Class / Patent application number | Description | Number of patent applications / Date published |
416203000 | UNSYMMETRICAL IMPELLER OR DISSIMILAR WORKING MEMBERS | 13 |
20080206058 | METHOD FOR REDUCING VIBRATION LEVELS OF A BLADED WHEEL IN A TURBOMACHINE - The present invention concerns a method for reducing vibration levels likely to occur in a turbomachine comprising at least a first and a second bladed wheel, where the two wheels are moving relative to one another about an axis of rotation and a gaseous fluid is passing over them, due to perturbations of an aerodynamic origin that are produced by the second bladed wheel or an obstacle on the first bladed wheel. The method includes the following steps in the design of said two bladed wheels: an initial configuration of the blades is defined; the synchronous forced response on the first bladed wheel is calculated as a function of the harmonic excitation force produced by the second bladed wheel expressed in the form of a linear function of the generalized aerodynamic force for the mode considered; a geometric tangential shift value θ is determined for the stacked cross sections of one of the two wheels so as to reduce the corresponding term to the generalized aerodynamic force. The set of cross sections with the tangential shifts thus defines a new configuration of the blades of said one of the two wheels which is applied to the blades of said one of the two wheels. | 08-28-2008 |
20080226454 | High efficiency cooling fan - A cooling fan includes an impeller which comprises a plurality of radially extending blades, each of which includes a blade hub, a blade tip and a blade midspan approximately midway between the hub and the tip. In addition, each blade includes a camber of between about 60° and 90° at the blade hub, between about 15° and 40° at the blade midspan and between about 15° and 40° at the blade tip. | 09-18-2008 |
20080304972 | ROTARY BODY FOR TURBO MACHINERY WITH MISTUNED BLADES - A rotary body for use in a turbo machine includes a hub having an outer edge and a plurality of slots formed in the outer edge, the slots having first and second spaced-apart opposing inner surfaces extending from the outer edge to a depth within the hub, and a plurality of blades secured to the outer edge of the hub, the slots and the blades being arranged such that at least two of the blades are positioned between each pair of adjacent ones of the slots. | 12-11-2008 |
20100266413 | WIND TURBINE ROTOR WITH VERTICAL ROTATION AXIS - A wind turbine rotor with a vertical rotation axis connected to a hub having at least two horizontal supports, on the ends of which are tightly fixed blades, each consisting of two wings joined together, with a symmetrical or concavo-convex airfoil with the airfoil's chord lengths and thickness diminishing toward both wing ends. The rotor blade's upper and lower wings are radially deflected from the central zone outwards. The chord length of both wing ends and the chord length in the central zone are approximately inversely proportional to the radii of its location in relation to the axis of the rotor's rotation. The deflecting angle of the lower wing can be greater than the deflecting angle of the upper wing or the length of the lower wing can be greater than the length of the upper wing. These specifications provide uniform wind power consumption along the wing's length, increasing the efficiency of a wind turbine and its service life. | 10-21-2010 |
20120070294 | UNIVERSAL SPHERICAL TURBINE WITH SKEWED AXIS OF ROTATION - A universal spherical reaction turbine for any flowing fluid at any depths or elevation that is capable of unidirectional rotation under reversible flow conditions. The turbine includes a rotatable shaft that is adapted to rotate about an axis of rotation; turbine blade support members that are fixedly attached to the rotatable shaft and a plurality of meridian turbine blades. The meridian turbine blades are fixedly attached to diametrically-opposite points that define a geometrical north-south meridian axis that is oriented at a skew angle to the axis of rotation of the rotatable shaft. The skew angle is greater than zero and less than 180 degrees, and, more preferably, between 25 and 35 degrees. The skewing ensures that those turbine blades that are attached to the diametrically-opposite points move on a helical trajectory with respect to the axis of rotation. | 03-22-2012 |
20120099995 | ROTARY MACHINE HAVING SPACERS FOR CONTROL OF FLUID DYNAMICS - A system includes a rotary machine with a fluid flow path extending along an axis of the rotary machine, a plurality of airfoils disposed about the axis, and a plurality of spacers disposed about the axis. Each spacer of the plurality of spacers is disposed circumferentially between adjacent airfoils of the plurality of airfoils to define a circumferential spacing of the airfoils about the axis. | 04-26-2012 |
20130052021 | ROTOR ASYMMETRY - A gas turbine engine has a section, such as a compressor section, with at least two spaced apart stator assemblies and an asymmetrical rotor assembly positioned between the spaced apart stator assemblies. The asymmetrical rotor assembly has a rotor array which is asymmetric about at least one diameter of the rotor assembly. | 02-28-2013 |
20130121833 | STRUCTURAL STATOR AIRFOIL - An airfoil comprises a leading edge, a trailing edge, and pressure and suction surfaces defined therebetween. An inner platform is coupled to a root section of the airfoil, with a curvilinear gusset extending along a lower surface of the inner platform, opposite the root section. An outer platform is coupled to a tip section of the airfoil, with a multi-lobed gusset extending along an upper surface of the inner platform, opposite the tip section. | 05-16-2013 |
20140044546 | BLADED ROTOR FOR A TURBOMACHINE - A bladed rotor for a turbomachine, in particular a gas turbine, having a plurality of blades distributed around the circumference thereof; the blade distribution being made up of a natural-number sector count of first angular sectors and second angular sectors; a first blade count of first blades being arranged in the first angular sectors, and a second blade count of second blades being arranged in the second angular sectors, said second blade count being different from said first blade count; and the sector count being odd (Z=2n+1, n=1, 2, 3, . . . ) and/or greater than two (Z>2). | 02-13-2014 |
20140301852 | BLADE CASCADE FOR TURBO MACHINE - A blade cascade for a turbomachine, in particular a gas turbine, including multiple identical blade groups which are situated next to each other and which each include
| 10-09-2014 |
20140322021 | METHOD OF AND A DEVICE FOR REDUCING THE AZIMUTHAL TORQUE ACTING ON A PULLING POD UNIT OR AZIMUTH THRUSTER - This invention relates to a device and method of reducing the azimuthal torque acting on a pulling pod unit or azimuth thruster ( | 10-30-2014 |
20150110629 | TURBINE BUCKET HAVING NON-AXISYMMETRIC BASE CONTOUR - Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric contour proximate a junction between the base and the airfoil. | 04-23-2015 |
20160186772 | AXIAL COMPRESSOR ROTOR INCORPORATING NON-AXISYMMETRIC HUB FLOWPATH AND SPLITTERED BLADES - A compressor apparatus includes: a rotor including: a disk mounted for rotation about a centerline axis, an outer periphery of the disk defining a flowpath surface having an non-axisymmetric surface profile; an array of airfoil-shaped axial-flow compressor blades extending radially outward from the flowpath surface, wherein the compressor blades each have a root, a tip, a leading edge, and a trailing edge; and an array of airfoil-shaped splitter blades alternating with the compressor blades, wherein the splitter blades each have a root, a tip, a leading edge, and a trailing edge; and wherein at least one of a chord dimension of the splitter blades at the roots thereof and a span dimension of the splitter blades is less than the corresponding dimension of the compressor blades. | 06-30-2016 |