• 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 guide device (1) for a turbine or a compressor formed with an impeller (2) with a number n of guide vanes (L1, L2, ..., Li, Li + 1, ..., Ln) which are arranged in succession on the impeller (2) in the circumferential direction at a non-equidistant, non-uniform distance Δ i, i + 1, Δ i, i + 1 each determining the distance between two guide vanes (Li, Li + 1) immediately following one another in the circumferential direction.
    公开号:CH715415A2
    申请号:CH01092/19
    申请日:2019-08-29
    公开日:2020-04-15
    发明作者:Leitenmeier Christoph；Spengler Sebastian
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to a compressor and a turbine nozzle with a guide device with guide vanes.
    A compressor is a machine (fluid energy machine) that supplies mechanical work to an injected gas, wherein compressors are used for this purpose to compress gases. They increase the pressure and the density of the working gas. Machines where low compression is a side effect when transporting gases are called fans or blowers and are generally not included in the class of compressors. A turbine is a rotating fluid machine that converts the drop in the internal energy of a flowing fluid into mechanical power, namely torque times speed, which it emits again via its shaft.
    A part of its internal energy is extracted from the fluid flow, which is transferred to the rotor blades of the turbine. The turbine shaft is then rotated via these blades and the usable power is used on an output. Because of the high mechanical and thermal stresses due to centrifugal force and the thermal gradients and transients in operation, the turbine impellers are considered a central point in the design of a turbine. In addition to an optimal design in terms of efficiency, structural mechanical aspects are the focus of the design in order to ensure the operational safety of the turbine impellers. An important additional point is the realization of a low turbine mass, since the materials used are typically expensive and a low mass or a low moment of inertia is decisive for the acceleration behavior. For the economical use of such turbines and compressors, the service life of the turbine impellers should be improved and optimized as far as possible. The lifespan of the turbines is limited by material fatigue due to cyclical loads. Low-cycle (LCF) and high-cycle (HCF) fatigue overlap. Due to the high temperatures during operation, creep fatigue represents another damage mechanism for the guide vanes of the turbine wheel.
    It is known that vibration-related breaks on rotor blades of e.g. Radial turbines, which can be attributed to resonance vibrations, are among the most common causes of failures and damage, for example in the case of exhaust gas turbochargers for large diesel engines.
    In a theoretically assumed ideal wheel geometry, in which all guide vanes are shaped identically, the node lines of the vibrations initially have no preferred position with respect to the wheel. However, the guide vanes behave towards each other like coupled oscillators, which are distributed over the circumference of the impeller. The rotor blades are coupled via the connection to the hub. With suitable vibration excitation, there can be a wave-like expansion of the blade vibrations in the circumferential direction. The extent of this effect depends on the actual coupling between the blades.
    The invention is therefore based on the object to avoid the aforementioned disadvantages and to provide a solution in which, in particular, HFC damage to the rotor blades is significantly reduced or avoided.
    This object is achieved by the combination of features according to claim 1.
    A basic idea of the present invention is that the guide vanes are not arranged in a circumferential direction in a sequence of equidistant distances, as is known from the prior art, but rather at an irregular distance, thus in a distance pattern in which the distance is immediate adjacent vane differs. The distance in the circumferential direction can in each case increase or decrease from one guide vane to the next guide vane or, if appropriate, also remain the same in order to then increase or decrease again.
    According to the invention, a turbine nozzle for a turbine or a compressor nozzle for a compressor with an impeller with a number n of guide vanes is formed, which are successively arranged on the impeller in the circumferential direction in a non-equidistant, non-uniform distance Δi, i + 1, Δi , i + 1 each determine the distance from two guide vanes immediately following one another in the circumferential direction (namely the guide vane at position i and the subsequent guide vane at position i + 1). For this purpose, the distance in the circumferential direction along a fixed distance (radius) with respect to the center of the impeller is preferably considered.
    In a preferred embodiment of the invention it is provided that the n guide vanes distributed over the circumference are identical in shape. In an alternative embodiment of the invention, however, it can also be provided that individual or all of the guide vanes are designed differently in shape in at least one partial area. For example, To further stimulate secondary orders and to prevent main modes of harmonic excitation, a change in shape of individual guide vanes also contribute to this result.
    It is furthermore advantageously provided that a plurality of the distances .DELTA.i, i + 1 are each different from two guide vanes which follow one another directly in the circumferential direction. For example, but also all guide vanes can be arranged on the impeller with a different distance in each case related to the immediately adjacent guide vane. For this purpose, it is provided according to the invention that all distances Δi, i + 1 of each two guide vanes which follow one another in the circumferential direction are different, which results in a division pattern in the circumferential direction with n different angular division dimensions (based on 360 °).
    In a further advantageous embodiment of the invention it can be provided that the change in the distance .DELTA.i, i + 1 varies from two guide vanes to the following or preceding distance. In particular, it can be provided that the change in the distance Δi, i + 1 from two guide vanes to one another to the distance Δ i, i + 1 of the preceding one or the distance Δi, i + 1, i + 2 to the respective subsequent guide blade increases or decreases is. As a result, the distance between two successive guide vanes differs from one another over the entire circumference, resulting in a division pattern in the circumferential direction with different angular division dimensions (based on 360 °), for example an exemplary angular distance of consecutively 20 °, 30 °, 27 °, 18 °, ..., 33 °.
