Class / Patent application number | Description | Number of patent applications / Date published |
415124200 | Shaft transmission train having flexible means or coupling | 20 |
20100196141 | FUEL CELL COMPRESSOR SYSTEM - The invention provides a fuel cell compressor system that comprises a motor, including a motor shaft driven by the motor; a drive housing at least partially surrounding the motor shaft; a first gear set driven by the motor shaft; a carrier torque tube driven by the first gear set; and an impeller. The impeller includes an impeller shaft driven by the second gear set, so that the impeller shaft is configured to rotate at a speed greater than motor speed. Embodiments of the invention may also include a first bearing supporting the carrier torque tube and a second bearing supporting the impeller shaft. Embodiments of the invention may also include a seal system. | 08-05-2010 |
20110076136 | GAS COMPRESSOR MAGNETIC COUPLER - Provided in some embodiments is a gas compression system that includes a gas compressor having a drive shaft, an impeller drive shaft magnetically coupled to the drive shaft, and a shroud disposed between the drive shaft and the impeller drive shaft. In other embodiments provided is method that includes magnetically coupling a first drive shaft to a second drive shaft, receiving a rotational torque at the first drive shaft, transmitting the rotational torque from the first drive shaft to the second drive shaft via the magnetic coupling, and rotating a gas compressor impeller coupled to the second drive shaft. | 03-31-2011 |
20110188998 | Combustion exhaust energy conversion system - An energy conversion system that comprises a turbine rotor mounted inside an exhaust stack or chimney. The turbine is connected to a generator with a flexible drive shaft. | 08-04-2011 |
20120263579 | GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE - A gas turbine engine includes a central body support that provides an inner annular wall for a core flow path. The central body support includes first splines. A geared architecture interconnects a spool and a fan rotatable about an axis. A flex support interconnects the geared architecture to the central body support. The flex support includes second splines that intermesh with the first splines for transferring torque there between. | 10-18-2012 |
20130071233 | Device for Driving an Auxiliary Unit - A device for driving an auxiliary unit, in particular a high-pressure pump, includes a rotatably supported drive shaft of an internal combustion engine, wherein the drive shaft and a unit shaft of the auxiliary unit are operatively connected to each other by a coupling. The unit shaft has a first bearing on the side facing away from the coupling, and the coupling is a second bearing for the unit shaft. The device provides a low-cost, acoustically inconspicuous, tolerance-insensitive coupling solution for connecting, for example, a high-pressure pump camshaft to an available intake or exhaust camshaft. | 03-21-2013 |
20130129485 | PUMPING DEVICE THAT PROVIDES LINEAR CURRENT - A pumping device ensures that the fluid materials such as water and liquid are transmitted from one area to another area. The pumping device includes an outer flexible pipe forming an enclosed volume between a first suction area and a destination area, which has a flexible shaft through winch the rotational motion from the said pumping device is transferred and at least one impeller to which rotational motion is transferred through this flexible shaft and multiple centering components ensuring that the flexible shaft is centered and/or bedded inside the outer flexible pipe. | 05-23-2013 |
20130170958 | GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE - A gas turbine engine includes a central body support that provides an inner annular wall for a core flow path. The central body support includes a first mount feature. A geared architecture interconnects a spool and a fan rotatable about an axis. A flex support interconnects the geared architecture to the central body support. The flex support includes a second mount feature that cooperates with the first mount feature for transferring torque there between. A method of disassembling a front architecture of a gas turbine engine includes the steps of accessing forward-facing fasteners that secure a central body support to a flex support, wherein the flex support includes a geared architecture supported thereon, removing the fasteners, and decoupling first and second mount features respectively provided on the central body support and the flex support. | 07-04-2013 |
20130259657 | GAS TURBINE ENGINE GEARED ARCHITECTURE AXIAL RETENTION ARRANGEMENT - A support assembly for a geared architecture includes an engine static structure. A flex support is secured to the engine static structure and includes a bellow. A support structure is operatively secured to the flex support. A geared architecture is mounted to the support structure. First members are removably secured to one of the engine static structure and the flex support and second members are removably secured to the support structure. The first and second members are circumferentially aligned with one another and spaced apart from one another during a normal operating condition. The first and second members are configured to be engageable with one another during an extreme event to limit axial movement of the geared architecture relative to the engine static structure. | 10-03-2013 |
