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| Number | Title | Issue Date |
| 5820024 | Hollow nozzle actuating ring A hollow actuating ring and apparatus for actuating and/or vectoring the flaps of an aircraft gas turbine engine nozzle by transferring actuation loads from a small number of actuators to a greater number of pivotal divergent flap members of the nozzle. T... | 10/13/1998 |
| 5807072 | Variable stator vane assembly A variable stator vane assembly which substantially eliminates leakage paths by utilizing a cantilevered finger spring seal and an o-ring is described. In one form, the stator vane assembly includes a spacer configured to form, with an upper, or outer, su... | 09/15/1998 |
| 5778676 | Dual fuel mixer for gas turbine combustor An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct in which a fuel manifold is provided in flow communication with a fuel supply and control means, a set of inner and outer counter-rotating swirle... | 07/14/1998 |
| 5775092 | Variable size gas turbine engine A simple cycle gas turbine engine which includes a variable flow booster, a small high pressure compressor, and a power turbine is described. The variable flow booster, which includes a low pressure compressor, has at least two flow paths. In one embodime... | 07/07/1998 |
| 5768884 | Gas turbine engine having flat rated horsepower A gas turbine engine operable so that, in one embodiment, by adjusting the speed of an intercooler fan, the orientation of a variable inlet guide vane, and the orientation of a variable area turbine nozzle, the conditions at the inlet of the high pressure... | 06/23/1998 |
| 5749705 | Retention system for bar-type damper of rotor blade 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... | 05/12/1998 |
| 5749701 | Interstage seal assembly for a turbine A seal assembly positioned between forward and aft rotor stages of a turbine separates a forward cavity and an aft cavity on each side thereof. The seal assembly includes a seal body connected to a platform portion of a stator nozzle located between the f... | 05/12/1998 |
| 5740988 | Axisymmetric vectoring nozzle actuating system having multiple power control circuits A failsafe nozzle actuating system for an aircraft gas turbine engine axisymmetric vectoring exhaust nozzle has a vectoring ring operably linked to a plurality of pivotal flaps which are circumferentially disposed about a nozzle centerline and bounding an... | 04/21/1998 |
| 5732546 | Transient turbine overtemperature control A gas turbine engine includes a compressor joined to a turbine by a core rotor, with a combustor disposed therebetween for receiving compressed air from the compressor and fuel through a valve for producing combustion gas discharged to the turbine. A spee... | 03/31/1998 |
| 5720434 | 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... | 02/24/1998 |
| 5703362 | Method for nondestructive/noncontact detection and quantification of alpha case on a surface of a workpiece made of titanium or a titanium-based alloy A method for nondestructive/noncontact detection of alpha case on a surface of a workpiece made of titanium or a titanium-based alloy. Infrared radiation is reflected off of a selected portion of the workpiece surface and sensed by a detector which may co... | 12/30/1997 |
| 5701733 | Double rabbet combustor mount A combustor mount joins a mounting arm of a combustor to a conical nozzle support of a turbine nozzle. The mounting arm includes a conical mounting flange having first and second axially spaced apart radial lands and a plurality of circumferentially space... | 12/30/1997 |
| 5699966 | Exhaust nozzle of a gas turbine engine An exhaust nozzle of a gas turbine engine effective for reducing the emission of infrared radiation and providing an extensive maneuvering capability. The nozzle preferably is of the two-dimensional type and includes an exhaust cowl with a generally recta... | 12/23/1997 |
| 5695322 | Turbine blade having restart turbulators A turbine blade includes an airfoil having first and second opposite sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. A single restart turbulator rib is disposed in the passage adjacent to the inl... | 12/09/1997 |
| 5695321 | Turbine blade having variable configuration turbulators A turbine blade includes an airfoil having opposite first and second sides and an internal passage extending longitudinally therebetween. A plurality of turbulator ribs extend from the first side into the passage and have substantially identical configura... | 12/09/1997 |
| 5695320 | Turbine blade having auxiliary turbulators A gas turbine blade includes an airfoil having first and second sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. A plurality of longitudinally spaced apart primary turbulator ribs extend into the ... | 12/09/1997 |
| 5694767 | Variable slot bypass injector system An afterburning, gas turbine aircraft engine with an annular duct for carrying bypass airflow is provided with a sliding valve type of rear Variable Area Bypass Injector (VABI) system. This rear VABI varies the direction and volume of the flow of bypass a... | 12/09/1997 |
| 5694760 | Cumbustor lean flameout control A gas turbine engine includes a controller configured for controlling combustor lean flameout. The engine includes a compressor joined to a turbine by a core rotor, with a combustor disposed therebetween for receiving compressed air and fuel for generatin... | 12/09/1997 |
| 5690473 | Turbine blade having transpiration strip cooling and method of manufacture A gas turbine engine turbine blade and method of manufacture includes an airfoil having pressure and suction sides joined together at leading and trailing edges. The airfoil further includes a supply channel for receiving compressed air, and has an elonga... | 11/25/1997 |
| 5685157 | Acoustic damper for a gas turbine engine combustor An apparatus for suppressing or attenuating acoustic pressure oscillations in a gas turbine engine combustor, the apparatus having a quarter wave resonator with a cavity closed at a first end and open at a second end and a characteristic length that refle... | 11/11/1997 |
