Patent application number | Description | Published |
20130195667 | IMPELLER FOR CENTRIFUGAL COMPRESSOR - An impeller for a centrifugal compressor is characterized in that a shroud side of a front edge | 08-01-2013 |
20130266432 | SCROLL STRUCTURE OF CENTRIFUGAL COMPRESSOR - A scroll structure of a centrifugal compressor | 10-10-2013 |
20130266433 | TURBINE SCROLL PART STRUCTURE - In a turbine scroll part structure of a radial turbine, a flow passage | 10-10-2013 |
20130266436 | HOUSING STRUCTURE OF EXHAUST GAS TURBOCHARGER - A casing treatment | 10-10-2013 |
20130272865 | SCROLL STRUCTURE OF CENTRIFUGAL COMPRESSOR - In a scroll structure of a centrifugal compressor, there are provided a radius increase arc portion E in which a radius from the center of a scroll | 10-17-2013 |
20130294903 | SCROLL SHAPE OF CENTRIFUGAL COMPRESSOR - In a scroll shape of a centrifugal compressor, an enlargement rate of a ratio A/R of a cross-sectional area A of a scroll portion | 11-07-2013 |
20130343885 | SCROLL STRUCTURE OF CENTRIFUGAL COMPRESSOR - An axial cross-sectional shape of a scroll flow path | 12-26-2013 |
20140010647 | TURBOCHARGER AND METHOD OF MANUFACTURING FLOATING BUSH - A turbocharger and a method of manufacturing a floating bush with which noise can be reduced, and the rotation speed can be increased. In a turbocharger in which a rotating shaft having a circular cross-section and connecting a turbine rotor and a compressor rotor is supported in a freely rotatable manner, at two axially separated positions via floating bushes, by an inner circumferential surface disposed so as to surround the rotating shaft in a bearing housing, an inner circumferential surface of each of the floating bushes has a non-circular shape in which the curvature of the cross-sectional shape varies in the circumferential direction. | 01-09-2014 |
20140341729 | RADIAL TURBINE - A radial turbine comprises a plurality of nozzle vanes disposed along a circumferential direction inside a spiral scroll and configured to regulate a flow of a working gas from the scroll to a rotor blade, wherein each of the nozzle vane includes a leading edge bulging portion on both end portions in a width direction of an inlet leading edge portion, the leading edge bulging portion being bulged toward a pressure face side of the nozzle vane relative to a central portion, so that a vane angle is configured to correspond with an inflow angle of the working gas to be flown into the nozzle vane, and wherein each of the nozzle vane includes a trailing edge bulging portion on both end portions in a width direction of an outlet trailing edge portion, the trailing edge bulging portion being bulged toward the pressure face side relative to a central portion, so that an outflow angle of the working gas from the outlet trailing edge of the nozzle vane becomes uniform. | 11-20-2014 |