Patents Represented by Attorney Jerome C. Squillaro
-
Patent number: 5391256Abstract: A method and passage system is applicable to hollow structures, such as hollow rib core fan blades, for removing alpha case and contamination, for improving surface texture, and for smoothing diffusion bonded joints to reduce notches and flaws, after fabrication. The passage system allows for venting and full cavity access to permit cleaning of the interior of the hollow structure. The method of cleaning the interior of a hollow structure may comprise applying an etchant to strip the topical layer from the inside of a hollow mechanical structure, such as a hollow core airfoil; or may comprise pumping an abrasive flow through the hollow cavities of the structure.Type: GrantFiled: April 5, 1993Date of Patent: February 21, 1995Assignee: General Electric CompanyInventors: Kurt L. Hansen, Johnny F. Hill, II, Arthur L. Ludwig
-
Patent number: 5390498Abstract: A gas turbine engine fuel distribution assembly includes a fuel manifold having a fuel distribution channel therein, and a plurality of fuel distribution valves disposed inside the manifold. Each valve is disposed in the manifold for providing a bypass channel therearound for allowing unobstructed flow of the fuel through the distribution channel in turn to each of the valves. Each valve has an inlet disposed in flow communication with the distribution channel for receiving a portion of the fuel therefrom, and an outlet extending laterally through the manifold for providing controlled fuel flow therefrom.Type: GrantFiled: February 15, 1994Date of Patent: February 21, 1995Assignee: General Electric CompanyInventor: David A. Sulkin
-
Patent number: 5388964Abstract: A hybrid gas turbine engine rotor blade includes an airfoil and a dovetail integrally joined thereto. The airfoil includes an inner portion disposed adjacent to the dovetail to provide a structural transition, and an outer portion disposed thereabove for effecting a pressure rise in airflow channeled thereacross. A nosepiece is disposed adjacent to the leading edge of the airfoil inner portion, and a tailpiece is disposed adjacent to the trailing edge of the airfoil inner portion. The nosepiece, tailpiece, and airfoil inner portion are collectively aerodynamically configured for effecting a pressure rise in the airflow channeled thereacross.Type: GrantFiled: September 14, 1993Date of Patent: February 14, 1995Assignee: General Electric CompanyInventors: John J. Ciokajlo, Michael T. O'Brien
-
Patent number: 5388962Abstract: The present invention discloses a system for cooling turbine rotor disk posts in a gas turbine engine with a preferred embodiment illustrating an application for a high pressure turbine stage 1 rotor disk. The disk includes a plurality of circumferentially alternating posts and slots disposed about the periphery of the disk with each slot receiving a dovetail of a radially extending blade. The cooling system comprises a plurality of seal bodies with each seal body including a relatively low volume thermal isolation chamber positioned over the top of a corresponding disk post; a plurality of axially extending blade cooling plenums supplied with cooling air with one of the plenums positioned radially inward of each of the blades; a plurality of shallow, radially extending slots formed in a relatively low stressed axially facing surface of each of the blade dovetails for diverting cooling air from the blade cooling plenums to the thermal isolation chambers.Type: GrantFiled: October 15, 1993Date of Patent: February 14, 1995Assignee: General Electric CompanyInventors: Thomas G. Wygle, David G. W. Fargher, Arthur J. Piekarski
-
Patent number: 5388959Abstract: A fan assembly for a gas turbine engine for aircraft has a stator casing made of a first material and an annular abradable seal structure made of a second material comprising an epoxy foam having heat expandable, thermoplastic microballoons filled with a chemical which expands when the second material is cured such that the second material bonds directly to the stator casing upon curing thereby minimizing the number of processing steps during manufacture.Type: GrantFiled: August 23, 1993Date of Patent: February 14, 1995Assignee: General Electric CompanyInventors: James M. Forrester, Bradley R. Love, Jack W. Baldwin
-
Patent number: 5387086Abstract: A turbine blade is provided which includes an airfoil section having a leading edge flow region and a trailing edge flow region. The leading edge flow region includes an inner cavity having a serpentine geometry and first and second air inlets. The first air inlet is at one end of the inner cavity and is coupled to a first conduit which supplies air coolant thereto. The leading edge flow region also includes a leading edge cavity having a plurality of air film holes at the leading edge of the blade. The leading edge cavity is coupled to the inner cavity by impingement holes therebetween. The leading edge flow region further includes a refresher passageway which connects the first conduit at the base of the blade with the second inlet of the inner cavity. The refresher passageway refreshes the airflow in the inner cavity after the airflow has flowed part way through the inner cavity and has become warmed.Type: GrantFiled: July 19, 1993Date of Patent: February 7, 1995Assignee: General Electric CompanyInventors: David A. Frey, Mark E. Ulliman
-
