman, Michael R. Storage, Michael A. Umney, Mark K. Meyer
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Patent number: 5369952Abstract: A variable friction force damper utilizes geometric variations in a sliding surface to vary the frictional force. In particular, variation in thickness of the member on which the sliding surface is formed produces a corresponding variation in the displacement of a compression spring. This variation in spring displacement produces a variation in the compression force exerted by the spring, i.e., the force with which the sliding member is pressed against the sliding surface. This in turn causes a variation in the frictional force which the sliding surface exerts on the sliding member. The result is a variable friction force damper having a variable damping capability which allows a controlled response at variable input levels.Type: GrantFiled: July 20, 1993Date of Patent: December 6, 1994Assignee: General Electric CompanyInventor: Steven A. Walters
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Patent number: 5368911Abstract: A method for manufacturing a composite material comprises the steps of furnishing a layer of a matrix material, forming a groove in the matrix-material layer using a laser to remove material from the layer of matrix material in the form of a groove, and placing a reinforcement into the groove. Preferably, the surface of the layer of matrix material is smoothed with a laser beam prior to formation of the groove. In most instances, more than one layer is desired, and the steps of furnishing, forming, and placing are repeated, using the same or different materials, to build up a multilayer composite material. Cylindrical, flat, or curved panel composite materials can be readily prepared, using metal, intermetallic, or ceramic materials for the matrix.Type: GrantFiled: March 27, 1992Date of Patent: November 29, 1994Assignee: General Electric CompanyInventors: Seetharamaiah Mannava, Vanon D. Pratt, Henry MacLaren, Joseph J. Jackson, Patrick M. Kenney
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Patent number: 5367871Abstract: A plasma jet igniter is used to reliably relight a jet engine at high altitudes under adverse combustion conditions. The air-fuel mixture from the primary combustion zone of the jet engine combustor may be used as the plasma medium or, alternatively, liquid fuel direct from the aircraft fuel system may be used as a fuel charge.Type: GrantFiled: April 16, 1993Date of Patent: November 29, 1994Assignee: General Electric CompanyInventors: Kattalaicheri S. Venkataramani, John C. Scott
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Patent number: 5368444Abstract: Pairs of cylindrical rolling pin elements are disposed in mating nests between blade dovetails and disk posts in a gas turbine engine rotor assembly. During periods of change of disk rim elastic strain caused by changes in rotor speed, relative movement between the blade dovetails and disk posts is afforded through rolling contact of the pin elements. High pressure load slippage between conventional pressure face portions of dovetails and posts and resultant fretting wear damage is obviated. Multiple pairs of pins and nests and pins of other than cylindrical geometry are also contemplated.Type: GrantFiled: August 30, 1993Date of Patent: November 29, 1994Assignee: General Electric CompanyInventor: Bernard J. Anderson
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Patent number: 5368888Abstract: Apparatus and method for simultaneously coating interior and exterior surfaces of articles, such as advanced turbine airfoils, the interior surfaces defined by narrow, complex passageways. The apparatus and method, in addition to providing for simultaneous coating of interior and exterior surfaces, also permits additional control over the coating process by permitting control over the partial pressure of reactive gas introduced into the reaction chamber. The apparatus also permits for subsequent thermal treatment of the coated parts in an inert gas atmosphere with no intermediate cooling step thereby reducing costs while eliminating the potential for damage due to handling by the elimination of at least one handling operation.Type: GrantFiled: September 16, 1992Date of Patent: November 29, 1994Assignee: General Electric CompanyInventor: David V. Rigney
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Patent number: 5363643Abstract: A combustor liner segment includes a panel having four sidewalls forming a rectangular outer perimeter. A plurality of integral supporting lugs are disposed substantially perpendicularly to the panel and extend from respective ones of the four sidewalls. A plurality of integral bosses are disposed substantially perpendicularly to the panel and extend from respective ones of the four sidewalls, with the bosses being shorter than the lugs. In one embodiment, the lugs extend through supporting holes in an annular frame for mounting the liner segments thereto, with the bosses abutting the frame for maintaining a predetermined spacing therefrom.Type: GrantFiled: February 8, 1993Date of Patent: November 15, 1994Assignee: General Electric CompanyInventor: Ely E. Halila
