• 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:
    Radial compressor, in particular radial compressor of an exhaust gas turbocharger, with a rotor-side impeller (10) and a stator housing, wherein the impeller (10) comprises a plurality of blades (12), wherein a relation to the vector circumferential speed opposite circumferential direction measured exit angle of each blade is dimensioned such that the radially inner exit angle (β 2 i) and the radially outer exit angle (β 2a) deviate from one another, namely such that the radially inner exit angle (β 2 i) is greater than the radially outer exit angle (β 2a).
    公开号:CH706524B1
    申请号:CH00745/13
    申请日:2013-04-09
    公开日:2017-01-13
    发明作者:Benetschick Hannes
    申请人:Man Diesel & Turbo Se；
    IPC主号:
    专利说明:

    The invention relates to a centrifugal compressor according to the preamble of claim 1.
    From DE 2 524 710 B2 a radial compressor with a fixed Vorleitrad and the Vorleitrad downstream, rotating impeller is known. The impeller has blades, which are characterized by a so-called entry angle and by a so-called exit angle, wherein both the entry angle and the exit angle of the blades of the impeller radially inside a so-called inner section is dimensioned differently than radially outward on a so-called outer section. According to DE 2 524 710 B2, the radially inner exit angle of the moving blades, relative to the circumferential direction, is smaller than the radially outer exit angle of the same. Such a radial compressor is particularly suitable for use in so-called process compressors and has a high efficiency.
    On this basis, the invention is based on the object to provide a novel centrifugal compressor with increased pump stability. This object is achieved by a radial compressor according to claim 1. According to the invention, the radially inner exit angle β 2ij der Blade of the impeller is greater than the radially outer exit angle β 2ajeder the blade of the impeller.
    When radial compressor according to the invention, the radially inner exit angle of the blades of the impeller is greater than the radially outer exit angle of the same. This can improve the pumping stability of a centrifugal compressor. The inventive radial compressor is particularly suitable for use in turbochargers.
    Preferably, the radially inner exit angle β2izwischen 20 ° and 45 °, in particular between 30 ° and 45 °, greater than the radially outer exit angle β2a. Such an angular offset between the radially inner exit angle and the radially outer exit angle of the blades of the impeller is particularly suitable for expanding the working range at the surge line of the centrifugal compressor, so that a centrifugal compressor with increased pump stability can be provided.
    According to an advantageous embodiment of the invention, the radially inner exit angle β2izwischen 45 ° and 90 °. This dimensioning of the radially inner exit angle of the blades of the impeller in conjunction with the above-described angular offset between the radially inner exit angle and the radially outer exit angle of the blades of the impeller is particularly suitable to increase the pumping stability of the centrifugal compressor in an advantageous manner.
    According to an advantageous embodiment of the invention, the centrifugal compressor on a housing-side recirculation structure, via which a recirculating flow upstream of the impeller is miscible with a main flow. Then, when the inventive contouring of the exit angle of the blades is used in conjunction with a housing-side recirculation structure, the pumping stability of the centrifugal compressor can be further improved.
    Preferred embodiments of the invention will become apparent from the independent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawing. Showing:<Tb> FIG. 1: <SEP> is a perspective view of an impeller of a radial compressor according to the invention;<Tb> FIG. 2: <SEP> a meridian section through an advantageous development of the radial compressor according to the invention; and<Tb> FIG. 3 <SEP> is a diagram for further clarification of the invention.
    The present invention relates to a centrifugal compressor, in particular a centrifugal compressor of an exhaust gas turbocharger.
    A radial compressor has at least one rotor-side impeller and a stator-side housing. 1 shows a perspective view of a radial compressor according to the invention, namely an impeller 10 of the centrifugal compressor, FIG. 2 showing a meridian section through the radial compressor in the region of the rotor-side impeller 10 and a stator-side housing 11.
    The rotor-side impeller 10 of the centrifugal compressor has a plurality of blades 12, wherein the blades 12 are characterized on the one hand by an entry angle and on the other hand by an exit angle, which is measured in each case relative to a circumferential direction of the impeller 10.
    The present invention relates to the design of the exit angle β2der blades 12 of the impeller 10, each measured relative to a circumferential direction U of the impeller 10th
    The relative to the circumferential direction U measured exit angle β2der of the blades 12 is dimensioned such that a radially inner exit angle β2iand the radially outer exit angle β2 deviate from each other, namely such that, as shown in Fig. 1, in the region of each blade 12 of the radially inner Exit angle β2 is greater than the outer exit angle β2a.
    With such an inventive design of the exit angle β2der of the blades 12 of the impeller 10 is radially inward on the blading of the impeller 10, a pronounced delay of a so-called relative speed set so that a radially outward displacement effect for the flow begins. As a result, a delay of the relative speed which is typical for centrifugal compressors is moderated radially outwards, whereby the pump stability of the impeller 10 and thus of the entire radial compressor can be increased.
    This gain in pump stability can be used to increase a feasible range of variation for the throughput of the centrifugal compressor over the prior art. Furthermore, this gain in pump stability can be used to increase the realizable compressor pressure ratios, these two effects can also be used in combination with each other.
    The above-mentioned deceleration of the relative speed corresponds to the ratio w2a / w1a, where, for the variable w2aum, the relative velocity of the flow is radially outward at the exit of the impeller 10 and at the size w1aum the relative velocity of the flow is radially outward at the entrance of the impeller 10 is. The relative speeds w1iam entrance and the relative speeds w2iam outlet of the impeller 10 are visualized in Fig. 1 by arrows.
