Matches 1 - 30 out of 30


Match Document Document Title
US20140341726 BLOOD PUMP WITH SEPARATE MIXED-FLOW AND AXIAL-FLOW IMPELLER STAGES AND MULTI-STAGE STATORS  
A pump for a fluid which can be blood has a stator housing and a rotor hub with leading and trailing portions and an intermediate portion disposed therebetween. At least one impeller blade at the...
US20140099185 HYDROELECTRIC POWER GENERATING DEVICE AND SYSTEM  
A fluid conduit has a constant diameter and a chamber in the conduit has a larger diameter than the diameter of the conduit. Within the chamber, an impeller is rotatable by fluid moving through...
US20150023786 Serial Fan Device  
a serial fan device including two fans linked serially is provided. Each of the two fans has a housing, a driving member and a fan wheel, the housing has an outer frame and a base, the outer frame...
US20130104566 TURBINE OF A TURBOMACHINE  
A turbine of a turbomachine is provided and includes opposing endwalls defining a pathway into which a fluid flow is receivable to flow through the pathway; and a nozzle stage at which adjacent...
US20100232954 BYPASS DUCT OF A TURBOFAN ENGINE  
In the area of the support struts and/or the aerodynamic fairings downstream of the stator vanes, the cross-section of the bypass duct of a turbofan engine is enlarged such that the pressure...
US20100034648 Method of assembling a multi-stage turbine or compressor  
A method is disclosed for assembling a multi-stage compressor or a multi-stage turbine for use in a gas-turbine engine. The method comprises the steps of assembling a rotor drum so as to comprise...
US20080260516 METHOD FOR MODIFYING A MULTISTAGE COMPRESSOR  
A method for modifying a multistage compressor (101) involves exchanging the rotor blades of the first compressor rotor blade row (LA1) for modified rotor blades which have an identical blade leaf...
US20120087786 Stator Structure of Turbo Molecular Pump and Method for Manufacturing the Same  
The present invention discloses an improved stator structure of a turbo molecular pump and a method for manufacturing the same. The stator comprises a plurality of stator blade assemblies, and...
US20110164967 AXIAL FLOW MACHINE HAVING AN ASYMMETRICAL COMPRESSOR INLET GUIDE BAFFLE  
An axial flow machine having an asymmetrical air inlet and, downstream therefrom, a compressor having an inlet guide baffle composed of guide vanes is characterized in that at least some of the...
US20090129918 Blower unit  
A blower unit has a first axial fan and a second axial fan for generating a flow of cooling air passing through a heat exchanger disposed under an intake duct through which an intake air to be...
US20110223013 Reduced Monobloc Multistage Drum of Axial Compressor  
A rotor stage of an axial turbomachine compressor drum includes a symmetrical wall in rotation around the axis of rotation. The wall comprises a veil defining the general form of the drum and an...
US20090214332 MULTISTAGE PUMP ASSEMBLY HAVING REMOVABLE CARTRIDGE  
A multistage pump assembly includes a manifold having an inlet port configured to be coupled to a supply pipe and an outlet port configured to be coupled to a discharge pipe. The inlet and outlet...
US20100172747 PLASMA ENHANCED COMPRESSOR DUCT  
A compression system is disclosed, comprising a first compressor having a first flowpath, a second compressor having a second flowpath located axially aft from the first compressor, and a...
US20080260526 COUNTER-ROTATING AXIAL-FLOW FAN  
A counter-rotating axial-flow fan includes a housing that is constituted from a first divided housing unit and a second divided housing unit. Engaging members and first stopper portions are...
US20120014786 WATER POWERED TURBINE AND TURBINE SYSTEMS  
Disclosed herein are turbines and turbine systems that may be used to generate power and/or electricity from flowing water or may be used in various other applications such as the pumping of...
US20120128476 NOZZLE STAGE FOR A TURBINE ENGINE  
A nozzle stage for a turbine engine includes two substantially cylindrical rings, respectively an inner ring and an outer ring, with, extending between them: vanes carried by a first one of the...
US20100172750 AIR CONDITIONING APPARATUS EQUIPPED WITH A COMPRESSOR AND A VORTEX  
An air-conditioner comprises, in an accommodating structure: an axial compressor powered by a built-in motor unit which circulates air, an axial flow-straightening stator to create a static...
US20070280825 Turbine assembly  
A turbine assembly includes a turbine having a seat extending outward from a top face and a bottom face of the turbine, a shaft hole defined in a bottom face of the seat, multiple blades...
US20150125280 ROTOR OF ROTARY MACHINE AND ROTARY MACHINE  
A rotor (10) of a rotary machine (T1) according to the invention includes a plurality of rotor members (20, 30, and 40) which are joined to each other in the axial direction in which the axis (P)...
US20140233178 Fan Impeller with Multiple Blades Shaped and Disposed to Provide High Air-Power Efficiency  
A fan impeller with multiple blades shaped and disposed to provide high air-power efficiency. The fan impeller includes a hub, a first plurality of primary blades and a second plurality of...
US20150010394 INDUCER  
The present invention relates to an inducer geometry which can optimize the behavior stability of cavitation in an inducer having a plurality of blades of the same geometry. In the inducer having...
US20150007569 VOLUMETRIC ENERGY RECOVERY DEVICE AND SYSTEMS  
A volumetric expander (20) configured to transfer a working fluid and generate useful work includes a housing. The housing includes an inlet port (24) configured to admit relatively high-pressure...
US20120163965 Axial Compressor  
When a gas turbine is operated with inlet guide vanes (IGVs) closed during part load operation or the like, the degradation of aerodynamic performance and of reliability may potentially occur...
US20150078908 GAS TURBINE ENGINE FOR AIRCRAFT ENGINE  
A gas turbine stator for aircraft engines has a blade array with a plurality of blades constituted by a series of first blades and a series of second blades with different geometries; the array is...
US20100166546 APPARATUSES, SYSTEMS, AND METHODS OF GAS TURBINE ENGINE COMPONENT INTERCONNECTION  
One embodiment is an apparatus comprising a first rotational gas turbine engine component including first threads; a second rotational gas turbine engine component including second threads; the...
US20170122107 TURBINE ROTOR FOR A LOW PRESSURE TURBINE OF A GAS TURBINE SYSTEM  
The invention relates to a turbine rotor for a low pressure turbine of a gas turbine system, in particular of an aero engine, comprising four bladed rotor disks which are arranged in series in the...
US20170114802 Compressor  
A compressor, in particular, of a turbomachine The compressor comprises at least one blade ring and at least two ring segments, wherein the blade ring has at least two equally large ring segments....
US20170067422 Flexible Airflow System  
A flexible airflow system providing customizable components for mounting, directing airflow and/or modifying airflow. The system may include a dual fan apparatus for providing heated or cooled air...
US20160222789 Structures and Methods for Forcing Coupling of Flow Fields of Adjacent Bladed Elements of Turbomachines, and Turbomachines Incorporating the Same  
Turbomachines having close-coupling flow guides (CCFGs) that are designed and configured to closely-couple flow fields of adjacent bladed elements. In some embodiments, the CCFGs may be located in...
US20150267709 MOTOR-DRIVEN TURBO COMPRESSOR  
In the compressor of the present invention, an intermediate pressure port through which a first discharge chamber and a first chamber communicate with each other is formed in a front housing. In...

Matches 1 - 30 out of 30