Patent number: 5386851Abstract: A fuel valve comprising main fuel valve connected to a burner staging valve such that fuel flow from the main fuel valve is divided between pilot and main domes in a dual annular combustor. The burner staging valve includes a movable spool located within a fixed sleeve such that the spool may be moved both laterally and rotated within predetermined limits. The movable spool and sleeve include pilot, main and inlet windows arranged such that the inlet windows receive fuel from the main fuel valve and the pilot and main windows split the fuel flow between the pilot and main domes of the combustor.Type: GrantFiled: January 12, 1994Date of Patent: February 7, 1995Assignee: General Electric CompanyInventors: Martin A. Clements, Robert M. Darby
-
Patent number: 5387085Abstract: A gas turbine engine airfoil includes a serpentine cooling circuit with a branch cooling circuit disposed in parallel therewith for independently controlling discharge of cooling air therefrom through respective discharge holes in pressure and suction sides of the airfoil. Metering orifices are provided between the serpentine circuit and the branch circuit for controlling flow of cooling air into the branch circuit from the serpentine circuit, and therefore controlling discharge of the cooling air from the branch discharge holes relative to the serpentine discharge holes.Type: GrantFiled: January 7, 1994Date of Patent: February 7, 1995Assignee: General Electric CompanyInventors: Theodore T. Thomas, Jr,, Ching-Pang Lee
-
Patent number: 5385013Abstract: A gas turbine engine thermal backbone deflection control apparatus to counter the effects of backbone bending due to nacelle aerodynamic, thrust, and maneuver loads by introducing a controlled backbone counter-bending moment by applying an uneven temperature or thermal field around the backbone to induce controlled compression and/or tensioning forces in the backbone or casing between axially spaced apart frames connected by the backbone. One embodiment of the invention provides for flowing thermal control air along an axially and circumferentially sector of the engine casing. The thermal backbone deflection control apparatus is controlled by the engines digital electronic control system using input signals generated by engine thrust load, inlet moment load sensors and/or blade tip clearance sensors.Type: GrantFiled: November 30, 1993Date of Patent: January 31, 1995Assignee: General Electric CompanyInventors: Michael L. Barron, James W. Brantley, Thomas G. Wakeman
-
Patent number: 5386184Abstract: A modified inverter/converter unit electronically commutates a switched reluctance machine to provide multiple voltage levels for engine and aircraft applications. A set of power switching transistors apply an exciting current to windings in the switched reluctance machine to produce power at a first voltage level. Additional voltage levels may be provided by using the turns ratio from one or more transformers and the switching frequency from the power switching transistors. Alternatively, additional voltage levels may be provided by using windings of a plurality of transformers internal to the switched reluctance machine.Type: GrantFiled: July 23, 1993Date of Patent: January 31, 1995Assignee: General Electric CompanyInventor: William D. Jones
-
Patent number: 5381655Abstract: A variable cycle jet engine is provided with a mixing duct assembly which mixes core engine exhaust gas with bypass air when the engine is operating in a turbofan mode and which blocks flow from the core engine and isolates the core engine from the bypass flow when the engine is operating as a ramjet.Type: GrantFiled: May 10, 1993Date of Patent: January 17, 1995Assignee: General Electric CompanyInventors: Robert J. Orlando, Lawrence W. Dunbar
-
Patent number: 5379689Abstract: A multipurpose, automatic, self-contained device for manufacturing or repairing a workpiece made from a composite material includes a frame having an upper frame member and a lower frame member. A mechanical apparatus for providing a compressive force is mounted to the lower frame member and a lower platen is mounted to a movable member of the apparatus. An upper platen, positioned opposite to the lower platen, is mounted to the upper frame member. At least one heater is associated with at least one of the platens to apply heat to the workpiece and at least one temperature sensor is provided for mounting to the workpiece. The lower platen is moved toward and away from the upper platen by the mechanical apparatus to apply a compressive force to the workpiece disposed between the platens as a function of the temperature sensed from the workpiece and/or according to a predetermined schedule or plan.Type: GrantFiled: July 29, 1993Date of Patent: January 10, 1995Assignee: General Electric CompanyInventors: James V. Timmons, Bert C. Jones, III, Paul S. Manicke
-
Patent number: 5379585Abstract: A method of controlling a system is adapted to control flow to throat nozzle and vectoring nozzle actuators. The method comprises the steps of summing a plurality of signals representative of flow to the vectoring nozzle actuators with a signal representative of flow to the throat nozzle actuators to generate a total hydraulic flow signal. The total flow signal is then compared to a signal representative of total pump output to generate a reserve signal. Finally, a scaled rate limit signal is generated from the reserve signal and multiplied by predetermined ratio signals such that the ratio signals are limited by the difference between pump output and pump demand.Type: GrantFiled: July 6, 1993Date of Patent: January 10, 1995Assignee: General Electric CompanyInventors: Barton H. Snow, David M. Leighton, Michael J. Steckler
-
