Turbine blade with perfected aerodynamic characteristic and turbine wheel with such blade |
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IPC classes for russian patent Turbine blade with perfected aerodynamic characteristic and turbine wheel with such blade (RU 2520273):
 Turbine blade and turbine wheel with said blades / 2518767
Turbine wheel comprises turbine blades (20) shaped aerodynamic part (102). Said aerodynamic shape has rated profile corresponding to data cited in the tables 1 through 11 wherein distances X, Y, Z and R are given in inches and the tables 1' through 11' wherein said distances are given in centimetres. Magnitudes if coordinates X and Y are smoothly connected by arc with radius R to make profile cross-section of said shaped part at every distance Z. Profile cross-section at distances Z are smoothly interconnected to produce a complete aerodynamic shape.
 Turbomachine diffuser-distributor assembly / 2518746
Diffuser-distributor assembly intended to be installed at a compressor output in a turbine comprises a distributor. The distributor includes two, in essence, cylindrical walls: a radial inner one and a radial outer one. The walls are connected by radial blades. The distributor walls are extended to the downstream part beyond the radial blades. Radial clearance between the walls is circumferentially variable downstream the blades so that in essence to be minimal in the blades extension and maximal between the blades. The clearance is circumferentially variable up to the downstream end of the downstream walls of the distributor. Subject of the invention is also a turbomachine such as turbojet engine, turboprop engine or helicopter engine comprising the assembly described above.
 Steam-turbine engine low-pressure stage working blade / 2515582
Steam turbine (10) working blade (20) comprises airfoil section (42). Blade butt section (44) is secured to one end of airfoil section (42). Dovetail part (40) extends from butt section (44) and includes skewed part (40) with axial twist that features skew angle equal to 19 degrees. Rim section (46) is attached to airfoil section (42) at the end opposite the butt section (44). Airfoil shroud platform (48) is made integral with rim section part (46). Airfoil shroud platform (50) is secured to airfoil section (42) mid part between airfoil ends. Working blade (20) features outlet circular cross-section making about 4.43 m2 or larger. Airfoil section (42) features length making about 68.1 cm or larger.
 Turbine assembly of turbo-pump unit / 2511964
Turbine assembly of the unit includes a working medium - steam supply housing, a nozzle block with inclined nozzles, a turbine having a shaft with a runner, and a waste steam outlet housing located downstream of the turbine in the steam flow direction. The steam supply housing is equipped with a header including an axisymmetrical annular cover having the shape of a flattened fragment of a tore or a toroid. The turbine runner us made at least of one disc with blades. Blades are convex-concave as to width and have radial height comprising (0.05÷0.25) of the disc radius. The blade thickness is variable in the direction of steam flow with maximum in the middle part of the blade chord width. The chord width of the blade in the projection to a conditional chord plane attaching inlet and outlet side edges of the blade does not exceed radial height of the blade. The nozzles are made in the disc in the amount of 8÷15, located radially at equal distance with their longitudinal axes from the turbine axis and equally spaced in a conditional circumferential direction at equal angles determined in the range of (24÷45)°. Total number of blades exceeds by 2.6÷34.4 times the number of nozzles.
 Turbo-pump unit, and cold, hot and industrial water pumping method / 2511963
Turbo-pump unit includes a turbine assembly with working medium inlet and outlet housings, a nozzle block and a single-stage turbine. The unit includes a pump assembly with a screw centrifugal impeller. The working medium supply housing is equipped with a manifold including an axisymmetrical tight annular cover. The large part of the cover has the shape of a longitudinally flattened fragment of a tore or a toroid. Turbine runner blades are convex-and-concave as to width, radial height of 0.05÷0.25 of the turbine runner disc radius. The blade thickness is accepted as variable in the direction of working medium flow vector with maximum in the middle part of the blade chord width. The chord width of the blade in the projection to a conditional chord plane attaching inlet and outlet side edges of the blade does not exceed radial height of the blade. The inter-blade channel is of a confuser-and-diffuser type in the direction of the steam flow vector with maximum constriction of flow cross sectional area determined in zone of maximum thickness of blades. Total number of turbine runner blades exceeds by 2.6÷34.4 times the number of nozzles in the nozzle block.
