Bizarre Patents
Self Containing Enclosure for Protection from Killer Bees
A self contained protective enclosure with an opening for entry and egress and a screen for ventilation and viewing.
PatentStorm News
Make the Most of Our Site
See this month's Top Inventors and Most Cited Patents.
Stay on top of the latest innovations by subscribing to an RSS feed.
Registered users: Manage your profile.
| Number | Title | Issue Date |
| 8182230 | Fan blade preloading arrangement and method The fan blade includes a blade root at one end thereof configured for sliding insertion into a substantially axially extending slot defined in a periphery of a fan rotor hub. The blade comprises a first passageway extending at least partially through the blade root,... | 05/22/2012 |
| 8182213 | Vane assembly with removable vanes A vane assembly for a gas turbine engine where each vane is connected to at least one adjacent portion of at least one of the inner and the outer shrouds through a melt-weld connection. The melt-weld connection includes non-metallic heat-meltable material with a met... | 05/22/2012 |
| 8182201 | Load distribution system for gas turbine engine There is provided an axial bearing load distribution system for a gas turbine engine of the type having a low pressure rotor supported by axial bearings. The system comprises a line having an inlet end positioned in a high-pressure compressor gas path downstream of ... | 05/22/2012 |
| 8182199 | Turbine shroud cooling system A method of cooling a shroud ring in a turbine section of gas turbine engine includes identifying a series of alternating high temperature regions and lower temperature regions of a circumferential temperature distribution about the inner surface of the shroud ring,... | 05/22/2012 |
| 8181465 | Positioning arrangement for components of a pressure vessel and method The positioning arrangement comprises at least one pair of complimentary rounded recesses, each recess being provided on the mating face of the corresponding component. One ball is positioned between each pair of complementary recesses. ... | 05/22/2012 |
| 8172514 | Rim seal for a gas turbine engine The rim seal is positioned in an annular space between blades and a non-rotating adjacent structure in a gas turbine engine. The rim seal is connectable to the non-rotating structure and is made of an abradable material. ... | 05/08/2012 |
| 8171739 | Internally mounted fuel manifold with support pins An apparatus for internally mounting a fuel manifold within a surrounding casing in a gas turbine engine which includes a fuel manifold and support pins which are displaceable relative to mounting portions on the fuel manifold between a retracted position, wherein t... | 05/08/2012 |
| 8171738 | Gas turbine internal manifold mounting arrangement A mounting system supporting and positioning an internal fuel manifold of a gas turbine engine includes at least a heat shield surrounding a fuel inlet of the fuel manifold, the heat shield bearing at least a portion of a load to support the fuel manifold. ... | 05/08/2012 |
| 8171736 | Combustor with chamfered dome A combustor for a gas turbine engine includes an annular combustor shell having an inner liner and an outer liner respectively with inner and outer flanges at least partly overlapping to form a dome end portion of the shell, at least the outer flange including inter... | 05/08/2012 |
| 8171634 | Method of producing effusion holes A method of producing a plurality of effusion holes in a wall of a combustor of a gas turbine engine comprises: determining a hole pattern definition which provides a functional relationship of the spacing between each adjacent hole within the row of holes; using th... | 05/08/2012 |
| 8169100 | Torque transmission for an aircraft engine The torque transmission system for an aircraft engine permits a starter-generator to drive the engine on starting at a speed reducing ratio. Once the engine is running, the engine then drives the starter-generator also at a speed reducing ratio. ... | 05/01/2012 |
| 8166767 | Gas turbine combustor exit duct and hp vane interface An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions locat... | 05/01/2012 |
| 8151422 | Guide tool and method for assembling radially loaded vane assembly of gas turbine engine The vane assembly has mating vane support and vane ring, the vane ring having a plurality of annularly interspaced radial loading elements which, when the vane ring is assembled to the vane support, are in a resiliently flexed state and exert corresponding annularly... | 04/10/2012 |
| 8146365 | Fuel nozzle providing shaped fuel spray A fuel injection nozzle for a gas turbine engine has a central fuel ejection nozzle and a plurality of airflow passages within the spray tip that include a first and second group of circumferentially spaced apart fuel-spray forming airflow passages disposed on oppos... | 04/03/2012 |
| 8099227 | Control of gas turbine engine Systems, devices, and methods for controlling a fuel supply for a turbine or other engine using direct and/or indirect indications of power output and optionally one or more secondary control parameters. ... | 01/17/2012 |
| 8097972 | Gas turbine with magnetic shaft forming part of a generator/motor assembly A gas turbine engine including a first shaft being one of a main shaft concentrically mounted to at least one turbine rotor and a tower shaft directly driven by the main shaft and extending generally radially therefrom, the first shaft having a reduced diameter port... | 01/17/2012 |
| 8096746 | Radial loading element for turbine vane A vane assembly for a gas turbine engine comprising a number of radial loading elements disposed between lugs of the vane ring and the vane support, such as to generate a radial load force against the vane ring. The radial load force prevents unwanted relative movem... | 01/17/2012 |
| 8096131 | Fuel inlet with crescent shaped passage for gas turbine engines An inlet tube within a gas turbine engine which includes a primary fuel channel and a secondary fuel channel formed in a cylindrical tube body. The secondary channel has a substantially crescent shaped cross-sectional area which is complementary in shape to the prim... | 01/17/2012 |
| 8096130 | Fuel conveying member for a gas turbine engine A gas turbine engine fuel conveying member in fluid flow communication with at least one fuel nozzle, the fuel conveying member having at least first and second member portions sealingly engaged to one another, and means for conveying fuel defined at a junction betw... | 01/17/2012 |
