• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a turbine nozzle (1) for a radial turbocharger, wherein the turbine nozzle (1) comprises a plurality of first annular disk element (10) and a second annular disk element (20) and a plurality of vanes (30) between the first and second annular disk element ( 10, 20) are arranged, is composed, wherein the guide vanes (30) with each annular disk element (10, 20) are cohesively and / or non-positively and / or positively connected.
    公开号:CH714391A2
    申请号:CH01295/18
    申请日:2018-10-22
    公开日:2019-05-31
    发明作者:Haas Bernd；Niebuhr Johannes；Denkel Harald
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    Description [0001] Description:
    The invention relates to a turbine nozzle according to the preamble of claim 1, in particular a turbine nozzle for a radial turbocharger.
    The preferred field of application of the present invention relates to radial turbocompressors or radial turbochargers. In principle, the application of the invention is also conceivable for other compressors or for turbines. In a turbine, fluids generally flow from one or more chambers through a transition piece and along a designated fluid path. A number of turbine stages can typically be arranged in a row along the fluid path so that the fluids flow through so-called diffusers and blades of a first stage and then through diffusers and blades of subsequent stages of the turbine. In this way the turbine nozzles can direct the fluids towards the respective blades, causing the blades to rotate and e.g. drive a consumer, for example an electric generator or the like.
    Most of the compressors used today on the turbocharger are radial compressors, consisting of a radial compressor wheel, the spiral housing with a rear wall and a diffuser. The air is sucked in axially by the rotation of the compressor wheel and accelerated to high speeds. The air accelerated in this way leaves the compressor wheel radially in the direction of the diffuser. Centrifugal turbocompressors are generally used to deliver a process fluid to a higher pressure or a higher density. The process fluid is regularly compressed so that volume contraction takes place in the compression process.
    However, since it is necessary, depending on the application, to adapt the diffusers to the application in terms of their size, shape and design, there is a high degree of product variability and variety of parts. Due to the required variance in blade height and blade profile for turbine nozzles, the manufacturing costs of e.g. cast or manufactured from the solid material or milled diffusers very high due to the many cast models required or the high machining rate.
    It is therefore an object of the present invention to overcome the aforementioned disadvantages and to propose a diffuser which can be produced inexpensively in spite of a high variance in shape, enables high efficiency and has high stability for operation.
    The object is achieved by a turbine nozzle with the features of claim 1.
    In connection with the invention, terms such as axial, tangential, radial or circumferential direction always refer to a rotor axis of the radial turbofluid machine, unless stated otherwise.
    A basic idea of the invention is that the turbine nozzle is composed of several parts from three assemblies, namely a first annular disk element and a second annular disk element and a plurality of guide vanes, which are arranged between the first and second annular disk element.
    According to the invention, therefore, a diffuser, in particular a turbine nozzle for a radial turbocharger, is proposed, the turbine nozzle being composed in several parts of a first annular disk element, a second annular disk element and a plurality of guide vanes, which are arranged between the first and second annular disk element, and wherein the The ends of the guide vanes are connected to each ring disk element in a material and / or non-positive and / or positive manner.
    [0011] This gives a "capped" diffuser. A turbine guide device with capped guide vanes on the one hand enables higher efficiency, as gap losses at the blade tips are avoided and, on the other hand, negative influences of rounding radii at the blade roots are avoided. Furthermore, due to the more rigid structure and the higher resistance to bursting of the turbine wheel, such a turbine nozzle can dissipate more energy than a non-«covered» or cast nozzle and thus offers an additional function as burst protection.
    In an advantageous embodiment of the invention it is provided that the annular disk elements are formed from a different, preferably more ductile material than the material of the guide vanes. The concept according to the invention thus offers the possibility of combining different materials and their properties in a suitable manner (e.g. the choice of a ductile material for the ring disk elements and the selection of a resistant material for the blades in order to reduce erosions).
    Another embodiment is advantageous in which the annular disk elements have correspondingly shaped recesses for fastening the guide vanes and the guide vanes with their respective end sections can be inserted into the corresponding recesses in the annular disk elements or can be introduced there.
    In a further advantageous embodiment of the invention it is provided that the two ring disk elements are aligned in parallel planes to one another and the guide blades extend in a parallel alignment between the two ring disk elements along their extension axis. In this way, the axis of extension also runs parallel to the axis of the turbine nozzle.
