Patents Represented by Attorney Jerome C. Squillaro
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Patent number: 5356264Abstract: The present invention is a viscoelastic damper assembly for a front frame for a gas turbine engine that is removable, reusable, and retrofitable. The viscoelastic damper is disposed within a strut for damping vibration of the strut caused by airstream pressure pulses from first stage fan blades operating at transonic speeds. The viscoelastic damper can be installed in struts on gas turbine engines already in service or during manufacture. Also, the viscoelastic damper can be easily removed and reused when repairs to the front frame are required.Type: GrantFiled: October 14, 1993Date of Patent: October 18, 1994Assignee: General Electric CompanyInventors: Dennis W. Watson, Michael T. Bonnoitt
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Patent number: 5353685Abstract: The reliability of a fluid multiplexed actuation system is increased by arranging a pair of fluidic multiplexers in a parallel fluid flow path between a selector valve and several fluid actuators. Position sensors associated with the fluidic multiplexers and with the fluid actuators provide feedback signals to a microprocessor. In the event the feedback signals identify a malfunction in the fluidic multiplexer currently supplying fluid to the actuators, the microprocessor will deactivate the malfunctioning fluidic multiplexer and activate a redundant or back-up fluidic multiplexer by actuating the selector valve.Type: GrantFiled: October 7, 1993Date of Patent: October 11, 1994Assignee: General Electric CompanyInventor: Barton H. Snow
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Patent number: 5353865Abstract: An improved heat transfer assembly includes a textured impingement surface and means for impinging cooling air directly upon the textured surface. A component includes a surface textured to increase convective heat transfer with minimal increase in resistance to conductive heat transfer through the component. The textured surface can comprise an array of closely spaced hemispherically shaped protuberances. A method is disclosed for texturing a surface with discrete laser welds.Type: GrantFiled: March 30, 1992Date of Patent: October 11, 1994Assignee: General Electric CompanyInventors: Eugene F. Adiutori, Byron A. Pritchard, Jr., Stephen Aleshin
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Patent number: 5353587Abstract: A film starter structure for a combustor of a gas turbine engine which includes a plurality of circumferentially spaced, axially extending ribs formed on a radially inner surface of a forward section of an outer combustor liner adjacent a combustor dome. An annular ring overlays the ribs for defining a plurality of air passages. A support extends from the combustor dome and supports the outer liner about the dome. Compressor discharge air is introduced into the air passages and exits the air passages along the inner surface of the outer liner for establishing a cooling film barrier on the outer combustor liner surface. A spring seal between the combustor dome and the inner ring seats the dome within the ring and establishes a seal for preventing leakage air therebetween and allowing independent radial expansion of the liner and dome by compressing the spring seal.Type: GrantFiled: February 16, 1994Date of Patent: October 11, 1994Assignee: General Electric CompanyInventor: Ely E. Halila
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Patent number: 5354176Abstract: A variable pitch propeller blade system includes a conductive clevis attached to a rotor, a mating non-conductive clevis fastened to a non-conductive propeller blade, a pin journaling through bores in each clevis, joining the clevises to form a hinge joint, and a conductive path along a substantial part of the propeller blade.Type: GrantFiled: September 29, 1993Date of Patent: October 11, 1994Assignee: General Electric CompanyInventors: Jan C. Schilling, Charles E. Steckle
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Patent number: 5351477Abstract: A dual fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct having contained therein a gas fuel manifold and a liquid fuel manifold in flow communication with a gas fuel supply and a liquid fuel supply, respectively, and control means, a set of inner and outer annular counter-rotating swirlers adjacent the upstream end of the mixing duct, where at least the outer annular swirlers include hollow vanes with internal cavities and gas fuel passages, all of which are in fluid communication with the gas fuel manifold to inject gas fuel into the air stream, the vane cavities also having liquid fuel passages therethrough in fluid communication with the liquid fuel manifold, and a hub separating the inner and outer annular swirlers to allow independent rotation thereof, the hub having a circumferential slot in fluid communication with the liquid fuel passages which injects liquid fuel into the air stream, wherein high pressure air from a compressor is injected into theType: GrantFiled: December 21, 1993Date of Patent: October 4, 1994Assignee: General Electric CompanyInventors: Narendra D. Joshi, Eric J. Kress
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Patent number: 5351478Abstract: An apparatus and method for minimizing compressor casing distortion due to bleed air extraction wherein the compressor casing includes an annular outer casing having at least one outlet duct, an annular inner casing disposed co-axially with the outer casing and spaced radially inwardly therefrom to define a plenum, two radial discs extending inwardly from the outer casing defining a plenum, a plurality of small area bleed openings located in the inner casing for imparting a radial velocity to the bleed air greater than the circumferential velocity entering the plenum, an air tube located over each bleed opening, and a baffle plate located on top of the air tubes and communicating with the radial discs for supporting the casings, whereby the bleed air impinges on the outer casing and controls distortion by sufficiently reducing the circumferential temperature gradient forming at the outer casing.Type: GrantFiled: May 29, 1992Date of Patent: October 4, 1994Assignee: General Electric CompanyInventors: Roger C. Walker, Richard J. Fallon, Harold P. Rieck, Jr., John D. Bibler