| 5682747 | Gas turbine combustor heat shield of casted super alloy A heat shield for a gas turbine engine combustor of the type composed of multiple annular stages. The heat shield is particularly adapted for use in a middle stage disposed between radially inward and outward stages of a multistage combustor, and configur... | 11/04/1997 |
| 5681144 | Turbine blade having offset turbulators A gas turbine engine blade includes an airfoil having first and second sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. Respective pluralities of first and second turbulator ribs extend inwardly f... | 10/28/1997 |
| 5680766 | Dual fuel mixer for gas turbine combustor An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct in which a fuel manifold is provided in flow communication with a fuel supply and control means, a set of inner and outer counter-rotating swirle... | 10/28/1997 |
| 5680755 | Convertible ejector selectively cooled thrust vectoring exhaust nozzle A nozzle cooling system for selectively cooling longitudinally extending and circumferentially adjacent divergent exhaust flow confining elements bounding a hot exhaust gas flowpath in a divergent section of an aircraft gas turbine engine exhaust nozzle a... | 10/28/1997 |
| 5680754 | Compressor splitter for use with a forward variable area bypass injector The present invention is a unique splitter of a core engine compressor in a double bypass, variable cycle engine. The splitter is extended forward to a second fan section. The extended splitter may divide the rotor blades into outer and inner portions to ... | 10/28/1997 |
| 5675971 | Dual fuel mixer for gas turbine combustor An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct in which a fuel manifold is provided in flow communication with a fuel supply and control means, a set of inner and outer counter-rotating swirle... | 10/14/1997 |
| 5669757 | Turbine nozzle retainer assembly A turbine nozzle assembly includes an outer casing having first and second spaced apart support flanges for supporting a nozzle segment including a plurality of nozzle vanes extending between inner and outer bands. The outer band includes first and second... | 09/23/1997 |
| 5657633 | Centerbody for a multiple annular combustor A multiple annular combustor for a gas turbine engine is disclosed having a plurality of concentrically disposed annular combustion zones about a centerline axis. The multiple annular combustor includes a first annular combustion zone, a second annular co... | 08/19/1997 |
| 5655876 | Low leakage turbine nozzle A turbine nozzle includes a circumferentially continuous annular outer band, and a plurality of circumferentially spaced apart vanes extending radially inwardly therefrom. A circumferentially segmented inner band is joined to the vanes and is disposed coa... | 08/12/1997 |
| 5641267 | Controlled leakage shroud panel A shroud panel for a turbine shroud includes forward and aft hooks which are used to support the panel radially above a plurality of turbine rotor blades. The panel forward hook has radially outer and inner lands, with the outer land being defined by a pl... | 06/24/1997 |
| 5639212 | Cavity sealed compressor A compressor includes an axially split casing surrounding stages of rotor blades and stator vanes. The vanes include a shroud joined to radially inner ends thereof and disposed in a cavity adjoining a rotor disk. An annular cavity seal abuts the vane shro... | 06/17/1997 |
| 5638682 | Air fuel mixer for gas turbine combustor having slots at downstream end of mixing duct An air fuel mixer is disclosed having a mixing duct, a set of inner and outer counter-rotating swirlers adjacent the upstream end of the mixing duct, and a hub separating the inner and outer swirlers to allow independent rotation thereof, wherein high pre... | 06/17/1997 |
| 5634767 | Turbine frame having spindle mounted liner A turbine frame includes annular outer and inner bands with circumferentially spaced apart struts extending therebetween. Annular outer and inner liners adjoin the outer and inner bands, and a plurality of fairings surround respective ones of the struts a... | 06/03/1997 |
| 5632600 | Reinforced rotor disk assembly A reinforced rotor disk assembly includes a rotor disk having a rim, hub, and web therebetween. The web includes at least one annular extension spaced radially inwardly of the rim. A plurality of rotor blades extend outwardly from the rim. And, a reinforc... | 05/27/1997 |
| 5630703 | Rotor disk post cooling system A cooling system for use in a rotor assembly of a gas turbine engine, the rotor assembly including an annular disk rotatable about a centerline axis of the engine and a plurality of blades mounted on the disk. The disk includes alternating posts and slots... | 05/20/1997 |
| 5630700 | Floating vane turbine nozzle A turbine nozzle includes outer and inner bands having respective mounting holes therein. A plurality of vanes extends through respective pairs of outer and inner holes in the bands. The vane outer and inner ends are resiliently supported to the bands to ... | 05/20/1997 |
| 5630319 | Dome assembly for a multiple annular combustor A dome assembly for a multiple annular combustor is disclosed as including an annular dome plate having at least two radial domes, wherein each of the radial domes include a plurality of circumferentially spaced openings therein. A heat shield is position... | 05/20/1997 |
| 5628621 | Reinforced compressor rotor coupling A compressor rotor includes a rim having airfoils extending radially outwardly therefrom, and a corresponding web and hub extending radially inwardly. A row of curvic coupling teeth extends axially away from one end of the rim. An imperforate support ring... | 05/13/1997 |
| 5622475 | Double rabbet rotor blade retention assembly A turbine rotor assembly includes a rotor disk, rotor blades joined thereto, and a blade retention plate for axially retaining the blades on the disk. The disk includes an outer rim, an inner hub, and an annular web extending therebetween. An axial extens... | 04/22/1997 |
| 5622473 | Variable stator vane assembly A variable stator vane assembly which substantially eliminates leakage paths by utilizing a cantilevered finger spring seal and an o-ring is described. In one form, the stator vane assembly includes a spacer configured to form, with an upper, or outer, su... | 04/22/1997 |