20130302144 | WIND TURBINE POWER TRANSMISSION SYSTEM - A power transmission system for increasing the rotational speed from a rotor of a wind turbine comprises a main shaft configured to be driven by the rotor, a support structure, and a gearbox. The support structure includes at least one bearing supporting the main shaft for rotation about the main axis, with no other degrees of freedom between the main shaft and support structure. The gearbox includes a gearbox housing rigidly coupled to the support structure and a gearbox input member coupled to the main shaft. The gearbox housing supports the gearbox input member for rotation about the main axis without any other degrees of freedom, and the gearbox input member is coupled to the main shaft with translational degrees of freedom in all directions and rotational degrees of freedom about axes perpendicular to the main axis. | 11-14-2013 |
20140140818 | GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE - A method for servicing a gas turbine engine includes disassembling a bearing compartment, providing access from a forward side of the gas turbine engine to a gearbox contained within said bearing compartment. The gas turbine engine provides a core flow path that extends from the forward side aftward in a core flow direction. The method includes servicing a component located within the bearing compartment. A method for servicing a gas turbine engine includes providing access from a forward side of a front center body assembly, and servicing a component located within a bearing compartment aft of the front center body assembly. The gas turbine engine includes a seal package located aft of a bearing package. A front wall is mounted to the front center body support and is removable from a front center body support to access at least one of the gearbox, the bearing package and the seal package. | 05-22-2014 |
20140140819 | Flexible Support Structure For A Geared Architecture Gas Turbine Engine - A gas turbine engine includes a fan shaft and a support which supports the fan shaft. The support defines a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines a flexible support lateral stiffness with respect to the support lateral stiffness. An input to the gear system defines an input lateral stiffness with respect to the support lateral stiffness. A method of designing a gas turbine engine is also disclosed. | 05-22-2014 |
20140161592 | GUIDANCE OF TURBINE ENGINE SHAFTS - Turbine engine ( | 06-12-2014 |
20140234079 | Geared Architecture for High Speed and Small Volume Fan Drive Turbine - A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system. | 08-21-2014 |
20140363276 | ULTRA HIGH BYPASS RATIO TURBOFAN ENGINE - An ultra high bypass ratio turbofan engine includes a variable pitch fan, a low pressure turbine, a reduction gearbox, and a plurality of outlet guide vanes. The ultra high bypass ratio turbofan engine has a bypass ratio between about 18 and about 40. The variable pitch fan and the low pressure turbine are coupled together by the reduction gearbox. The reduction gearbox reduces the speed of the variable pitch fan relative to the low pressure turbine. The plurality of outlet guide vanes are spaced aft of the variable pitch fan and are axially swept. The variable pitch fan and the low pressure turbine are configured to generate a fan pressure ratio between about 1.15 and about 1.24. | 12-11-2014 |
20150023785 | COUPLING FOR DIRECTLY DRIVEN COMPRESSOR - A coupling to attach an impeller of a compressor to a shaft of an electric motor. The coupling has a coupling body that is attached at a first of the ends thereof to the impeller and at the opposite second end, to the motor shaft. The coupling body has a deformable section between the first and second ends of the coupling body. The deformable section is configured such that under an unbalanced loading exerted against the coupling body upon a failure of the impeller, the deformable section will permanently deform without the ultimate strength of a material forming the coupling body being exceeded and prior to a permanent deformation of the shaft. In such manner, the electric motor is protected from damage upon a failure of the impeller. | 01-22-2015 |
20150037143 | JOINT - A coupling includes a first element having an annular projection and a second element having an annular recess. Both the first element and the second element have a common axis. A radius of the annular projection varies circumferentially around the axis to thereby define a connection profile. The annular projection is removably accommodated within the annular recess to couple the first and second elements to one another. | 02-05-2015 |
20150322792 | STUB SHAFT - A controlled collapse stub shaft is provided for allowing controlled axial movement of a mainline shaft which joins a fan or compressor to a turbine of a gas turbine engine. A first end of the stub shaft is adapted to be joined to the mainline shaft. A second end of the stub shaft is adapted to be joined to a part of the engine which is axially stationary relative to the controlled axial movement of the mainline shaft. The stub shaft further has an annular body between the first and second ends. The body contains a plurality of axially-spaced circumferential rows of circumferentially-extending slots, inter-slot ligaments being formed between the slots of each row. Successive rows are offset. In this way, the ligaments of the axially forwardmost and rearwardmost rows excepted, each ligament is sandwiched between a forward slot and a rearward slot of its neighbouring rows. Further, each ligament is joined to adjacent ligaments of its neighbouring rows by circumferentially-extending bars having a thickness in the axial direction corresponding to the axial spacing between the rows. The bars are axially deflectable to allow the axial distance between the first and second ends of the stub shaft to decrease. | 11-12-2015 |
20160131155 | CENTRIFUGAL COMPRESSOR - A centrifugal compressor includes a driving shaft ( | 05-12-2016 |
20160169233 | CENTRIFUGAL COMPRESSOR | 06-16-2016 |
20160195097 | AXIAL BLOWER VACUUM | 07-07-2016 |