# The blade of the impeller radial-axial turbines

The design of the blades of the impeller may be used to create radial-flow turbines. The blade of the impeller radial-axial turbine having a curvilinear shape, contains the input and output edges that are joined end surfaces of the rim and the hub has an input edge, made straight, parallel to the axis of rotation of the impeller, and in the Cartesian coordinate system, the Z axis coincides with the axis of rotation of the impeller, and the X axis lies in the meridional plane containing the output edge of the blade, the coordinates of the middle line x', y' and thickness d' of the blade in the cutting plane, crossing the coordinate plane XOZ on the X-axis and located at an angle of 68° to the plane XOZ, determined by the ratio of:the coordinates of the middle line x', y' and thickness d' of the blade in a section plane passing through the point (0; 0; 0,085 D

_{1}) crossing the coordinate plane XOZ on a straight line parallel to the X-axis, and located at an angle of 62° to the plane XOZ, determined by the ratio of:the coordinates of the middle line x', y' and thickness d' of the blade in the plane of section passing through the od angle of 55° to the plane XOZ, determined by the ratio of:where D

_{1}- nominal impeller diameter,x', y' - coordinates of the middle of the section line in the coordinate plane section X OY', and the X' axis is parallel to the X-axis and passes through the outlet edge of the blade, the axis Y' corresponds to the line of intersection of the coordinate plane YOZ and the plane intersecting the blade. The design of the blade allows you to increase the turbine efficiency and improve the cavitation characteristics. 3 Il. The invention relates to hydromelioration and can be used to create radial-axial turbines.The well-known vane of the impeller of the fluid machines (patent US 340120) slightly curved shape having input and output edges, and attached upper and lower end surfaces of the upper and lower disks of the impeller. The disadvantage of this design is the proper geometry of the input element of the blade naticoidea stream that leads to the wrap blade with large variations in the fluid velocity and correspondingly large energy losses. In addition, the blade has a low cavitation characteristics that Ki is aemono technical solution is the blade of the impeller according to patent US 147351, having input and output edges, and attached upper and lower end surfaces to curved surfaces of the hub and rim. The disadvantage of this design is the most uneven fluid flow leaving the impeller, which leads to significant energy losses in the output element of the fluid machines and thus reduce the overall effectiveness of its work.The technical result of the claimed invention is to form the blades of the impeller radial-axial turbines, consistent with a forced fluid flow and providing a uniform flow of liquid leaving the impeller. Improving the flow of the blade leads to increased efficiency and improved cavitation characteristics of the turbine.The present invention solves the problem of improving the conditions of flow of the blade by creating its new form, characterized by new relations parameters.The technical result is achieved by the fact that the blade of the impeller radial-axial turbine having a curvilinear shape, containing the input and output edges and the joining end surfaces of the rim and the hub has an input edge, made premade with the axis of rotation of the impeller, and the X-axis lies in the meridional plane containing the output edge of the blade, the coordinates of the middle line x', y' and thickness d' of the blade in a section plane that intersects the XY plane XOZ on the X-axis and located at an angle of 68° to the plane XOZ, determined by the ratio of:x'/D

_{1}= 0,188+0,1433(y'/D

_{1}) +1,3206(y'/D

_{1})

^{2};d'/D

_{1}= 0,0045+0,0626 ('/7D

_{1}) + 0,7235(y'/D

_{1})

^{2}-2,451(y'/D

_{1})

^{3};the coordinates of the middle line x', y' and thickness d' of the blade in a section plane passing through the point (0; 0; 0,085 D

_{1}) crossing the coordinate plane XOZ on a straight line parallel to the X-axis and located at an angle of 62° to the plane XOZ, determined by the ratio of:x'/D

_{1}= 0,243-0,1594(y'/D

_{1}) +1,584(y'/D

_{1})

^{2};d'/D

_{1}= 0,0053+0,0678(y'/D

_{1}) +0,5826 (y'/D1)

^{2}-2,0013(y'/D

_{1})