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Patent number: 5351888Abstract: A convergent-divergent exhaust nozzle is mounted to an exhaust duct of a jet aircraft engine by a circumferentially-spaced set of hydraulic cylinders. The cylinders are interconnected in captured flow via hydraulic circuits which allow the cylinders to function as a gimbal mounting. This mounting allows the entire nozzle to vector the exhaust without additionally loading the divergent flaps with vectored exhaust so that cool, low pressure ram air can be channeled directly to the divergent flaps for efficient cooling.Type: GrantFiled: May 14, 1993Date of Patent: October 4, 1994Assignee: General Electric CompanyInventors: John B. Taylor, Dudley O. Nash
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Patent number: 5351473Abstract: A gas turbine engine includes a fan, fan bypass duct, compressor, core duct, and turbine including a clearance control system. The core duct includes a bleed valve, the fan bypass duct includes a bleed vent, and a bleed pipe is disposed in flow communication therebetween. A feed pipe is disposed in flow communication between the bleed pipe and the clearance control system. The apparatus is effective for practicing a method of bleeding a portion of compressed air from the core duct to the fan bypass duct during a first mode of operation, and diverting a portion of the bleed air from the bleed pipe into the feed pipe for flow to the clearance control system at a low flowrate during the first mode. During a second mode of operation, the method includes bleeding a portion of the fan air from the fan bypass duct and through the feed pipe to the clearance control system while discontinuing bleeding of the compressed air from the core duct.Type: GrantFiled: April 30, 1993Date of Patent: October 4, 1994Assignee: General Electric CompanyInventor: Brian H. Shuba
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Patent number: 5351476Abstract: 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.Type: GrantFiled: April 14, 1993Date of Patent: October 4, 1994Assignee: General Electric CompanyInventors: Daniel J. Laborie, Joseph R. Marban, Wallace M. Schulze, Robert J. Baumbick
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Patent number: 5350279Abstract: A blade retaining sub-assembly for use in a gas turbine engine which includes at least one radially extending blade mounted in a dovetail slot of a rotatable annular disk. The sub-assembly prevents the blade from migrating from the dovetail slot in an axially forward direction and includes a pair of circumferentially spaced lugs extending from a pair of adjacent disk posts such that each of the lugs are disposed axially forward of, and circumferentially adjacent to, respective ones of the lateral surfaces of the blade dovetail. The sub-assembly further includes a retainer plate disposed in each of the lugs and the plate restrained. The plate includes a body section and a contoured platform which is disposed in confronting relationship with the blade dovetail, wherein the contoured platform includes a periphery which is predeterminedly shaped and positioned so as to enhance a load carrying capability of the plate and lugs.Type: GrantFiled: July 2, 1993Date of Patent: September 27, 1994Assignee: General Electric CompanyInventors: Ian F. Prentice, Jerome A. Juenger
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Patent number: 5349814Abstract: A method and assembly are effective for air-starting an aircraft gas turbine engine having a fan powered by a low pressure turbine through a first shaft, and a compressor powered by a high pressure turbine through a second shaft disposed coaxially therewith. A gear train is selectively operatively joined between the first and second shafts by selectively engaging a first clutch for transmitting torque through the first clutch only in one direction from the first shaft to the second shaft when the fan is windmilling for driving the second shaft to allow an air-start of the gas turbine engine during flight. In a preferred embodiment, a second clutch is operatively joined to the gear train and is selectively engageable at speeds of the second shaft below a predetermined release speed, and disengageable at the release speed and above for disconnecting the air-start assembly once the engine has been started.Type: GrantFiled: February 3, 1993Date of Patent: September 27, 1994Assignee: General Electric CompanyInventors: John J. Ciokajlo, Michael T. O'Brien
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Patent number: 5350599Abstract: An article is protected by a thermal barrier coating system. The article includes a substrate having an outer surface and a thermal barrier coating system deposited upon the substrate. The thermal barrier coating system includes a porous region wherein the ceramic is present as a porosity-containing columnar grain structure extending substantially perpendicular to the substrate surface, and an erosion-resistant densified region overlying the porous region. The thermal barrier coating is preferably applied by rotating the substrate past a deposition source to deposit the columnar grains, and then halting or slowing the rotation while continuing the deposition of the erosion-resistant region.Type: GrantFiled: October 27, 1992Date of Patent: September 27, 1994Assignee: General Electric CompanyInventors: David V. Rigney, Robert W. Bruce, Antonio F. Maricocchi