    It is further advantageous if the shape of the respective recess in the annular disk element corresponds to the cross-sectional shape of that guide vane in that region of the guide vane which protrudes into this recess. be2
    CH 714 391 A2, it is particularly advantageous if the shape of the recess and the guide vane end are each coordinated in such a way that when the ends of the guide vanes are inserted or mounted in the cutouts, a positive and non-positive connection between the respective guide vane and the respective annular disk element is established becomes. Alternatively or in addition, however, a method for forming a material bond can also be selected.
    In a likewise advantageous embodiment of the invention it is provided that all guide vanes have the same shape, which has a further favorable effect on the assembly and manufacturing costs.
    It has also proven to be particularly advantageous if all the guide vanes run linearly in the direction of their axis of extension and thus without curvature in this direction. Due to their shape, the guide vanes can then be produced inexpensively by continuous casting or milling from rod material and cut or cut to length depending on the blade length required.
    It is further advantageously provided that each washer element has a substantially constant thickness over the entire circumference and the depth of the respective recesses in the washer elements is between 50% and 100% of the thickness of the respective washer element. At a depth of 100%, this means that the cutouts are designed as a continuous opening in the ring element along the entire thickness.
    It is further advantageous if the thickness of the two annular disk elements is different and the thickness of the first annular disk element is preferably approximately twice the thickness, more preferably 175% -225% of the thickness of the second annular disk element. In combination with the different material selection mentioned above, the technical properties of the turbine nozzle can be optimized in this way.
    A further aspect of the present invention relates to a method for producing a turbine nozzle as described above, comprising the steps:
    a. Providing first and second washer members;
    b. Providing a number N of identical guide vanes;
    c. Introducing N recesses into each ring disk element corresponding to the cross-sectional shape of the guide vanes in their end sections at positions such that the guide vanes can be inserted with their direction of extension in parallel alignment with their end sections in the cutouts of the ring disk elements arranged in parallel planes;
    d. Introducing the guide vanes with their respective first end section into the cutouts in the first annular disk element and
    e. Introducing the guide vanes with their respective second end section into the recesses in the second annular disk element and
    f. Establishing a positive connection, frictional connection and / or material connection of the guide vanes with the respective ring disk elements in the area of the cutouts.
    The method can be particularly advantageous if the N shape guide vanes are made from a linearly extending profile by cutting or cutting the profile to the appropriate length. Alternatively, production by means of continuous casting would also be conceivable.
    Other advantageous developments of the invention are characterized in the dependent claims or are shown below together with the description of the preferred embodiment of the invention with reference to the figures. It shows:
    Fig. 1 is a perspective view of an embodiment of a turbine nozzle;
    2 is a plan view of the first annular disk element of the turbine nozzle from FIG. 1,
    3 shows a sectional view along the section line S1-S1 in FIG. 2;
    4 is a plan view of the second annular disk element of the turbine nozzle from FIG. 1,
    Fig. 5 is a sectional view taken along section line S1-S1 in Fig. 4 and
    Fig. 6 is a view of a front end and next to a side edge of a guide vane.
    The invention is described in more detail below using an exemplary embodiment with reference to FIGS. 1 to 6, the same reference symbols indicating the same structural and / or functional features.
    CH 714 391 A2 [0024] FIG. 1 shows a perspective view of an exemplary embodiment of a turbine nozzle 1. The turbine nozzle 1 is composed of several parts from the following components: a first annular disk element 10 (as shown in more detail in FIG. 2), a second annular disk element 20 (as shown in more detail in FIG. 4) and a large number of guide vanes 30 which are related 6 are described in more detail.
    The guide vanes 30 are arranged between the first and second annular disk element 10, 20, the guide vanes 30 being non-positively and positively connected to each annular disk element 10, 20 in this exemplary embodiment, by positive engagement in the pocket-like recesses 11 and 21 in the two washer elements 20, 30 are inserted. The shape of the respective recess 11, 21 of the cross-sectional shape of the guide vane 30 corresponds to the cross-sectional shape of the respective recess 11 or 21 in the connection area, which corresponds to the end section 31 or 32 of the guide vane 30. In this exemplary embodiment, all guide vanes 30 have the same shape.
    The arrangement is such that the two annular disk elements 10, 20 are aligned in parallel planes to one another and the guide vanes 30 extend in a parallel alignment between the two annular disk elements 10, 20 along their axis of extension A.
    2 and 4, the two washer elements 10, 20 are shown in more detail. The two ring disk elements are designed as closed flat and round rings, each with an upper side 12 or 22 and a lower side 13 or 23, respectively. The ring disk elements each have the cutouts 11 and 21 for fastening the guide vanes 30.