 Gas turbine cermet blade / 2510463
Cermet blade has shaped ceramic shell and drive rod with inner and outer flanges arranged there inside. Said drive rod has flexible pins inclined to drive rod inner flange and staying in contact with inner surface of shaped ceramic shell to ensure stability of said shell and to damp its vibration. Plate spring is arranged between drive rod inner flange and lower thrust flange of said shell to compensate for shaped shell thermal expansion. To up reliability, detachable drive rod outer shell abuts, without clearance, on upper thrust flange of shaped ceramic shell and is secured to rod outer radius.
 Single-crystal turbine blade, turbomachine module and turbomachine / 2498082
Single-crystal blade of turbine impeller is manufactured by casting with directionally crystallisation and comprises a blade airfoil, an end structural component of the blade airfoil and a transition zone. The blade airfoil consists of leading and back edges, sides of C-tray and C-back, centre line and longitudinal axis. The end structural element of the blade airfoil comprises the end side of the blade airfoil on the side of the gas-air path with the end side forming an angle to the longitudinal axis of the blade airfoil. The transition zone is located between the blade airfoil and the end side of the blade airfoil and provides for the blade airfoil bulb. The transition zone stretches around the leading edge between the point placed at the blade airfoil back and at the end side of the above end structural element upstream in relation to the C-back and the point placed at the blade airfoil tray and at the end side of the above end structural element upstream in relation to the C-tray. Other inventions of the group relate to a turbomachine module and a turbomachine comprising the above mentioned blades.
 Blade with asymmetrical platform, rotor blade wheel, turbomachine and turbomachine nozzle diaphragm section / 2498081
Blade (10) for turbomachine rotor blade wheel comprises an aerofoil section and at least one platform on the end of the aerofoil. The blade (10) is made so that to be set together with many other essentially similar blades so as to form a ring. The platform surface is fitted by profile (80) on the suction surface side and by profile (85) on the pressure surface side, respectively along the suction surface or pressure surface. The suction surface profile (85) of the blade has a recessed section (I) of the pressure surface located in the axial direction in the upstream half of the aerofoil section. Most of the surface between the aerofoil profiles is provided by the movement of a linear segment based on the profiles (80, 85) of suction surface and pressure surface.
 Blower guide vane made of 3d composite / 2497674
Invention relates to production of turbine blower guide vane of composite material. Proposed method comprises making of fiber preform by 3D weaving of one part. Said preform comprises first part extending in one lengthwise axis to make preform for vane airfoil and second part located and lengthwise end forming the preform for vane support. Second part consists of first layer and second layer facing the latter and separated therefrom by separation without cutting in making of preform. Proposed method comprises bending said first and second layers so that each of them is located in plane perpendicular to lengthwise axis, in fact, in symmetry about each other relative to said first part so that firs layer first section overlaps second layer second section ahead of first part edge. This method comprises jointing the preform with the mould to compact the former by polymer female die.
 Blade for turbomachine impeller, area of turbomachine nozzle block, impeller and turbomachine / 2496986
Blade of a turbomachine impeller comprises an aerofoil section with a trough, a back, rear and front edges, and also a shelf stretching from one of ends of the aerofoil perpendicularly to its longitudinal direction. The blade together with many identical blades forms a ring. Aerofoil sections of the ring are installed radially. Adjacent shelves of the blades are combined in pairs to form a continuous surface between their aerofoil sections, connecting the trough of the aerofoil section with the back of the adjacent aerofoil section. The specified surface in the upper half of the aerofoil section along the flow comprises a ledge located closer to the trough than to the back and a sunk channel arranged between it and the trough. The ledge is separated from the trough by means of the specified sunk channel. Other inventions of the group relate to the area of the turbomachine nozzle block and to the impeller comprising the above blades. Another invention relates to a turbomachine comprising the specified impeller.
 Turbine blade aerodynamic profile (versions) and turbine (versions) / 2350756
Turbine incorporates wheel rotor with multiple blades each comprising aerodynamic profile vane with designed profile corresponding, in fact, to values of Cartesian axials X, Y and Z listed in the table enclosed with the application materials. Z values are dimensionless quantities in the range of 0 to 1 transformed in distances Z expressed in inches by multiplying Z values by the vane height in inches. X and Y are distances in inches that, when conjugated by smooth continuous arcs, define the vane profile cross section at each Z distance. The profile cross sections at Z distances, when smoothly conjugated, form the vane complete shape.