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Patent number: 5350200Abstract: A tube coupling assembly for use in connecting first and second fluid-carrying tubes comprising an annular sleeve member and an annular ferrule which are operably affixable to respective ones of the tubes. A tube connector and a coupling nut threadingly engage one another so as to force first and second spherical surfaces of the sleeve member against generally frusto-conical surfaces of the ferrule and coupling nut respectively, thereby forming a fluid sealing means and accommodating angular misalignment between the tubes. An internal locking means is provided for preventing the disengagement of the sealing means. The coupling nut and tube connector each include wrenching surfaces which must be used to torque the assembly, with the applied torque and counter-torque avoiding torsional loading of the tubes.Type: GrantFiled: January 10, 1994Date of Patent: September 27, 1994Assignee: General Electric CompanyInventors: Ivan H. Peterson, James S. Hoelle, Thomas G. Wakeman
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Patent number: 5349850Abstract: An instrumentation light probe holder for use in observing and measuring operating characteristics of rotating blades of a gas turbine engine during engine operation or rotating components of a machine during operation is disclosed. The holder includes an elongated cylindrical member for insertion into an opening or bore formed radially through an annular casing of the gas turbine engine or machine housing. The cylindrical member has a hollow interior for receipt of an instrumentation light probe and a first end for insertion into the casing or housing and for holding an operating end of the probe at a selected set-back distance from the rotating blades or components. A grasping mechanism is provided for releasably holding the light probe in the cylindrical member.Type: GrantFiled: November 19, 1992Date of Patent: September 27, 1994Assignee: General Electric CompanyInventor: Joseph C. Young
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Patent number: 5349815Abstract: A flight vehicle scramjet combustor. The combustor, in its "2-D" and annular embodiments, has two spaced-apart, generally opposing, and longitudinally extending walls. One wall includes a generally aft-facing step having a first section and an interconnected second section, a forward wall portion attached to the first section, and an aft wall portion attached to the second section. The second section includes a fuel injector discharge orifice having a fuel discharge axis which is aligned generally perpendicular to the second section and which projects both generally towards the other wall and longitudinally aft. The combustor has a cylindrical embodiment which includes a cylindrical wall having a step and fuel injector discharge orifice similar those of the "2-D" and annular combustor embodiments.Type: GrantFiled: August 27, 1991Date of Patent: September 27, 1994Assignee: General Electric CompanyInventor: Paul H. Kutschenreuter, Jr.
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Patent number: 5348446Abstract: An airfoil for a gas turbine engine is constructed from a core body formed of a conventional nickel-based superalloy and leading and trailing edge components and squealer tip formed of a nickel aluminide alloy. The nickel aluminide components exhibit a high degree of thermal conductivity and efficiently transfer heat into the core body by direct conduction.Type: GrantFiled: April 28, 1993Date of Patent: September 20, 1994Assignee: General Electric CompanyInventors: Ching-Pang Lee, Anne M. Isburgh, Paul S. Wilson
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Patent number: 5348602Abstract: A bend portion of a bonded, laminated article is made substantially free of wrinkling, which results in interlaminar voids and discontinuities, by applying tension to at least one layer of a radially outer portion of a preform of the article during bonding, the tension being applied in a direction away from the bend, typically generally tangentially in respect to an inner portion. The apparatus includes a rigid support to carry the preform bend portion, held to the support to enable application of force or pressure to the outer layer.Type: GrantFiled: June 8, 1993Date of Patent: September 20, 1994Assignee: General Electric CompanyInventors: Peter Makarenko, Stacy E. Harris, Robert R. Martin
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Patent number: 5345757Abstract: 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.Type: GrantFiled: September 20, 1993Date of Patent: September 13, 1994Assignee: General Electric CompanyInventors: Thomas L. MacLean, Richard W. Stickles
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Patent number: 5345803Abstract: Disclosed is an apparatus for producing smooth, continuous arcuate contour bends in tubes used, for example, in the manufacture of fuel manifolds for gas turbine engines. A flexible die cavity circumscribing an arbor member with an integral adjustment feature are utilized to provide means for modifying the radius of curvature of the forming die cavity to compensate for variable tube spring back characteristics. A first embodiment provides for infinite adjustment of radius of curvature within range limits, while an alternate embodiment provides for incremental adjustment. Means are also provided to lock the adjustment feature once the desired radius of curvature has been achieved.Type: GrantFiled: August 30, 1993Date of Patent: September 13, 1994Assignee: General Electric CompanyInventor: Everett A. Cutter