    Each washer element 10, 20 has a number of 22 such recesses 11 and 21, which extend over the entire thickness of the respective washer elements 10, 20, which can be seen in the sectional views of FIGS. 3 and 5. At this point it should be mentioned that the number of recesses can also have a number other than 22. The first ring disk element 10 has twice the thickness compared to the second ring disk element 20.
    The guide vanes 30 all have the same shape in this embodiment and are introduced with their respective end sections 31, 32 into the corresponding recesses 11, 21 in the annular disk elements 10, 20. In order to influence the efficiency or the vibration behavior of the guide blades, it is also provided in the sense of the invention that the guide blades have different shapes and / or shapes. 6 shows a view of an end face of an end section 31 and also a side view of the guide vane 30. It can be clearly seen that the guide vane 30 runs linearly in the direction of its axis of extension A and thus has no curvature in this direction. Extension axis A The embodiment of the invention is not limited to the preferred exemplary embodiments specified above. Rather, a number of variants are conceivable which make use of the solution shown, even in the case of fundamentally different types.
    权利要求:
    Claims (11)
    [1]
    claims
    1. turbine guide device (1) for a radial turbocharger, the turbine guide device (1) consisting of several parts consisting of a first ring disk element (10) and a second ring disk element (20) and a plurality of guide vanes (30) which are between the first and second ring disk elements (10, 20) are arranged, is assembled, the guide vanes (30) being connected to each ring disk element (10, 20) in a material and / or non-positive and / or positive manner.
    [2]
    2. Turbine nozzle (1) according to claim 1, characterized in that the annular disc elements (10, 20) are formed from a different, preferably more ductile material than the material of the guide vanes (30).
    [3]
    3. Turbine nozzle (1) according to claim 1 or 2, characterized in that the annular disk elements (10, 20) have recesses (11, 21) for fastening the guide vanes (30) and the guide vanes (30) with their respective end sections (31, 32) are fitted in the corresponding recesses (11, 21) in the annular disk elements (10, 20).
    [4]
    4. Turbine nozzle (1) according to claim 1, 2 or 3, characterized in that the two annular disk elements (10, 20) are aligned with one another in parallel planes and the guide vanes (30) are aligned in parallel between the two annular disk elements (10, 20). extend along their extension axis (A).
    [5]
    5. Turbine nozzle (1) according to one of claims 2 to 4, characterized in that the shape of the respective recess (11, 21) corresponds to the cross-sectional shape of that guide vane (30) in that region of the guide vane (30) which in the corresponding recess (11.21) protrudes.
    [6]
    6. Turbine nozzle (1) according to one of the preceding claims, characterized in that all guide blades (30) have the same shape.
    [7]
    7. Turbine nozzle (1) according to one of the preceding claims, characterized in that all guide blades (30) in the direction of their extension axis (A) are linear and thus without curvature in this direction.
    CH 714 391 A2
    [8]
    Turbine nozzle (1) according to one of claims 2 to 7, characterized in that each annular disk element (10, 20) has a substantially constant thickness over the entire circumference and the depth of the respective recesses (11, 21) in the annular disk elements (10 , 20) is between 50% and 100% of the thickness of the respective annular disk element (10, 20).
    [9]
    9. Turbine nozzle (1) according to one of the preceding claims, characterized in that the thickness of the annular disk elements (10, 20) is different and the thickness of the first annular disk element (10) is preferably approximately twice the thickness, more preferably 175% -225% the thickness of the second annular disc element (20).
    [10]
    10. A method for producing a turbine nozzle (1) according to the features of one of claims 1 to 9, comprising the steps:
    a. Providing a first and a second ring disk element (10, 20);
    b. Providing a number N of identical guide vanes (30);
    c. Introducing N recesses (11, 21) into each annular disc element (10, 20) corresponding to the cross-sectional shape of the guide vanes (30) in their end sections (31, 32) at positions such that the guide vanes with their direction of extension (A) are parallel have their end sections (31, 32) inserted into the recesses (11, 21) of the ring disk elements (10, 20) arranged in each case in parallel planes;
    d. Introducing the guide vanes (30) with their respective first end section (31) into the recesses (11) in the first annular disk element (10) and
    e. Introducing the guide vanes (30) with their respective second end section (32) into the recesses (21) in the second annular disk element (20) and
    f. Establishing a positive connection, frictional connection and / or material connection of the guide vanes (30) with the respective annular disk elements (10, 20) in the area of the cutouts (11, 21).
    [11]
    11. The method according to claim 10, wherein the N shape-matched guide vanes (30) are produced from a linearly extending profile, by cutting off or cutting the profile to an appropriate length.
    CH 714 391 A2
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    引用文献:
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    法律状态:
    优先权:
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