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| Number | Title | Issue Date |
| 5820346 | Blade damper for a turbine engine A damper which provides both blade to blade and blade to ground damping is described. In one embodiment, the damper includes a retainer and a chicklet. The retainer is secured to a rotor disk by a bolt which extends through an opening in the disk and an o... | 10/13/1998 |
| 5820345 | Split rotor shaft driven lift fan A split fan for providing lift for an aircraft is described. In one embodiment, a main engine shaft extends to the split fan, and a portion of the split fan is located at an elevation above the main engine shaft and a portion of the split fan is located a... | 10/13/1998 |
| 5816049 | Dual fuel mixer for gas turbine combustor An apparatus for premixing fuel and air prior to combustion in a gas turbine engine is disclosed as including a linear mixing duct having a circular cross-section defined by a wall. A gas fuel manifold is positioned adjacent the upstream end of the mixing... | 10/06/1998 |
| 5813221 | Augmenter with integrated fueling and cooling A turbofan engine augmenter includes an exhaust casing and a combustion liner therein which define therebetween a cooling duct for receiving bypass air. A diffusion liner adjoins the combustion liner and defines with the casing an outer inlet for receivin... | 09/29/1998 |
| 5809772 | Turbofan engine with a core driven supercharged bypass duct A multiple bypass turbofan engine including a core engine assembly has a fan bypass duct radially outward of the core engine assembly and has first and second inlets disposed between forward and aft fans driven by a low pressure turbine and a core engine ... | 09/22/1998 |
| 5806303 | Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle A multiple bypass turbofan engine including a core engine assembly has a fan bypass duct radially outward of the core engine assembly and has first and second inlets disposed between forward and aft fans driven by a low pressure turbine and a core engine ... | 09/15/1998 |
| 5797726 | Turbulator configuration for cooling passages or rotor blade in a gas turbine engine A turbulator configuration is formed on an inner surface of one or more walls defining a cooling passage in a rotor blade of a gas turbine engine, where the cooling passage has a centerline extending therethrough. The turbulator configuration includes a p... | 08/25/1998 |
| 5797723 | Turbine flowpath seal A turbine seal includes a first arcuate segment defining a flowpath boundary between combustion gases and air, and includes a radially outwardly extending rail at one end thereof. A second arcuate segment is disposed coaxially with the first segment for d... | 08/25/1998 |
| 5791148 | Liner of a gas turbine engine combustor having trapped vortex cavity A liner for a gas turbine engine combustor is disclosed having a non-linear cavity section, wherein air and fuel injected therein form a trapped vortex for igniting and stabilizing a flame in the combustor. The cavity section, which is substantially recta... | 08/11/1998 |
| 5785498 | Composite fan blade trailing edge reinforcement The present invention provides a composite airfoil, particularly useful as a wide chord 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 reinforced region of its air... | 07/28/1998 |
| 5782078 | Tapered jam nut for turbine frame mount link A link for supporting a core engine within an outer shell of a gas turbine engine is described. The link, in one form, includes an elongate rod having a first end and a second end, and first and second rod end bearings are secured at the first second ends... | 07/21/1998 |
| 5779152 | Coordinated vectoring exhaust nozzle with scissors linkage An exhaust nozzle includes a plurality of circumferentially spaced apart exhaust flaps, and a plurality of scissor linkages joined to respective ones thereof. Each linkage includes a frame pivotally joined to a respective one of the flaps. A carriage is s... | 07/14/1998 |
| 5778658 | Recoup turbojet engine A turbojet engine includes a compressor and turbine, with a combustor disposed therebetween for generating exhaust gas. An afterburner includes an annular casing and liner spaced radially inwardly therefrom to define a cooling duct therebetween. A recoup ... | 07/14/1998 |
| 5775589 | Cooling apparatus for aircraft gas turbine engine exhaust nozzles The present invention provides coolable exhaust nozzle flap and seal assemblies having liners that are spaced inward and apart from their respective flap and seal cool walls, to form a cooling passage therebetween that converges in the axial downstream fl... | 07/07/1998 |
| 5771696 | Internal manifold fuel injection assembly for gas turbine A gas turbine engine fuel injection assembly includes a combustor case surrounding a combustor having a dome. An arcuate manifold is disposed inside the combustor case adjacent to the dome, and includes a plurality of fuel injectors disposed in flow commu... | 06/30/1998 |
| 5771680 | Stiffened composite structures and method of making thereof A stiffened composite is provided exhibiting multi-directional reinforcement with continuous long fibers. The composite has a substrate and serpentine stiffeners adhered thereto. The stiffeners merge toward, join with and diverge from adjacent stiffeners ... | 06/30/1998 |
| 5768149 | Systems and methods for automated tube design A design system for designing a tube for a gas turbine engine is described. The system including, in one embodiment, a computer workstation having a plurality of executable modules stored therein. The modules include a tube design module for routing a tub... | 06/16/1998 |
| 5760289 | System for balancing loads on a thrust bearing of a gas turbine engine rotor and process for calibrating control therefor A process for periodically calibrating an algorithm in a control unit of a system for balancing loads on a thrust bearing of a gas turbine engine rotor is disclosed involving the steps of initializing a calibration of the control unit algorithm, causing t... | 06/02/1998 |
| 5746578 | Retention system for bar-type damper of rotor A rotor blade for a rotor of a gas turbine engine having an axis of rotation including a root portion, a platform portion connected to the root portion and having a damper pocket formed therein, an airfoil portion connected to the platform portion, a gene... | 05/05/1998 |
| 5746574 | Low profile fluid joint A low profile joint is provided for a strut tube extending radially through a strut extending between an outer casing and an inner hub in a gas turbine engine frame. The strut tube has a longitudinal axis and a closed distal end. A sideseat is spaced from... | 05/05/1998 |