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Patent number: 5363654Abstract: Impingement cooling of a jet engine subassembly, such as a combustor. Adjacent raised corrugation portions and intervening plate portions (having impingement cooling holes) of a corrugated plate define coolant channels in fluid communication with the engine compressor. Dividers positioned transverse to the corrugation portions have a top side attached to a bottom surface of the plate portions and have a bottom side attached to the combustor liner. Corrugation portions define therewithin return channels in fluid communication with post-impingement cooling air. The dividers prevent crossflow between the impingement cooling air and the post-impingement cooling air.Type: GrantFiled: May 10, 1993Date of Patent: November 15, 1994Assignee: General Electric CompanyInventor: Ching-Pang Lee
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Patent number: 5361580Abstract: A gas turbine engine rotor support system includes outer and inner rotors having respective outer and inner blades interdigitated in respective blade row stages. A stationary rear frame includes a rear support shaft. A rotatable aft frame is disposed forwardly of the rear frame includes an aft support shaft. And, a rotatable forward frame is disposed forwardly of the aft frame and includes a forward support shaft. The forward and aft frames support the outer and inner rotors, and a first bearing is disposed between the aft shaft and the rear shaft for supporting the aft shaft; a second bearing is disposed between the forward shaft and the aft shaft for supporting the forward shaft; and a third bearing is disposed between a core shaft of a core turbine and the forward shaft for supporting the core shaft thereon.Type: GrantFiled: June 18, 1993Date of Patent: November 8, 1994Assignee: General Electric CompanyInventors: John J. Ciokajlo, Ambrose A. Hauser, Samuel H. Davison
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Patent number: 5361828Abstract: A heat transfer surface for use along a flowpath along the surface is scaled with rows of turbulators having ramp surfaces protruding into the flowpath operable to generate turbulence promoting vortices. The ramp surfaces may be oriented to present an upward or downhill ramp to the direction of the flowpath along the surface. The present invention is further characterized by triangular side surfaces which precipitous drop off from a top ramp surface to the base of the turbulator along the heat transfer surface. The preferred embodiment of the present invention provides a three sided pyramid shaped turbulator with a ramp downhill surface wherein the sharp edge at the intersection of the two precipitous side surfaces is a leading edge into the flowpath on the heat transfer surface. Alternate embodiments include turbulators with triangular and rectangular uphill ramp surfaces.Type: GrantFiled: February 17, 1993Date of Patent: November 8, 1994Assignee: General Electric CompanyInventors: Ching-Pang Lee, Joseph W. Savage, Melvin Bobo
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Patent number: 5362221Abstract: A manufacturing device is disclosed which has a connector which automatically self-aligns with a mating connector of a docking station. The device includes a receptacle for receiving and holding an unfinished workpiece. At least one connector is provided for coupling the receptacle to at least one process input, such as electrical energy, pneumatics, hydraulics or the like, via the docking station, and an alignment mechanism is provided for automatically aligning the connector for attachment to a mating connector on the docking station when the receptacle is advanced toward the docking station.Type: GrantFiled: August 17, 1992Date of Patent: November 8, 1994Assignee: General Electric CompanyInventor: Dennis G. Perkins
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Patent number: 5358374Abstract: A turbine nozzle includes a vane integrally joined between outer and inner bands, with the inner band having a purge hole for discharging a portion of cooling air channeled through the vane. A checkvalve is provided in the purge hole for preventing backflow therethrough into the vane. In an exemplary embodiment, the checkvalve allows a reduction in cooling air through the vane at low power operation for increasing efficiency while preventing backflow of combustion gases into the purge hole.Type: GrantFiled: July 21, 1993Date of Patent: October 25, 1994Assignee: General Electric CompanyInventors: Victor H. S. Correia, Richard W. Albrecht, Robert A. Frederick