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FIELD: engines and pumps. SUBSTANCE: turbine wheel and rotor blade has pressure side surface (19) and rarefaction side surface (21). Rarefaction side is smooth at its larger portion except for some bulges (25). Bulges are distributed nearby and along rear edge (17). Pressure side surface is smooth. EFFECT: smaller separation zone nearby blade surface charged with disturbances influencing the turbine efficiency. 12 cl, 4 dwg
The invention relates to a turbine blade, in particular to the blade for moving the turbine wheel of the low pressure turbine aircraft engine, and change the aerodynamic characteristics of the blades is improved in such a way as to prevent separation of the boundary layer airflow from the blade surface, mainly on the back of her hand vacuum. In the design of new forms of turbine blades, in particular for blades installed on a wheel of a given stage of the turbine, it is desirable to improve the performance by changing certain structural parameters. In particular, to reduce the weight of the turbine, one possible solution consists in reducing the number of blades, thus requiring that the profiles of the blades were modified to fit the corners of the output, and thus, to the extent possible to compensate for the efficiency loss. The closest analogue of the claimed invention is an aerodynamic surface is disclosed in U.S. patent No. 3578264, according to which fulfill many bumps on the aerodynamic surface to control the delay and offset air flow and increase the effect of heat transfer, which is achieved by performing bumps on a large (if not all) the square of this model is poverhnosti. However, the main disadvantage of this technical solution is that it is impossible to avoid separation of the boundary layer airflow from the surface of the blade at its rear in her hand vacuum. Acting thus, as disclosed in U.S. patent No. 3578264, you can set that has a detrimental risk of relapse air flow from the side of the vacuum. Such turbulent perturbations begin near certain areas of the sides of the depression of the scapula, and they are very harmful for performance. The invention is aimed at ensuring the reduction of these phenomena breakdown. In particular, according to the invention created by the turbine rotor blade with the surface of the discharge side and the surface side of the suction party rarefaction is smooth on most of its surface except for a few bumps, which are distributed around and along the rear edge and the surface of the discharge side is smooth. Preferably, the location of the bumps along the rear edge is chosen in such a way as to be near complete separation zone, calculated without the specified camber. To determine the location of such bumps along the rear edge, the starting point is the modeling of the zone of separation on the side of vacuum (TP whom of which can be obtained by calculation), and then decided to have such a bulge near the zone of maximum disturbance, as defined without the use of such convexity. Acting thus, as a rule, it turns out that at least one bulge is located essentially in the middle of the rear edge. Preferably, other bumps can be located close to the inner radial end of the rear edge and/or near the radial outer end of the rear edge. As a General rule, the calculations lead to the location of many of the bumps so that they are distributed along the outer radial thirds of the rear edge. The form of such convexity, preferably, in a General sense, is a form rounded shoulders, jutting out from the surface side of the vacuum and smoothly connecting with her. Preferably, the average cross-section convexity, taken perpendicular to the rear edge has the shape of a half-wave, which is smoothly connected to the surface side of the vacuum. In the embodiment, another cross-section convexity, taken perpendicular to the middle section has a wave-like shape and includes a Central extremum with damped lateral waves. In other words, as can be seen in this section, the bulge is similar in shape to the wave that is created is rather a flat surface of a liquid falling drop of liquid, when this waveform, however, is not isomorphic in the circumferential direction around a Central point. Preferably, the blade is a working blade. According to the second object of the invention, the set of turbine wheel with blades, which blades of the above type. The invention can be better understood and its other advantages appear more clearly in light of the following description, given only as an example and made with reference to the accompanying drawings, on which: Figure 1 is a detail view in perspective of a wheel of the turbine rotor provided with vanes in accordance with the invention; Figure 2 is a partial section of the blade, showing the profile convexity in accordance with the invention; Figure 3 is a partial section in another plane, showing the profile specified convexity; Figa is a view similar to Figure 3 showing a modification; and 4 is a schematic view showing the step in the method for determining the number and locations of the bumps along the rear edge. Figure 1 shows a set of blades 11 of the rotor, in particular blades, passing mainly radially from the periphery of the disc 13 of the rotor. Typically, each vane having a certain amount of thickness that varies from the front side to the rear side, is curved between the front is th edge 15 and trailing edge 17. Concave section or side 19 of the discharge is smooth. A convex section or side 21 of the vacuum is smooth on most of its surface except