Class / Patent application number | Description | Number of patent applications / Date published |
415062000 | Diverse type runners, blade systems or working fluid paths in runners | 14 |
20080260516 | METHOD FOR MODIFYING A MULTISTAGE COMPRESSOR - A method for modifying a multistage compressor ( | 10-23-2008 |
20080273962 | Liquid Turbine Device Including a Turbine Wheel with More Than One Set of Blades in Radial Succession - A liquid turbine device including a turbine wheel, in which the turbine wheel includes more than one set of blades in radial succession. | 11-06-2008 |
20090022576 | IMPELLER DRIVE FOR A WATER JET PROPULSION UNIT - A water propulsion unit having an intake housing, a pump housing and an outlet with two spaced apart counter rotating impellers being located in the pump housing. The impeller blades on one impeller have an opposite pitch to the blades of the second impeller. The impellers are configured so that one of the impellers will impart less energy to the water as it passes the blades of the impeller than the second impeller. | 01-22-2009 |
20090123265 | Gas Turbine Engine - The invention is directed to a gas turbine engine comprising a compressor, a combustion chamber, and a turbine section installed one after the other in series in the direction of the air and gas flow, wherein the compressor consists of two groups of blade wheels rotating in opposite directions to each other. The deviation of the performance defined as “air mass flow per second” between both compressor groups is minimized and a detachment of the air mass flow from the blades is substantially eliminated. The blade wheels of the second compressor group, beginning at the first blade wheel, are progressively bigger to allow a bypass for the air stream coming from the first compressor group to serve all the blade wheels of the second group essentially simultaneously. | 05-14-2009 |
20110064562 | Turbomolecular Pump - A turbomolecular pump has multiple stages of alternately arranged rotors and stators. Each of the rotors has blades radially extending from a rotating body. Each of the stators has blades radially extending toward the rotating shaft of the rotating body. The blades provided on at least either of a rotor and a stator are formed in a twisted shape having a blade angle set by an expression in which the radial distance from the rotating shaft is a variable. The expression of the blade angle is composed of a first expression which provides the optimum angle of each blade on the outer side of a predetermined radius of the blade and also composed of a second expression which provides the blade angle suppressing, on the inner side of the predetermined radius, reverse flow of gas molecules. | 03-17-2011 |
20120099961 | ROTARY MACHINE HAVING NON-UNIFORM BLADE AND VANE SPACING - A system, including a rotary machine including: a stator, a rotor configured to rotate relative to the stator, wherein the rotor comprises a plurality of blades having a non-uniform spacing about a circumference of the rotor. | 04-26-2012 |
20120107091 | FAN ASSEMBLY - A fan assembly includes a housing, a first frame, a second frame, at least one driving device, a supporting device, an active impeller and a passive impeller. The housing has an air-flowing channel, and the first frame and second frame are disposed at opposite sites of the air-flowing channel. The driving device is disposed on the first frame and actuates the active impeller to rotate. The supporting device is disposed on the second frame and has the passive impeller thereon. The passive impeller is propelled by the airflow generated by the active impeller. | 05-03-2012 |
20120107092 | AXIAL FLOW FAN - An axial flow fan including a rotation shaft section to be mounted on the rotation shaft of rotation drive means, an inner blade group provided outside the rotation shaft section so as to be coaxial therewith, and an outer blade group provided outside the inner blade group so as to be coaxial therewith, wherein the inner blade group is formed of a plurality of inner blades provided radially around the rotation shaft section, the outer blade group is formed of a plurality of outer blades provided radially around the rotation shaft section, and the velocity V | 05-03-2012 |
20130101392 | PROPULSIVE SYSTEM - This invention relates to an aircraft comprising: a first propulsive unit having a first fan with an axis of rotation; and a second propulsive unit local to the first propulsive unit, the second propulsive unit having a second fan with an axis of rotation, wherein the rotational axis of the first fan is proximate to the surface of the aircraft relative to the rotational axis of the second fan such that the first fan ingests boundary layer air when in use. | 04-25-2013 |
20130209222 | PUMP - The present invention relates to a multi-stage vacuum pump having a plurality of compression stages | 08-15-2013 |
20140205431 | VACUUM PUMP - A vacuum pump has an exhaust portion in which rotating blade portions and stationary blade portions are laminated in multiple stages. Each of the plurality of stator blades in one stage of the stationary blade portion is three-dimensionally connected to the stationary blade portion main body by an inner circumferential side support portion on the inner circumferential end side, and three-dimensionally connected to the stationary blade portion main body by an outer circumferential side support portion on the outer circumferential end side, and a cutout is provided in a circumferential front end of the outer circumferential side support portion. | 07-24-2014 |
20150315974 | TWO SPOOL GAS GENERATOR WITH IMPROVED PRESSURE SPLIT - A gas turbine engine has a first shaft including a first compressor rotor. A second shaft includes a second compressor rotor disposed upstream of the first compressor rotor. The second compressor rotor has a first overall pressure ratio. The first compressor rotor has a second overall pressure ratio, with a ratio of the first overall pressure ratio to the second overall pressure ratio being greater than or equal to about 3.0. | 11-05-2015 |
20160161133 | VENTILATION MODULE WITH SWIRLER FAN - The disclosure aims to provide a ventilator module with improved efficiency. The ventilator module employs the dual structure of fans includes a swirler fan and a suction fan, in which the swirler fan is disposed at the front side and the suction fan is disposed at the rear side of the swirler fan so that a swirl formed by the drive of the swirler fan forms a donut-like low pressure zone around an inlet, and a tornado is formed by rotating the donut-like low pressure zone by the drive of the suction fan thereby cause the air below swirler fan to ascend at high velocity so as to be suctioned and discharged. | 06-09-2016 |
415063000 | Including internally passaged runner with reaction type jet discharge nozzle | 1 |
20130101393 | REACTION TURBINE AND HYBRID IMPULSE REACTION TURBINE - A reaction turbine has channels formed in the top surface of a disc to create nozzles. The channels can be covered by a membrane sealed to the disc or by the housing extended from a combustor. Each channel may have a first section extending radially outwardly from an inlet of the reaction turbine and a second curved section extending from the first section to a periphery of the disc. A reaction turbine may also receive input from an impulse turbine. Fluid flows through the impulse turbine and fluid from the impulse turbine enters an inlet of the reaction turbine. The reaction turbine may have cooling channels and cooling fins to lower the temperature of the disc during operation. In addition, magnets may provide bearing support and electricity generation. In addition, the reaction turbine may have a dual shaft construction, with each shaft connected to a reaction turbine. One reaction turbine powers a compressor, while the second reaction turbine powers a load through the second shaft. | 04-25-2013 |