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A self defense weapon formed as a memo pad and which is easily held by a person's fingers, therefore making it possible to provide protection from a mugger and also to quickly and easily write a record or a message without failure of missing or forgetting significant information under a stressful situation.
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| Number | Title | Issue Date |
| 8166748 | Gas turbine engine booster having rotatable radially inwardly extending blades and non-rotatable vanes A gas turbine engine booster includes one or more rotatable booster stages having booster blades extending radially inwardly from a rotatable drum and one or more non-rotatable vane stages having booster vanes extending radially outwardly from a non-rotatable shell.... | 05/01/2012 |
| 8096106 | Drive mechanism A drive mechanism comprising a first sprocket encircled by a tensioned chain and an orbit sprocket arranged to orbit the first sprocket in response to a resynchronisation signal. The orbit sprocket is arranged to displace the tensioned chain relative to the first sp... | 01/17/2012 |
| 8015798 | Geared counter-rotating gas turbofan engine A gas turbine engine includes a gear system driven by a first and second counter rotating low pressure shaft and a fan driven by the gear system. ... | 09/13/2011 |
| 7984607 | Gas turbine engine systems and related methods involving vane-blade count ratios greater than unity Gas turbine engine systems and related methods involving vane-blade count ratios greater than unity are provided. In this regard, a representative turbine stage for a gas turbine engine includes a first set of rotatable blades operative to be positioned downstream o... | 07/26/2011 |
| 7950220 | Turbine engine compressor A counter-rotating blade stage in lieu of a stator stage may compensate for relatively low rotational speed of a gas turbine engine spool. A first spool may have at least two compressor blade stage and at least two turbine blade stage. A combustor is located between... | 05/31/2011 |
| 7832193 | Gas turbine engine assembly and methods of assembling same A method of assembling a gas turbine assembly includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine, coupling a low-pressure turbine to the core gas turbine engine, coupling a booster compressor to a gearbox, a... | 11/16/2010 |
| 7765789 | Apparatus and method for assembling gas turbine engines A gas turbine engine assembly is provided. The gas turbine engine assembly includes a core engine. The gas turbine engine assembly further includes a first rotor spool including a first fan assembly, an intermediate-pressure turbine, and a first shaft. The first fan... | 08/03/2010 |
| 7752836 | Gas turbine assembly and methods of assembling same A method for assembling a gas turbine engine includes coupling a gearbox to a low-pressure turbine, the gearbox includes a plurality of planetary gears intermeshed with the sun gear, each of the planetary gears includes a first gear portion having a first diameter a... | 07/13/2010 |
| 7716914 | 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 disposed downstream from the high-pressure compressor, and a high-pressure turbine coupled to the high-pressure compressor using a shaft, counter-rotating... | 05/18/2010 |
| 7685808 | Gas turbine engine assembly and methods of assembling same A method for assembling a gas turbine engine includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine, and coupling a counter-rotating fan assembly to the core gas turbine engine such that air discharged from the ... | 03/30/2010 |
| 7603844 | Gas turbine engine assembly and methods of assembling same A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a gearbox to the low-pressure turbine, coupling a first fan assembly to the gearbox such that the first fan assembly rotates in a first direction... | 10/20/2009 |
| 7526913 | Gas turbine engine assembly and methods of assembling same A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a gearbox including an input, a first output, and a second output, to the low-pressure turbine, coupling a first fan assembly to the gearbox firs... | 05/05/2009 |
| 7513102 | Integrated counterrotating turbofan A turbofan engine includes a fan, compressor, combustor, single-stage high pressure turbine, and low pressure turbine joined in serial flow communication. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pr... | 04/07/2009 |
| 7513103 | Gas turbine engine assembly and methods of assembling same A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine such that the forwar... | 04/07/2009 |
| 7493753 | Gas turbine engine assembly and methods of assembling same A method facilitates assembling a gas turbine engine. The method comprises coupling a low-pressure turbine rotatable about a drive shaft to a counter-rotating fan assembly including a first fan assembly and a second fan assembly wherein the first fan assembly rotate... | 02/24/2009 |
| 7493754 | Gas turbine engine assembly and methods of assembling same A method for assembling a gas turbine engine including providing a core gas turbine engine at least partially defined by a frame and having a drive shaft rotatable about a longitudinal axis of the core gas turbine engine. A low-pressure turbine is coupled to a core ... | 02/24/2009 |
| 7490460 | Gas turbine engine assembly and methods of assembling same A gearbox includes a support structure, at least one sun gear coupled within the support structure, and a plurality of planetary gears coupled within the support structure. The support structure includes a first portion, an axially aft second portion, and a thrust s... | 02/17/2009 |
| 7490461 | Gas turbine engine assembly and methods of assembling same A method for assembling a gas turbine engine including providing a core gas turbine engine at least partially defined by a frame. The gas turbine engine has a drive shaft that is rotatable about a longitudinal axis of the core gas turbine engine. A counter-rotating ... | 02/17/2009 |
| 7451592 | Counter-rotating turbine engine including a gearbox A turbine engine arrangement is provided in which contra rotating shafts 104, 105 are respectively secured to a fan and a gearbox 106 which is also coupled to the shaft 104. In such circumstances the relative rotational speed ratio between the s... | 11/18/2008 |
| 7412819 | Turbojet architecture with two fans at the front A turbojet has a low-pressure compressor and two fans at the front of an intermediate casing which fans are driven by two independent shafts. The compressor is disposed under the rear fan and has a downstream ring of rotor blades connecting the rear fan to the drive... | 08/19/2008 |