^{3};the coordinates of the middle line x', y' and thickness d' of the blade in a section plane passing through the point (0; 0; 0,175 D

_{1}) crossing the coordinate plane XOZ on a straight line parallel to the X-axis and located at an angle of 55° to the plane XOZ, determined by the ratio of:x'/D

_{1}= 0,349-0,6003(y'/D

_{1}) +1,4409 (y'/D

_{1})

^{2}+1,0113(y'/D

_{1})

^{C};d'/D

_{1}= 0,0071+0,0562 (y'/D

_{1}) +0,4965(y'/D

_{1})

^{2}-1,5670(y'/D

_{1The essence of the present invention is illustrated in the drawings, which show:in Fig.1 is a view of the blades of the impeller in the projection on the coordinate plane YOZ Cartesian coordinate system, the Z axis coincides with the axis of rotation of the impeller, and the X axis lies in the meridional plane containing the output edge of the blade, and the position of the planes, hooking the blade; Fig.2 is a view of the blades in the plan, i.e. the projection on the coordinate plane XOY; Fig.3 is a view along the normal to the section plane In the - CenturyThe blade of the impeller radial - axial turbine according to the invention has a curvilinear shape, includes a straight inlet flange 4 and the output edge 5 and the joined end surfaces 6 and 7 to the rim and the hub. The claimed ratio of the parameters characterizing the shape of the blade resulting from performing a large amount of computational studies to test the conformity of the input element of the blade incident flow and the form of the blade, providing uniform fluid flow over the impeller, ka set of profiles, corresponding to the intersection of the body of the blade inclined planes, as shown in Fig.1. The profile of each section in accordance with Fig. 3 is specified by the coordinates x', y' middle line 8 and the diameter d' of the circles inscribed in the profile. Plane sections 1, 2 and 3 (Fig.1) set the coordinates of zi(i = 1, 2, 3) the point of intersection of the plane with the Z axis and angles1between the plane and the coordinate plane XOZ. The coordinates of the middle lines and the thickness of the cross sections of the blade are defined by the following relations:Section 1:where D1- nominal diameter of the impeller;x', y' - coordinates of the middle of the section line in the coordinate plane section X OY', and the X' axis is parallel to the X-axis and passes through the outlet edge of the blade, the axis Y' corresponds to the line of intersection of the coordinate plane YOZ and the plane intersecting the blade (Fig.1).We have conducted a comparative study of flow area of the turbine diameter D1=LM with the claimed form of the blades and the flow area of the turbine close speed [1, page 23] in the mode corresponding to the speed ratio of ns=115. As a result of application of the flow part with bretania leads to an increase in electricity generation at the expense of efficiency.Literature1. Reference turbines, Ed. by N. N. Kovalev. L., engineering, 1984 ClaimsThe blade of the impeller radial-axial turbine having a curvilinear shape, containing the input and output edges and the joining end surfaces of the rim and the hub, characterized in that the input edge is made rectilinear, parallel to the axis of rotation of the impeller, and in the Cartesian coordinate system, the Z axis coincides with the axis of rotation of the impeller, and the X axis lies in the meridional plane containing the output edge of the blade, the coordinates of the middle line x', y' and thickness' of the blade in the cutting plane, crossing the coordinate plane XOZ on the X-axis and located at an angle of 68° to the plane XOZ, are determined by the ratiosthe coordinates of the middle line x', y' and thickness' of the blade in a section plane passing through the point (0; 0; 0,085 D1) crossing the coordinate plane XOZ on a straight line parallel to the X-axis, and located at an angle of 62° to the plane XOZ, are determined by the ratiosthe coordinates of the middle line x', y' and thickness d' of the blade in the plane with the first axis X, and located at an angle of 55° to the plane XOZ, are determined by the ratioswhere D1- nominal diameter of the impeller;x', y' - coordinates of the middle of the section line in the coordinate plane section X OY',moreover, the X' axis is parallel to the X-axis and passes through the outlet edge of the blade, the axis Y' corresponds to the line of intersection of the coordinate plane YOZ and the plane intersecting the blade. }

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