for a few bumps 25 in accordance with the invention, which are distributed around and along the rear edge 17. In General, such a bulge 25 preferably has basically the shape of rounded shoulders, jutting out from the surface 21 side of the vacuum and smoothly connecting with her. Preferably, the profile convexity perpendicular to the surface side of the vacuum, where it is located, is changed between the forms shown in figure 2 and 3. Thus, as shown in figure 2, the average cross-section through the bulge 25, taken perpendicular to the rear edge 17 has the form of a simple half-wave, which smoothly connects with the surface of the side 21 of the vacuum. Should be observed that the slope of this half was more gentle toward the front side and steeper toward the rear side. In this section of the protrusion is connected with the rear edge continuously. For comparison, if consideration is given relative to another section of the same convexity, which is perpendicular relative to previous section, i.e. parallel with the rear edge, as shown in Figure 3, we can see that auclast has the form, which is more complex, namely a wave-like form with one or more waves, including the Central extremum 27 and decaying lateral wave 28. In the variant with Figa can be seen that the cross-section convexity 25 contains a lot of evanescent waves on both sides of the extreme. As mentioned above, this section is comparable with the wave, which is formed on the calm surface of a liquid falling drop of liquid. "Revolving" around the bulge, the cross-section varies in a continuous manner from one of these sections to another for one quarter turn. With the preferred form of convexity, which is as defined above, followed by a description of the locations for these protuberances and the way these are defined location. Figure 4 is a diagram showing, from left to right the different stages of the location of the protuberances on the blade 11, if you look at its surface side 21 of depression. The gray portion represents an area of 30 "separation" on the side of the vacuum near the rear edge. You can see that without any convexity, this separation zone 30 passes, practically over the entire height of the blade from the rear edge, with a maximum width of, essentially, in the middle. The analysis of this form leads to the location of the first bumps 25a near the zone of maximum disturbance, i.e. in the middle is opacki, near the rear edge. The result of this first simulation (not shown) shows the reduction of the area of disturbance on the middle height, but also shows constant perturbations on the inner and outer radial ends. This leads to the location of the other bumps 25b near the inner radial end of the rear edge and/or near the outer radial end 25c of the rear edge. Thus, by way of example, when three bumps placed at the location as shown, this corresponds to a variant of implementation, which is shown in figure 1; in this case, the width of the zone of disturbance or zone of separation is reduced, practically across the radial height of the blade, while, nevertheless, maintaining a pronounced zone of disturbance between the Central bulge and the outer bulge. It was found that the application of the method disclosed in the context of the invention, placing fourth convexity 25d along the outer radial thirds of the trailing edge between the Central bulge 25a and the outer bulge 25c serves to reduce this last zone of separation. 1. The turbine rotor blade having a surface (19) on the pressure side and the surface (21) hand vacuum, characterized in that the underpressure is smooth on most of its surface except for a few bumps (25), which RAS is defined near and along the rear edge (17), the surface of the discharge side is smooth. 2. The blade according to claim 1, characterized in that the location of the protuberances (25) along the rear edge is chosen in such a way as to be near zone (30) complete separation, calculated without the specified camber. 3. The blade according to claim 1, characterized in that it contains a bulge (25a), located essentially in the middle of the length of the rear edge. 4. The blade according to claim 1, characterized in that the bumps are mostly the shape of rounded shoulders, jutting out from the surface side of the vacuum and smoothly connecting with her. 5. The blade according to claim 1, characterized in that it contains one bulge (25b) near the inner radial end of the rear edge. 6. The blade according to claim 1, characterized in that it contains one bulge (25c) near the outer radial end of the rear edge. 7. The blade according to claim 1, characterized in that it contains many bumps (25c-25d), distributed radially on the outer third of the back edge. 8. The blade according to claim 1, wherein the average cross section of each convexity perpendicular relative to the rear edge has the shape of a half-wave, which is smoothly connected to the surface side of the vacuum. 9. The blade of claim 8, wherein the slope of the half-wave is more gently sloping towards the front side and more KRU is propelled toward the rear side. 10. The blade of claim 8 or 9, characterized in that the cross-section convexity perpendicular relative to the middle section has a wave-like shape and includes a Central extremum and decaying side of the wave. 11. The blade according to claim 1, characterized in that it is a working blade. 12. The turbine wheel, characterized in that it is equipped with blades, each of which is a blade according to any one of claims 1 to 11.
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