Bizarre Patents
Combination Beverage Container and Spittoon
A combination beverage container and spittoon includes a bottom portion including outer wall and a first inner wall defining a spittoon space.
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| Number | Title | Issue Date |
| 8186144 | Component ventilation and pressurization in a turbomachine A dual-flow turbomachine (10), essentially comprising a fan (14), a compressor (20), a combustion chamber (21), a turbine (22) and an exhaust casing (24), which comprises an auxiliary air compressor (48) driven by a S... | 05/29/2012 |
| 8181442 | Gas turbine aircraft engine with power variability A gas turbine aircraft engine with power variability is provided. The gas turbine aircraft engine comprises a compressor and a turbine mounted on a common shaft, and, a continuously variable transmission coupled to the shaft for transmitting power to a propulsion lo... | 05/22/2012 |
| 8181443 | Heat exchanger to cool turbine air cooling flow A cooling system of a gas turbine engine, includes a heat exchanger having a common wall shared by a first air passage for directing a portion of a compressor air flow to be used as cooling air, and a second air passage for directing a portion of a bypass air flow, ... | 05/22/2012 |
| 8176725 | Reversed-flow core for a turbofan with a fan drive gear system A gas turbine engine comprises a fan drive gear system, a low spool connected to the fan drive gear system, and a high spool disposed aft of the low spool. The low spool comprises a rearward-flow low pressure compressor disposed aft of the fan drive gear system, and... | 05/15/2012 |
| 8141337 | Dual flow turbine engine equipped with a precooler A bypass turbine engine includes a precooler having an annular cross-sectional shape about the axis of a pod and arranged inside the rear part of an inner shroud in contact with a cold fluid exiting a fan duct. ... | 03/27/2012 |
| 8127528 | Auxiliary propulsor for a variable cycle gas turbine engine A core engine of a variable cycle gas turbine engine includes a low pressure spool for generating streams of bypass air and pressurized air, and a high pressure spool for further pressurizing the stream of pressurized air to generate streams of combustion air and su... | 03/06/2012 |
| 8099944 | Hybrid propulsive engine including at least one independently rotatable propeller/fan A hybrid propulsive technique includes providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine. The hybrid propulsive technique comprises extracting energy from the working fl... | 01/24/2012 |
| 8082726 | Tangential anti-swirl air supply A turbofan flow delivery system includes a fan case housing a fan. Flow exit guide vanes are arranged downstream from the fan and extend radially inwardly from the fan case toward a bypass flow path. A supply passage includes an opening provided in the fan case betw... | 12/27/2011 |
| 8082727 | Rear propulsor for a variable cycle gas turbine engine A gas turbine propulsion system comprises a turbofan engine, a peripheral duct, an annular frame, an auxiliary turbine and an auxiliary fan. The turbofan engine is configured to produce bypass air and combustion air. The bypass air flows through a bypass duct and th... | 12/27/2011 |
| 8065867 | Radial ball bearing A bearing assembly includes an outer race and an inner race with a ball bearing element located between the inner and the outer races. The inner race has a first portion and a second portion separated from the first portion by a split. The first portion includes a f... | 11/29/2011 |
| 8033094 | Cantilevered tip turbine engine A tip turbine engine (10) according to the present invention includes an engine support structure (12) for cantilevering a load bearing shaft from an engine support plane (P). An engine support structure (12) defines the engine support plane (P)... | 10/11/2011 |
| 8028513 | Variable bypass turbine fan An engine for powering a vehicle, such as a military aircraft or a commercial aircraft, is provided. The engine broadly comprises a main core with a plurality of spools with each spool having a plurality of compressor blades and a plurality of turbine blades attache... | 10/04/2011 |
| 8015796 | Gas turbine engine with dual fans driven about a central core axis A gas turbine engine includes a compressor section, a combustor section and a turbine section, all arranged about a central axis. A turbine rotor drives a driveshaft for rotation on the central axis. The driveshaft in turn drives at least two fan rotors on axes para... | 09/13/2011 |
| 7966806 | Turbofan engine assembly and method of assembling same A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a low-pressure turbine coupled to said core gas turbine engine, a counter-rotating booster compressor comprising a first rot... | 06/28/2011 |
| 7966807 | Vapor cooled static turbine hardware A cooling system for a gas turbine engine includes a non-rotating component extending into an engine flowpath, a vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condens... | 06/28/2011 |
| 7963098 | Composite duct assembly A carbon composite duct assembly has a duct body having an opening. The duct body extends along an axis. The opening extends transversely to the axis. The duct body has a carbon composite fabric layer. The duct body has an axial flange extending along the axis and a... | 06/21/2011 |
| 7946104 | Bleed air relief system for engines A bleed air relief system for engines in which a flow of bleed air from the engine compressor is passed along a bleed air duct and exhausted into a bypass air stream passing through the engine. A cover is mounted over the outlet of the bleed air duct and can include... | 05/24/2011 |
| 7926260 | Flexible shaft for gas turbine engine A shaft for a gas turbine engine is provided that includes a first shaft section, a second shaft section, a first flexible linkage, and a second flexible linkage. The first shaft section extends between a forward axial end and an aft axial end along a first axial ce... | 04/19/2011 |
| 7921637 | High bypass-ratio turbofan jet engine To provide a turbofan jet engine which is capable of increasing the bypass ratio without increasing the fan diameter, and of reducing air resistance acting on the engine, a front fan duct that discharges air compressed by a front fan to the atmosphere and an aft fan... | 04/12/2011 |