Patent number: 5379970Abstract: A mounting means is adapted to hold a large component while it is being bolted to a frame. A hook is attached to the component and adapted to suspend the component in a first position. A bracket is attached to the frame and is adapted to receive the hook, hold the component in the first position, and align the component with a mounting bolt. The component is then drawn to a second, installed, position as the mounting bolt is tightened.Type: GrantFiled: April 2, 1993Date of Patent: January 10, 1995Assignee: General Electric CompanyInventors: Steven E. Linthicum, Wilson T. Guy
-
Patent number: 5375978Abstract: The present invention provides a composite airfoil particularly useful as a fan blade, having a high degree of twist, in a large high bypass ratio turbofan engine. The composite airfoil of the present invention has a progression of filament reinforced airfoil laminations of varying span, arranged in order by span, and interrupted by at least one filament reinforced airfoil lamination having a span out of height order to form what is called a confused or broken shear plane where radially outer tips of the laminations end.Type: GrantFiled: October 4, 1993Date of Patent: December 27, 1994Assignee: General Electric CompanyInventors: Charles R. Evans, Barrett J. Fuhrman, Jackie D. Jones, Richard A. Ridilla
-
Patent number: 5375420Abstract: A double annular combustor having concentrically disposed inner and outer annular combustors is provided with inner and outer domes. A centerbody is disposed between the inner and outer domes and is constructed of a plurality of annular segments. Each segment includes an upper wall, a lower wall, an upstream wall and a downstream end. The upper and lower walls include flanges extending therefrom to form cavities, within which are cooling holes. Pins are also provided which extend between the upper and lower walls of the centerbody to augment the cooling and structural connection thereof.Type: GrantFiled: August 12, 1993Date of Patent: December 27, 1994Assignee: General Electric CompanyInventors: Stephen W. Falls, Hubert S. Roberts, Jr., James N. Cooper, Stephen E. Melton
-
Patent number: 5376827Abstract: An integrated turbine and generator includes a power turbine having counter-rotating outer and inner rotor blades extending from respective outer and inner rotors. The outer and inner rotors are supported by stationary front and rear frames. At least one electrical generator includes a field core for creating magnetic poles which is disposed coaxially with an armature for generating electrical power upon relative rotation therebetween. The field core and the armature are disposed coaxially with the outer rotor and radially outwardly therefrom, with one of the field core or armature being fixedly joined to the outer rotor for rotation therewith, and the other one thereof being fixedly joined to the front and rear frames.Type: GrantFiled: May 27, 1993Date of Patent: December 27, 1994Assignee: General Electric CompanyInventor: William R. Hines
-
Patent number: 5372476Abstract: A turbine nozzle support assembly includes nozzle segments each having an inner band with an integral retention flange extending radially inwardly therefrom. A plurality of retention tabs extend radially inwardly and are spaced axially aft of the retention flange to define a capture slot therebetween. A nozzle support includes a radially outwardly extending upper flange having a plurality of support pins extending axially, forwardly therefrom and disposed in complementary retention apertures in the retention flanges of the nozzle segments. A retention key is disposed in the capture slot axially between the upper flange and the retention tabs for axially retaining the nozzle segments on the nozzle support.Type: GrantFiled: June 18, 1993Date of Patent: December 13, 1994Assignee: General Electric CompanyInventors: Robert J. Hemmelgarn, Andrew Shepherd
-
Patent number: 5373222Abstract: A datuming device is provided for use with a machine tool having a movable member which is guided under computer numerical control. The datuming device permits measurement of displacements in a direction not parallel with a displacement probe's line of travel. The device includes a non-sensitive surface which, when probed by the displacement probe, does not indicate a changing displacement when the movable member is moved from a first position to a second position. The nonsensitive surface serves as a reference surface. The device further includes a sensitive surface which, when probed by the displacement probe, exhibits a changing displacement when the movable member is moved from the first position to the second position. The sensitive surface is generally configured as an inclined surface on the datuming device.Type: GrantFiled: March 17, 1993Date of Patent: December 13, 1994Assignee: General Electric CompanyInventors: R. David Hemmerle, Charles W. Muchmore, William D. Rouse, Timothy M. Heitzman
-
Patent number: 5369882Abstract: A generally wedge-shaped vibration damper for rotor blades of a gas turbine engine has a pair of scrubbing surfaces and is loosely retained in a pocket incorporated in the rotor blade platform. The pocket is partly defined by a plurality of surfaces which orient the damper so that it is slidably displaceable and rotatable only in a predetermined plane. During rotation of the rotor disk, the damper of one rotor blade is displaced in a plane transverse to the rotor axis of rotation by centrifugal forces to a position at which one scrubbing surface of the damper abuts a side surface of the platform of the adjacent rotor blade and the other scrubbing surface abuts an inner surface of the platform of the rotor blade in which the damper is inserted. The scrubbing action of the damper serves to damp vibratory motion in the platforms of both blades.Type: GrantFiled: November 2, 1993Date of Patent: December 6, 1994Assignee: General Electric CompanyInventors: Philip W. Dietz, Charles E. Steckle, Robert J. Corsmeier