| 8092178 | Turbine blade for a gas turbine engine The turbine blade comprises an airfoil having opposite pressure and suction sidewalls extending from a platform to a free end tip and in a chordwise direction from a leading edge to a trailing edge. The blade has two winglets extending in a chordwise direction from ... | 01/10/2012 |
| 8092165 | HP segment vanes A stator vane segment, for constructing a circumferential array of like segments in a gas turbine engine, each segment in the array being separated by an axially extending joint from an adjacent segment and being releasably mounted to an outer engine casing. Each st... | 01/10/2012 |
| 8092145 | Particle separator and separating method for gas turbine engine A system and method for particle separation in a gas turbine engine centrifugal impeller bleed air system using a tangential velocity component of the compressor bleed air to centrifuge the particles radially outwardly and convey the particles circumferentially, awa... | 01/10/2012 |
| 8091367 | Combustor with improved cooling holes arrangement A gas turbine engine combustor liner with at least one of the inner and outer liners that is effusion cooled and has a row of groups of circumferentially spaced apart dilution holes defined therethrough. Each group is located within a respective zone of the combusto... | 01/10/2012 |
| 8076882 | Motor drive architecture with active snubber A method and apparatus is disclosed for controlling a system comprising at least one electric motor. The motor drive circuit includes a reconfigurable active snubber. Under given resonance conditions, the active snubber is configured to use a resistive element to di... | 12/13/2011 |
| 8075247 | Centrifugal impeller with internal heating An internal heating arrangement for a centrifugal impeller for a gas turbine engine is provided having at least one heating passage extending through into the rotor for directing air bled from the rotor exit along the backface and forwardly through the impeller.... | 12/13/2011 |
| 8074452 | Nested channel ducts for nozzle construction and the like A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel, adapted for conveying fuel flow, is formed in a surface of a gas turbine engine component. The channel includes at ... | 12/13/2011 |
| 8072113 | Inductance augmenter for an electric machine The electric machine comprises a rotor and stator, the rotor and stator having generally equal axial lengths. The stator has at least one primary and at least one control winding disposed around the stator. The electric machine comprises a stator extension of a magn... | 12/06/2011 |
| 8051664 | Pre-loaded internal fuel manifold support A system for mounting an internal fuel manifold within a gas generator case of a gas turbine engine includes at least one fastener support assembly having a fastener pin and at least one receiving element, respectively engaged to either the internal fuel manifold or... | 11/08/2011 |
| 8042752 | Nozzle repair to reduce fretting A method repair for reducing fretting of a fuel nozzle of a gas turbine engine, including attaching at least one stiffening element to an outer surface of a portion of a stem member of the fuel nozzle, with a size and shape of the at least one stiffening element bei... | 10/25/2011 |
| 8033786 | Axial loading element for turbine vane A vane assembly for a gas turbine engine comprising an axial loading element disposed between a mounting element of the vane ring and a cooperating portion of the supporting structure, such as to generate a load force therebetween in an axial direction. The axial lo... | 10/11/2011 |
| 8001793 | Gas turbine engine reverse-flow combustor A gas turbine engine reverse-flow sheet metal combustor for an aero gas turbine engine has a louverless single-piece liner design which includes a plurality of effusion patches, containing multiple rows of effusion cooling holes, bounded by cooled effusionless bands... | 08/23/2011 |
| 8000846 | Airborne electronics housing assembly An aircraft electronics housing assembly maintains the electronics unit at given ambient conditions despite changes in conditions outside the housing during the aircraft flight cycle. ... | 08/16/2011 |
| 7997140 | Method and apparatus for troubleshooting noise/vibration issues of rotating components There is provided a method for troubleshooting noise/vibration issues of rotating components, the method comprising: receiving an audio signal of the rotating components in operation; generating a frequency spectrum corresponding to the audio signal; selecting a fre... | 08/16/2011 |
| 7965052 | Motor driving system and method for starting a motor A method and system is provided for starting a motor which is useful, among other things, is useful for motors under unknown or variable load/inertia conditions. If a first attempt to start the motor using a first frequency ramp-up rate fails, a subsequent start att... | 06/21/2011 |
| 7950216 | Gas turbine engine fuel control system A fuel control system having a combustive energy value evaluator determining a combustive energy value of the fuel, and a controller calculating a desired flow rate based at least on the combustive energy value and controlling a fuel metering device such that the fu... | 05/31/2011 |
| 7949440 | Aircraft cruise speed control The present invention provides an alternative to the auto-throttle integrated in an aircraft autopilot by restricting the conditions in which the system operates. The proposed system removes the auto-throttle function from the autopilot system and gives it directly ... | 05/24/2011 |
| 7948139 | Magnetic control circuit separation slit An electric alternator/motor having a stator with at least two non-overlapping sectors is provided. Each sector includes a first winding, first and second magnetic circuits and a saturation control assembly. A cross-talk reduction feature, such as a peripheral slit ... | 05/24/2011 |
| 7937926 | Integral heater for fuel conveying member A fuel conveying member for an engine, the fuel conveying member having heating means integrated therein to permit pyrolysis of carbonaceous deposits. ... | 05/10/2011 |
| 7926286 | Heat shield for a fuel manifold A fuel injection system for a gas turbine engine having a manifold ring, a plurality of spray tip assemblies and a heat shield including at least two heat shield segments cooperating to at least substantially surround a cross-section of the manifold ring around a ci... | 04/19/2011 |
| 7919894 | Architecture for electric machine The invention includes an electric machine having a rotor, stator and at least one winding in the stator adapted to conduct a current, and a secondary winding, electrically isolated from the first winding and inductively coupled to the first winding, which may be us... | 04/05/2011 |