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Patent number: 5357744Abstract: A turbine flowpath assembly includes a plurality of circumferentially spaced apart airfoils disposed within an annular outer casing. Each of the airfoils includes outer and inner integral bands. A plurality of flowpath outer and inner panels are disposed between adjacent ones of the bands and circumferentially overlap the bands. The panels and bands are joined together at the respective overlaps for allowing circumferential movement therebetween while providing sealing.Type: GrantFiled: July 1, 1993Date of Patent: October 25, 1994Assignee: General Electric CompanyInventors: Robert P. Czachor, Christopher C. Glynn
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Patent number: 5357742Abstract: The hot core engine compartment of a turbojet engine is cooled by the metered flow of cooling air exhausted through a laminar flow nacelle system. This arrangement reduces the need for extracting bypass ram air from the engine performance cycle for cooling purposes and thereby improves specific fuel consumption and engine efficiency. A turbocompressor pump driven by bleed air from the core engine compressor draws cooling air through the laminar flow nacelle system and pumps the air into a manifold surrounding the core engine.Type: GrantFiled: January 12, 1994Date of Patent: October 25, 1994Assignee: General Electric CompanyInventor: Franklin E. Miller
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Patent number: 5356545Abstract: A dry film, low coefficient of friction lubricant for titanium pieces is prepared by mixing together solid lubricant particles, poly(tetrafluoroethylene), a suspending agent, and a curable resin in an evaporable carrier. The mixture is applied to titanium or titanium alloy surfaces that contact each other in service. The carrier is evaporated during a subsequent thermal cure, leaving a lubricating film on the surfaces.Type: GrantFiled: January 15, 1991Date of Patent: October 18, 1994Assignee: General Electric CompanyInventor: Peter Wayte
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Patent number: 5356265Abstract: A gas turbine engine turbine blade includes an airfoil having pressure and suction sides joined together at leading and trailing edges and extending from a root to a tip. The airfoil also includes a longitudinally extending flow channel for receiving compressed air, with the flow channel including a chordally extending, imperforate septum dividing the flow channel into first and second laterally spaced apart flow chambers. The blade further includes a supply manifold for receiving the compressed air at a single pressure which is disposed in flow communication with both the first and second chambers for channeling thereto respective first and second portions of the compressed air. The septum is used to reduce or eliminate radial velocity distortion, or blowoff of film cooling air from the suction side.Type: GrantFiled: August 25, 1992Date of Patent: October 18, 1994Assignee: General Electric CompanyInventor: David M. Kercher
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Patent number: 5357450Abstract: The invention provides a system and method for automatically, accurately, and repeatable aligning computer numerically controlled (CNC) movable machine components with respect to their respective degrees of freedom of motion. One embodiment of the invention, particularly useful for maintenance purposes, provides a programmable CNC programmer that uses a spindle mounted probe to measure at least two different positions of a point on a movable machine component to evaluate the geometric condition of the component with respect to a degree of freedom of motion of the component and issue alignment instructions to the machine operator. One embodiment provides the invention in a CNC computer program on a programmable media having a programmed set of instructions. The preferred embodiment uses the controller control the CNC machine's operation and spindle movement, perform the machine components' maintenance evaluation, and issue instructions for aligning the components in a consistent manner.Type: GrantFiled: February 10, 1994Date of Patent: October 18, 1994Assignee: General Electric CompanyInventors: R. David Hemmerle, James E. Randolph, Jr., John G. J. Frezza
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Patent number: 5355668Abstract: A catalyst-bearing component of a gas turbine engine is provided. Catalytic materials are provided on components defining the gas flow path of the engine, so that emissions of carbon monoxide and unburned hydrocarbons are reduced. The catalytic materials are selected from the group consisting of noble metals and transition metal oxides. The portions of the gas flow path where such materials are advantageously applied include the combustor, the turbine and the exhaust system. The catalytic coating is preferably applied in conjunction with a thermal barrier coating system interposed between a substrate component and the catalytic coating.Type: GrantFiled: January 29, 1993Date of Patent: October 18, 1994Assignee: General Electric CompanyInventors: Antoinette E. Weil, Jon C. Schaeffer, Julia A. Fields