Class / Patent application number | Description | Number of patent applications / Date published |
416242000 | Reverse curve surface | 14 |
20100303632 | DOUBLE LEADING EDGE AIRFOIL FOR WIND TURBINE BLADE ROOT - The invention relates to an aerodynamic profile for the root of a wind turbine blade having a double leading edge, including a leading edge ( | 12-02-2010 |
20110008176 | TURBOMOLECULAR PUMP - An object is to provide a turbomolecular pump with rotor and stator blades alternatively arranged that can prevent collision between the adjacent rotor and stator blades due to air inrush, which may take place due to vacuum break in a system operation, prevent excessive centrifugal force to a hub portion of a rotor, and further enhance pumping performance. A blade cross sectional profile taken along the circumferential direction of each of the rotor blades of a rotor blade stage has an upstream portion curved convexly backward in a rotational direction of the rotor and a downstream portion curved convexly forward in the rotational direction of the rotor, thereby forming the blade cross sectional profile into an S-shape or inversed S-shape. | 01-13-2011 |
20120201692 | ROTOR OF A TURBOMACHINE COMPRESSOR, WITH AN OPTIMISED INNER END WALL - A rotor of a turbomachine compressor, including a bladed rotor disk fitted at its radially external end with a wall forming the inner end of an annual flow channel of a primary gas flow, and formed from multiple angular sectors, each of which is delimited between two blades of the disk which are consecutive in a circumferential direction and includes a bulging portion which is convex in the axial direction and in the circumferential direction, together with, upstream from the bulging portion, a troughed portion which is concave in the axial direction and in the circumferential direction and which has a base which is roughly punctiform. | 08-09-2012 |
20130028747 | FAN PROPELLER, IN PARTICULAR FOR A MOTOR VEHICLE - A fan propeller comprises blades ( | 01-31-2013 |
20130189116 | WIND TURBINE BLADE HAVING A GEOMETRIC SWEEP - A swept wind turbine blade ( | 07-25-2013 |
20130224039 | Rotor for Vertical Wind Power Station - The present invention relates to a rotor for a vertical wind power station comprising a plurality of planar rotor elements ( | 08-29-2013 |
20130224040 | HIGH ORDER SHAPED CURVE REGION FOR AN AIRFOIL - A turbomachine blade with a localized dihedral feature has a high order polynomial shaped curve region. | 08-29-2013 |
20140023516 | DIAGONAL IMPELLER FOR A DIAGONAL FAN, AND DIAGONAL FAN - A diagonal impeller for a diagonal fan ( | 01-23-2014 |
20140294595 | ROTOR BLADE ASSEMBLY FOR WIND TURBINE HAVING LOAD REDUCTION FEATURES - Rotor blade assemblies for wind turbines are provided. In one embodiment, a rotor blade assembly includes a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge each extending between a tip and a root. The rotor blade further defines a span and a chord. A span-wise portion of the pressure side includes along a chord-wise cross-section a plurality of inflection points. The plurality of inflection points include a first inflection point and a second inflection point, the first and second inflections points positioned within approximately 50% of the chord from the leading edge. | 10-02-2014 |
20140348660 | BLADE CASCADE AND CONTINUOUS-FLOW MACHINE - A blade cascade of a continuous-flow machine is disclosed. The blade cascade has at least one side wall that is constructed in a wave-like manner in the peripheral direction and has at least one elevation and at least one depression. At least a profile-like rib is integrated in or combined with the side wall, which has a blade profile with a pressure side and with an opposite suction side. A continuous-flow machine with such a blade cascade is also disclosed. | 11-27-2014 |
20140363306 | AXIAL-FLOW FAN - An axial-flow fan has a blade with a recessed part that is recessed toward a front edge formed in a rear edge of the blade. A rounded stress-relieving part is formed in a positive pressure surface side and a negative pressure surface side of a front-edge-side edge part of the recessed part as seen in a cross-sectional view of the blade. | 12-11-2014 |
20150044058 | AXIAL FLOW FAN AND AIR-CONDITIONING APPARATUS HAVING THE SAME - A leading edge of a blade has a first curved portion provided with a leading-edge rearmost point, and a trailing edge of the blade has a second curved portion located on the inner circumferential side of the trailing edge and a third curved portion located on the outer circumferential side of the blade on the trailing edge. The third curved portion has a trailing-edge foremost point, and the second curved portion has a trailing-edge rearmost point. The trailing edge and a first concentric circle, which is one of concentric circles having as their center an axis of rotation and passes through the leading-edge rearmost point, intersect each other at a first intersection. The first intersection is located between the trailing-edge rearmost point and the trailing-edge foremost point. | 02-12-2015 |
20160061216 | COMPRESSOR ROTOR AIRFOIL - A compressor rotor airfoil in a gas turbine engine is presented. Opposed pressure and suction sides are joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip. A leading edge dihedral angle is defined at a point on the leading edge between a tangent to the airfoil and a vertical. The leading edge dihedral angle has a span-wise distribution. The distribution has at least one inflection point. A method of reducing a rub angle between a compressor rotor blade and a casing surrounding the blade is also presented. | 03-03-2016 |
20160122011 | AIRFOIL FOR ROTOR BLADE WITH REDUCED PITCHING MOMENT - A rotor blade for a rotary wing aircraft includes a root region extending from a rotor head to about 15% to 20% of a blade radius, a main region extending from a radial extent of the root region to about 80% to 95% of the blade radius, a tip region extending from a radial extent of the main region to a blade tip, and a trailing edge. A portion of one of the root region, the main region and the tip region has an airfoil profile section including a trailing edge reflex camber relative to a base airfoil shape of a remainder of the one of the root region, the main region, and the tip region to reduce pitching moment of the rotor blade while maintaining a positive aerodynamic characteristic of the base airfoil shape. The reflex camber extends 20% of a blade chord from the trailing edge. | 05-05-2016 |