    It is further advantageous if the respective distance Δi, i + 1 of two guide vanes in the circumferential direction is determined in accordance with a predetermined division plan in such a way that there is a targeted division of the periodically harmonic vibration excitation into its secondary orders in the event of vibration excitation during operation of the turbine nozzle he follows.
    Another aspect of the present invention relates to a turbine with a turbine nozzle as described above.
    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:<tb> Fig. 1 <SEP> an exemplary schematic embodiment of a turbine nozzle according to the invention.
    The invention is explained in more detail below with reference to FIG. 1, in which FIG. 1 shows a merely exemplary top view of a turbine nozzle 1 with the dividing positions T1 to T15, which shows the mounting positions of the guide blades L1, L2, …, Represent L15.
    The turbine nozzle 1 is designed for a turbine or a compressor and has an impeller 2 with a hub, not shown in the center Z of the impeller 2. The 15 guide vanes L1, L2, ..., Li, Li + 1,. .., L15, are successively arranged on the impeller 2 in the circumferential direction at a non-equidistant, non-uniform distance Δi, i + 1.
    Δi, i + 1 each determines the relative distance in the circumferential direction along a circular arc line of two guide vanes Li, Li + 1 immediately following one another in the circumferential direction.
    As can also be seen in FIG. 1, all the distances Δi, i + 1 from each of two guide vanes Li, Li + 1 immediately following one another in the circumferential direction are different, which results in a division pattern in the circumferential direction with different angular division masses. Nevertheless, certain guide vane spacings can also occur several times, but preferably always with at least one different guide vane spacing between two guide vanes lying between them. For example, the distance between the position of the guide vane L3 and the position of the guide vane L4 be equal to the distance between the position of the guide vane L9 and the position of the guide vane L10.
    The invention is not limited in its implementation to the preferred exemplary embodiments specified above. In this respect, the turbine guide device is suitable both for a turbine or as a compressor guide device for a compressor. 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 (9)
    [1]
    1. Turbine guide apparatus (1) for a turbine or a compressor designed with an impeller (2) with a number n of guide vanes (L1, L2, ..., Li, Li + 1, ..., Ln) which are connected to the impeller (2 ) are arranged in succession in the circumferential direction at a non-equidistant, non-uniform distance Δi, i + 1, where Δi, i + 1 each determines the distance between two guide vanes (Li, Li + 1) which follow one another in the circumferential direction.
    [2]
    2. Turbine nozzle (1) according to claim 1, characterized in that the n guide blades (L1, L2, ..., Li, Li + 1, ..., Ln) are identical in shape.
    [3]
    3. Turbine nozzle (1) according to claim 1, characterized in that the n guide blades (L1, L2, ..., Li, Li + 1, ..., Ln) are designed differently in their shape to at least in a partial area.
    [4]
    4. Turbine guide apparatus (1 j according to claim 1, 2 or 3, characterized in that a plurality of the distances Δ i, i + 1 from two guide vanes (Li, Li + 1) immediately following one another in the circumferential direction is different.
    [5]
    5. Turbine nozzle (1) according to claim 1, 2 or 3, characterized in that all the distances .DELTA.i, i + 1 are different from each two vanes (Li, Li + 1) immediately following one another in the circumferential direction, whereby a division pattern in the circumferential direction is different different angular pitch dimensions.
    [6]
    6. Turbine nozzle (1) according to one of the preceding claims, wherein the change in the distance Δ i, i + 1 of two guide vanes (Li, Li + 1) to the respective subsequent or previous distance is discontinuous.
    [7]
    7. Turbine nozzle (1) according to claim 6, wherein the change in the distance Δ i, i + 1 of two guide vanes (Li, Li + 1) to each other to the distance Δ i, i + 1 of the preceding or the distance Δ i, i + 1, i + 2 is increasing or decreasing to the subsequent guide vane.
    [8]
    8. Turbine nozzle (1) according to any one of the preceding claims, wherein the respective distance Δ i, i + 1 of two guide vanes (Li, Li + 1) in the circumferential direction is determined in accordance with a predetermined division plan so that it is in the operation of the Turbine nozzle (1) is a targeted division of the periodically harmonic vibration excitation in their secondary orders.
    [9]
    9. Turbine with a turbine nozzle (1) according to one of the preceding claims 1 to 8.
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    同族专利:
    公开号 | 公开日
    RU2019129338A|2021-03-18|
    JP2020060186A|2020-04-16|
    KR20200041275A|2020-04-21|
    DE102018125148A1|2020-04-16|
    CN111042873A|2020-04-21|
    US20200116025A1|2020-04-16|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE10326533A1|2003-06-12|2005-01-05|Mtu Aero Engines Gmbh|Rotor for a gas turbine and gas turbine|
    US8684685B2|2010-10-20|2014-04-01|General Electric Company|Rotary machine having grooves for control of fluid dynamics|
    US8678752B2|2010-10-20|2014-03-25|General Electric Company|Rotary machine having non-uniform blade and vane spacing|KR102333202B1|2020-05-07|2021-11-30|청호나이스 주식회사|Air Blower and Air Purifier Including the Same|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102018125148.3A|DE102018125148A1|2018-10-11|2018-10-11|Turbine baffle with bladed baffle|
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