| 5738493 | Turbulator configuration for cooling passages of an airfoil in a gas turbine engine A turbulator configuration formed on an inner surface of at least one wall of a cooling passage for a rotor blade in a gas turbine engine is disclosed, where the cooling passage has an upstream end, a downstream end, and a longitudinal axis therethrough. ... | 04/14/1998 |
| 5738491 | Conduction blade tip A turbine blade includes an airfoil having a root, tip cap, and laterally opposite pressure and suction sides extending between leading and trailing edges. A cooling circuit is disposed inside the airfoil and extends from the tip cap to the root for circu... | 04/14/1998 |
| 5738489 | Cooled turbine blade platform A turbine blade includes a dovetail, shank, platform, and airfoil. A cooling circuit extends radially therethrough for circulating a coolant. A thermal conductor is disposed on a lower surface of the platform for conducting heat from the platform to the s... | 04/14/1998 |
| 5735671 | Shielded turbine rotor A turbine rotor includes a rotor disk having a plurality of dovetail slots defining therebetween respective disk posts. Each post has a top land and a plurality of tangs spaced radially therebelow inside adjacent ones of the slots. A plurality of turbine ... | 04/07/1998 |
| 5735666 | System and method of controlling thrust forces on a thrust bearing in a rotating structure of a gas turbine engine A system for controlling thrust forces on a thrust bearing in a rotating structure of a gas turbine engine at designated operating points including a device for providing thrust load compensation to the thrust bearing, a control for operating the thrust l... | 04/07/1998 |
| 5733102 | Slot cooled blade tip A turbine blade includes an airfoil having an internal cooling circuit therein. The airfoil extends from a root to a tip cap, and includes laterally opposite pressure and suction sides extending between a leading edge and an opposite trailing edge over wh... | 03/31/1998 |
| 5725355 | Adhesive bonded fan blade A fan blade includes a spar having first and second opposite sides. The spar sides include a fatigue-life enhanced surface layer, with the spar first side having a cavity bounded in part by the surface layer. A skin closes the cavity and is bonded to the ... | 03/10/1998 |
| 5725354 | Forward swept fan blade A gas turbine engine fan blade includes a main body having a radially spaced apart root and tip, and axially spaced apart leading and trailing edges. A front shell is fixedly joined to a portion of the body leading edge to collectively define with the bod... | 03/10/1998 |
| 5709516 | Washer faced spring assembly A washer faced spring assembly is disclosed for a motion absorbing and motion damping application which includes a first washer having a circular or polygonal hole therethrough centered about a central axis, a second washer disposed opposite to the first ... | 01/20/1998 |
| 5704763 | Shear jet cooling passages for internally cooled machine elements A cooling passageway construction particularly adapted for cooling the interior of a heated turbine engine assembly and/or airfoil blade includes an undulating partition which subdivides the passageway into first and second subpassages. The partition defi... | 01/06/1998 |
| 5702230 | Actively controlled acoustic treatment panel An actively controlled acoustic treatment panel for suppressing noise in a gas turbine engine nacelle including a backsheet formed by a planar matrix of adjacent individually controllable elements, where each of the controllable elements has a transducer ... | 12/30/1997 |
| 5694768 | Variable cycle turbofan-ramjet engine An improved variable cycle turbofan-ramjet engine is disclosed. The engine includes a split fan assembly, a bypass channel surrounding a core engine and a mode selector valve for selectively bypassing air around an aft fan and the core engine. In a first,... | 12/09/1997 |
| 5690472 | Internal cooling of turbine airfoil wall using mesh cooling hole arrangement A turbine airfoil has a mesh cooling hole arrangement which includes first and second pluralities of cooling holes formed within the interior structure of the side walls of the airfoil so as to extend between and along but not intersect spaced internal an... | 11/25/1997 |
| 5690280 | Multifunction exhaust system for gas turbine engines A short take off and vertical landing (STOVL) nozzle for a jet aircraft provides thrust reversing and thrust vectoring functions using two pairs of flaps. Each flap is independently actuated and controlled to allow for numerous exhaust gas exit configurat... | 11/25/1997 |
| 5689435 | Systems and methods for automated bracket design A design system for designing brackets for gas turbine engines is described. The system may be implemented with a computer workstation and includes a part model library and a drawing note library. The computer workstation is configured to receive a bracke... | 11/18/1997 |
| 5683225 | Jet engine variable area turbine nozzle A turbine nozzle for a gas turbine engine subassembly having an axial turbine. The turbine nozzle airfoil-shaped vanes are fixedly attached to one or both of the annular inner and outer casings. Apparatus is provided to vary the vane airflow passage area ... | 11/04/1997 |
| 5680767 | Regenerative combustor cooling in a gas turbine engine A combustor, for a gas turbine engine, employing regenerative combustor cooling. The combustion gas flow direction extends generally longitudinally aft of the combustor fuel nozzle. A coolant flowpath between the combustor casing and the combustor liner h... | 10/28/1997 |
| 5660525 | Film cooled slotted wall 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 slot extends inwardly f... | 08/26/1997 |
| 5660524 | Airfoil blade having a serpentine cooling circuit and impingement cooling An airfoil blade, such as a jet engine turbine rotor blade. An internal serpentine coolant circuit has a last downstream passageway bounded by four monolithic inner walls which are monolithic with at least a portion of the outer walls. Two of the inner wa... | 08/26/1997 |
| 5660523 | Turbine blade squealer tip peripheral end wall with cooling passage arrangement A turbine blade squealer tip has a cooling passage arrangement which includes a peripheral end wall surrounding a central portion of an end cap of the squealer tip, an outer peripheral groove defined in an outer surface of the peripheral end wall being sp... | 08/26/1997 |