| 7921635 | Peripheral combustor for tip turbine engine A tip turbine engine (40) provides a peripheral combustor (30) with a more efficient combustion path through the combustor and through the tip turbine blades (34). In the combustor, the core airflow is received generally axially from compressor ... | 04/12/2011 |
| 7921636 | Tip turbine engine and corresponding operating method A tip turbine engine has a more efficient core airflow path from the hollow fan blades, through the combustor and to the combustion chamber of a combustor. The turbine engine includes a rotatable fan having a plurality of radially-extending fan blades each defining ... | 04/12/2011 |
| 7900433 | Fan exhaust nozzle for turbofan engine The cross sectional flow area of a fan discharge nozzle on one side of a central plane of an associated gas turbine engine power plant is greater than the corresponding flow area of the fan discharge nozzle on an opposite side of the central plane to compensate for ... | 03/08/2011 |
| 7886518 | Turbofan engine cowl assembly and method of operating the same An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan no... | 02/15/2011 |
| 7882695 | Turbine blow down starter for turbine engine In order to start a turbine engine (10), high-pressure fluid is directed onto a turbine (34a) to cause rotation of the turbine and thereby start the turbine engine. In a disclosed embodiment, the high-pressure fluid is provided through a fluid o... | 02/08/2011 |
| 7882694 | Variable fan inlet guide vane assembly for gas turbine engine A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly couple... | 02/08/2011 |
| 7877980 | Convertible gas turbine engine A gas turbine engine includes a turbomachinery core operable to generate a flow of pressurized combustion gases at a variable flow rate, while maintaining a substantially constant core pressure ratio; a rotating fan disposed upstream of the core, the fan adapted to ... | 02/01/2011 |
| 7870722 | Systems and methods for passively directing aircraft engine nozzle flows Systems and methods for passively directing aircraft engine nozzle flow are disclosed. One system includes an aircraft nozzle attachable to an aircraft turbofan engine, with the nozzle including a first flow path wall bounding a first flow path and being positioned ... | 01/18/2011 |
| 7870721 | Gas turbine engine providing simulated boundary layer thickness increase A nacelle assembly for a gas turbine engine includes a fan cowl disposed about an axis, a core cowl within the fan cowl and a bleed passage having an inlet that receives a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from th... | 01/18/2011 |
| 7866141 | Cooling device for the primary nozzle of a dual-flow turbojet engine The invention relates to a dual-flow turbojet engine comprising an engine which is disposed in a nacelle and is provided with case which defines jointly with the said nacelle an annular passage through which a secondary flow supplied by a fan placed upstream of the ... | 01/11/2011 |
| 7861513 | Aeroengine ventilation system A gas turbine engine comprising a ventilation zone defined between a core engine casing and a core fairing and having a discharge nozzle, the engine further comprises a pre-cooler having a flow of coolant therethrough and which coolant being ducted into the ventilat... | 01/04/2011 |
| 7861512 | Turbofan bypass duct air cooled fluid cooler installation A cooling apparatus for cooling a fluid in a bypass gas turbine engine comprises a heat exchanger disposed within a bypass duct and accommodated by a sub-passage defined by a flow divider affixed to an annular wall of the bypass duct. The sub-passage defines an open... | 01/04/2011 |
| 7854112 | Vectoring transition duct for turbine engine A transition duct (112) is provided at the outlet of a turbine engine. The transition duct transitions the outlet of the tip turbine engine (10) from round to rectangular. The transition duct also provides a plurality of variable vanes at the outlet of... | 12/21/2010 |
| 7845157 | Axial compressor for tip turbine engine A tip turbine engine (10) according to the present invention provides at least one gear (90) coupling rotation of a bypass fan (24) to an axial compressor (22), such that the axial compressor (22) is driven by rotation of the fan (... | 12/07/2010 |
| 7845158 | Turbine engine mounting arrangement An engine mounting arrangement is provided in which a mounting structure is created through fins (21, 42) extended between a core (22, 46) and a mounting ring (23, 48). The fins (21, 42) have a tangential lean and substantive planar aspec... | 12/07/2010 |
| 7845156 | Turbofan exhaust system A turbofan exhaust system includes at least one exhaust nozzle with a trailing edge having an upper edge, a lower edge, an inner lateral edge-and an outer lateral edge. The upper edge is upstream with respect to the lower edge. The outer lateral edge of the exhaust ... | 12/07/2010 |
| 7836680 | Aircraft combination engines thermal management system An engine combination for generating forces with a gas turbine engine generating force that utilizes an engine lubricant for lubricating moving components in the turbofan engine, and an internal combustion engine provided in the combination as an intermittent combus... | 11/23/2010 |
| 7818958 | Jet engine nacelle for an aircraft and aircraft comprising such a nacelle A nacelle for an aircraft high-bypass jet engine, in which a jet engine having a longitudinal axis is mounted, the nacelle including a wall concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct for fluid inner ... | 10/26/2010 |
| 7797922 | Gas turbine engine case and method of making A casing for an aircraft turbine bypass engine comprises a splitter having slots to receive and be welded to a plurality of struts extending between an outer ring and an inner hub of the casing. ... | 09/21/2010 |
| 7793488 | Turbofan case and method of making A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed. ... | 09/14/2010 |
| 7788899 | Fixed nozzle thrust augmentation system A thrust augmentation system for a mixed exhaust turbofan engine comprises an augmentation duct, a combustion system and a fixed area exhaust nozzle. The augmentation duct receives primary and secondary air of the turbofan engine and is positioned co-axially with an... | 09/07/2010 |
