10 results about "Radial distribution" patented technology

The utility model belongs to steam turbine equipment technical field, concretely relates to a steam turbine shaft seal rack assembly tool, and this tool includes: base, is equipped with the arc locating surface that matches with the curvature of shaft seal strip in its inner ring, a pair of support is arranged in both ends of base, the rotating drum is coaxially suspended in the above of arc locating surface with locating surface, the rotating shaft is through rotating drum and is rotatablely arranged on the support in both ends, drive assembly is connected with one end of rotating shaft, wherein, the rotating drum extends along the axial direction of rotating shaft, and there are multiple containing grooves in radial distribution, the containing groove extends along the circumference of rotating drum, covers the rack groove that shaft seal strip sets, and the depth of containing groove is adapted to the height of rack, when drive assembly drives rotating drum to rotate to the direction of arc locating surface, the lug of rack circumference is embedded in the rack groove.

The utility model discloses a karting boat relates to karting boat technical field. The karting boat includes the hull and the propeller, and the propeller includes the casing, the motor, the connecting rod, the impeller, the first flow guide and the second flow guide, and the motor drives the rotation of the impeller, and the water flow is inhaled from the casing side wall water inlet, and the water flow is formed after the acceleration of the impeller and is rotated jet. Rotating water flow first hits the first flow guide piece, and the first flow guide piece of radial distribution divides the water flow into multiple sub flow channels, and forces the water flow to discharge along the axial direction. Subsequently, the water flow enters the second flow guide area, and the taper structure makes the flow passage cross section area gradually reduce, and the water flow speed improves, and finally the water flow is sprayed from the water outlet in the approximate straight line form. Through the first flow guide, the preliminary rectification is realized, and the second flow guide carries out secondary despinning to the central vortex, and the synergistic effect is formed, and the second flow guide piece produces the reverse moment, converts the rotation energy into the additional thrust, and can improve the power of the propeller.

The application relates to a thread tool grinding method, device and numerical control equipment. The method comprises the following steps: determining the intersection between the chip flute edge line on the outer cylindrical surface of a blank and a thread guide line; determining the circumferential machining range of a machining track section from the intersection based on a machining range parameter; determining the axial distribution of the thread guide line along the tool axis within the circumferential machining range as the axial distribution of the machining track section along the tool axis from the intersection; decreasing the bottom surface circle radius of the blank along the circumferential deflection angle relative to the intersection based on a radial clearance angle parameter to obtain the radial distribution of the machining track section along the tool radial direction from the intersection; and determining the grinding track of a grinding wheel on the blank when grinding thread teeth based on the geometric parameters of the grinding wheel and the radial distribution and axial distribution of the machining track section. The method can ensure the grinding efficiency of the thread tool.

The utility model relates to the technical field of semiconductor manufacturing equipment, specifically disclose a tray structure for silicon carbide epitaxial equipment, including tray base, the concentric circle arrangement of multiple wafer bearing positions is provided with in the upper end surface of circular tray base, each wafer bearing position is the recessed structure of ladder, including embedding setting bottom support ring in the upper end of circular tray base, the inclined transition surface is connected with the upper surface of tray base the outer edge of bottom support ring's upper end surface, through recessed bearing position structure of ladder, the risk of wafer thermal deformation breakage is reduced significantly, radial flow guide groove optimizes reaction gas radial distribution uniformity, and the composite structure of graphite matrix and silicon carbide coating and the processing of round corner edge are matched, effectively improve the anti -peeling ability of coating and equipment service life under high temperature working condition, finally realize the synchronous improvement of epitaxial layer thickness consistency and production yield.

The utility model relates to a cooling structure, turbulence unit and turbine blade relates to aircraft technical field to solve the problem of turbine blade trailing edge cooling performance is poor, radial distribution uneven in the prior art. The cooling structure of the utility model, including turbulence rib and turbulence column, the periphery of turbulence rib sets at least 2 turbulence columns. The utility model can increase the contact area between turbine blade pressure side wall surface and suction side wall surface, thereby enhancing the pressure -bearing capacity of turbine blade, and promoting structural strength.

The application relates to a design method for deriving and developing a downward flow path of an aero-engine axial flow compressor, which comprises the following steps: step one, downward pressing of compressor inlet and outlet hubs, namely, downward pressing of inner flow paths of the compressor inlet and outlet; step two, re-determination of the compressor hub flow path according to the downward pressing amount of the compressor inlet and outlet hubs; step three, re-determination of the compressor casing flow path while keeping the compressor flow path area unchanged; step four, re-determination of the design rotating speed of the compressor while keeping the compressor rotating speed inlet blade tip tangential velocity unchanged; step five, adjustment of the blade profile of each stage of rotor and stator blades while keeping the compressor stage pressure ratio, efficiency and radial distribution unchanged; step six, adjustment of the inlet pre-whirl angle of each stage while keeping the compressor rotor counterforce unchanged; and step seven, checking of the radial distribution of the diffusion factors of each stage of the compressor rotor and stator, and if the radial distribution exceeds the engineering applicable value, returning to step one, adjusting the downward pressing amount of the compressor inlet and outlet hubs and performing iterative optimization.

The utility model discloses a kind of electroplating conductive disc, it is related to electroplating equipment field, including annular disc, the annular disc is evenly provided with several movable grooves along its radial distribution, each movable groove is rotatably connected with rotating block, the both ends of rotating block are fixedly connected with conductive hanging ring, and the upper side of each movable groove is equipped with the limiting structure for fixed rotating block. Through the conductive hanging ring of inside and outside two circles setting, the conductive hanging ring spacing is small, small workpiece can be hung, the spacing of outer conductive hanging ring is big, larger workpiece can be hung, after electroplating is completed, control motor drives horizontal plate and the horizontal rotation of U-shaped brush plate, at this time, U-shaped brush plate passes through the conductive hanging ring of several located in inside in turn, and the adherend on the surface of conductive hanging ring is brushed off, it is convenient to hang and set electroplating for different size workpiece, and the adherend on the surface of conductive hanging ring is cleaned fast and convenient, improve practicality.

A method for predicting leakage losses in axial compressor grates is disclosed. This method calculates the grate leakage flow rate based on the inlet and outlet aerodynamic parameters at the compressor's planar blade mid-diameter and the grate geometric parameters. Then, it calculates the compressor's mainstream loss caused by the grate leakage by comparing the grate leakage flow rate with the compressor's mainstream flow rate. Finally, it determines the influence range and radial distribution law of the grate leakage loss using the compressor's planar blade geometric parameters. This invention targets compressor stators with grate seals. During compressor design and analysis, it eliminates the need for experimental measurements. It predicts grate leakage flow losses using the aerodynamic parameters at the stator's mid-diameter and the geometric parameters of the grate cavity, considering the impact of the leakage flow on the compressor stator blade passages. This allows for the incorporation of the radial influence of grate leakage on compressor outlet performance into the compressor's flow path design and analysis, predicting the grate leakage flow rate, and the influence range and magnitude of the stator outlet loss caused by the grate leakage flow, thus achieving more refined flow path calculations for axial compressors.