| 7409819 | Gas turbine engine and method of assembling same A method of assembling a gas turbine engine that includes rotatably coupling a first low-pressure turbine rotor to a high-pressure turbine, rotatably coupling a second low pressure turbine rotor to the first low-pressure turbine rotor, and rotatably coupling the sec... | 08/12/2008 |
| 7395657 | Flade gas turbine engine with fixed geometry inlet An aircraft propulsion system includes a gas turbine engine having a fan section, at least one row of FLADE fan blades disposed radially outwardly of and drivingly connected to the fan section, the row of FLADE fan blades radially extending across a FLADE duct circu... | 07/08/2008 |
| 7334392 | Counter-rotating gas turbine engine and method of assembling same A method for assembling a gas turbine engine includes providing a first fan assembly including a plurality of rotor blades that are configured to rotate in a first rotational direction at a first rotational speed, rotatably coupling a second fan assembly axially aft... | 02/26/2008 |
| 7299621 | Three-spool by-pass turbojet with a high by-pass ratio The invention relates to aerodynamically matching the rear fan of a turbojet having two fans and a low-pressure compressor at the front of the intermediate casing, said fans being driven by two independent shafts. Said compressor is disposed between the blades of th... | 11/27/2007 |
| 7296398 | Counter-rotating turbine engine and method of assembling same A method for assembling a gas turbine engine that includes providing a first fan assembly configured to rotate in a first rotational direction, rotatably coupling a second fan assembly to the first fan assembly, wherein the second fan assembly is configured to rotat... | 11/20/2007 |
| 7290386 | Counter-rotating gas turbine engine and method of assembling same A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor that includes a first plurality of turbine blade rows configured to rotate in a first direction, and rotatably coupling a low-pressure turbine outer rotor to the ... | 11/06/2007 |
| 7246484 | FLADE gas turbine engine with counter-rotatable fans An exemplary embodiment of a FLADE counter-rotating fan aircraft gas turbine engine includes at least one row of FLADE fan blades disposed radially outwardly of and drivingly connected to one of axially spaced-apart first and second counter-rotatable fans. A core en... | 07/24/2007 |
| 7237378 | Turbomachine with low noise emissions for aircraft The invention relates to a turbomachine (1) for an aircraft comprising a gas generator (4) designed such that hot gases are ejected from a combustion chamber (28) towards the upstream side of the turbomachine, and also comprising a plurality of ... | 07/03/2007 |
| 7055303 | Gas turbine engine architecture A gas turbine engine having an oil cavity architecture and bearing placement which reduce heat rejection and oil system complexity by enclosing the reduction gearbox bearings and at least the shaft bearings supporting the high pressure shaft in the same oil cavity. | 06/06/2006 |
| 7048496 | Turbine cooling, purge, and sealing system A rotor system for a gas turbine engine is provided having an outer rotor which includes an annular outer spool that comprises at least one ring portion of increased thickness with respect to the remainder of the outer spool, attached to a relatively thinner, axiall... | 05/23/2006 |
| 6988357 | Nested core gas turbine engine A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section. ... | 01/24/2006 |
| 6935837 | Methods and apparatus for assembling gas turbine engines A method enables a gas turbine engine including a first rotor assembly and a second rotor assembly coupled in axial flow communication downstream from the first rotor assembly to be assembled. The method comprises coupling an upstream end of an extension duct to an ... | 08/30/2005 |
| 6763652 | Variable torque split aircraft gas turbine engine counter rotating low pressure turbines An aircraft gas turbine engine includes a low pressure turbine having a low pressure turbine flowpath and low pressure inner and outer shaft turbines with counter rotatable low pressure inner and outer shaft turbine rotors, respectively. The low pressure inner and o... | 07/20/2004 |
| 6739120 | Counterrotatable booster compressor assembly for a gas turbine engine A counterrotatable booster compressor assembly for a gas turbine engine having a counterrotatable fan section with a first fan blade row connected to a first drive shaft and a second fan blade row axially spaced from the first fan blade row and connected to a second... | 05/25/2004 |
| 6732502 | Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor An aircraft gas turbine engine includes high and low pressure turbines having respective counter rotatable low pressure inner and outer rotors with low pressure inner and outer shafts in part rotatably disposed co-axially within a high pressure rotor and drivingly c... | 05/11/2004 |
| 6684626 | Aircraft gas turbine engine with control vanes for counter rotating low pressure turbines An aircraft gas turbine engine includes a low pressure turbine having a low pressure turbine flowpath and counter rotatable low pressure inner and outer shaft rotors having inner and outer shafts, respectively. The low pressure inner and outer shaft rotor... | 02/03/2004 |
| 6666017 | Counterrotatable booster compressor assembly for a gas turbine engine A counterrotatable booster compressor assembly for a gas turbine engine having a counterrotatable fan section with a first fan blade row connected to a first drive shaft and a second fan blade row axially spaced from the first fan blade row and connected ... | 12/23/2003 |
| 6647707 | Nested core gas turbine engine A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section.... | 11/18/2003 |
| 5443590 | Rotatable turbine frame A rotatable turbine frame includes annular outer and inner bands having a plurality of circumferentially spaced apart struts extending therebetween. An annular drive shaft is fixedly joined to the inner band for transmitting output torque therefrom, and t... | 08/22/1995 |
| 5361580 | Gas turbine engine rotor support system A gas turbine engine rotor support system includes outer and inner rotors having respective outer and inner blades interdigitated in respective blade row stages. A stationary rear frame includes a rear support shaft. A rotatable aft frame is disposed forw... | 11/08/1994 |