    Fig. 1 further illustrates with an arrow the vector of the rotational movement, the amount of which denotes the so-called angular frequency ω of the compressor 10, wherein for the angular frequency ω holds:ω = 2 * π * n,with the speed n of the impeller 10th
    For the peripheral speed u2 of the blades 12 of the impeller 10 at the exit of the impeller 10, the following relationship applies:u2 = ω * r2,where r2um is the radius of the blades 12 at the exit of the impeller 10. Radial inside, ie with a small radius r2i, the circumferential velocity is smaller than the radial outside at the same angular frequency, ie at a large radius r2a.
    As already mentioned, according to the invention in the region of each blade 12 of the impeller 10, the radially inner exit angle β2igösser than the radially outer exit angle β2a, wherein the radially inner exit angle β2ivorzugsweise at least 10 ° greater than the radially outer exit angle β2a.
    Preferred is a variant of the invention, in which the radially inner exit angle β2ium at least 20 ° greater than the radially outer exit angle β2a is particularly preferred, the radially inner exit angle β2ium at least 30 ° than the radially outer exit angle β2a.
    According to an advantageous embodiment of the invention, the radially inner exit angle β2izwischen 20 ° and 45 °, preferably between 30 ° and 45 °, greater than the radially outer exit angle β2a.
    When radially outer exit angle β2ahandelt it is that angle of the blades 12 at the outlet of the impeller 10, which include the blades 12 at the radially outer end with the circumferential direction of the impeller 10 according to FIG. 1.
    When radially inner exit angle β2ider blades 12 is that angle which the blades 12 radially inside immediately adjacent to a hub of the impeller 10 on the outlet side with the circumferential direction of the impeller 10 according to FIG. 1 include.
    The radially inner exit angle β2iam outlet of the impeller 10 is in the region of each blade 12 is preferably at least 45 °, preferably the radially inner Austrittswinkei β2izwischen 45 ° and 90 °.
    This dimension of the radially inner exit angle β 2 of the rotor blades 12 in conjunction with the angular offset between the radially inner exit angle β 2 i and the radially outer exit angle β 2 a permits the provision of a radial compressor with a particularly advantageous pump stability.
    Fig. 2 illustrates an advantageous development of the inventive radial compressor, wherein in the region of the housing 11 thereof a recirculation structure 13, a so-called casing treatment is formed, namely such that an existing operating points of the radial compressor recirculation flow 14, which the Rezirkulationsstruktur 13 opposite to a main flow 15 flows through, upstream of the impeller 10 with the main flow 15 is miscible. As a result, in combination with the measures described above for configuring the exit angle β2 of the rotor blades 12 of the rotor 10, the pump stability of the radial compressor according to the invention can be further increased.
    Depending on the operating point of the centrifugal compressor can be formed by the recirculation structure 13 and a secondary flow 16 which is parallel to the main flow 15 and downstream of the leading edge of the impeller 10 associated with the main flow 15.
    In the diagram of FIG. 3, a total pressure ratio .DELTA.p of the centrifugal compressor is shown above a volumetric flow V. FIG. 3 shows on the one hand the surge limit attainable with the radial compressor according to the invention and the resulting achievable operating line of the compressor 17. According to FIG. 3, therefore, in the radial compressor according to the invention, the pumping limit 17 can be shifted to smaller values of the volume flow and thus the pump stability can be improved. The reference numeral 18 in Fig. 3, the surge limit of a running according to the prior art radial compressor is shown, wherein the reference numeral 18 indicates the achievable operating line of a radial compressor according to the prior art. The speed lines with constant speed are indicated in Fig. 3 by the reference numeral 19. Reference numeral 20 illustrates the characteristic curve with optimum efficiency for the inventive radial compressor. Reference numeral 21 illustrates the so-called barrier.
    With the invention, in a radial compressor in the region of the impeller 10 radially inside in the region of an internal section a more intense in comparison with the prior art delay of the working medium can be set as radially outside on an outer section. This has the consequence that a part of near-hub energy-rich working medium is displaced to the outer section of the blades 12. This makes it possible to energetically enrich the flow which is critical for radial compressor impellers in the vicinity of the housing and to increase the pumping stability of the radial compressor 10.
    The inventive radial compressor is designed for use in an exhaust gas turbocharger.
    LIST OF REFERENCE NUMBERS
    [0031]<Tb> 10 <September> Wheels<Tb> 11 <September> Housing<Tb> 12 <September> blade<Tb> 13 <September> recirculation<Tb> 14 <September> recirculation<Tb> 15 <September> mainstream<Tb> 16 <September> secondary flow<tb> 17, 18 <SEP> Pumping limit<tb> 17, 18 <SEP> Characteristic / Operating Line Compressor<Tb> 19 <September> speed line<tb> 20 <SEP> optimal efficiency<Tb> 21 <September> cut-off limit
    权利要求:
    Claims (9)
    [1]
    1. Radial compressor, in particular radial compressor of an exhaust gas turbocharger, with a rotor-side impeller (10) and a stator housing (11), wherein the impeller (10) comprises a plurality of blades (12) and wherein a relative to the vector of peripheral speed opposite circumferential direction measured exit angle (β2 ) each blade is dimensioned such that the radially inner exit angle (β2i) and the radially outer exit angle (β2a) differ, characterized in that the radially inner exit angle (β2i) is greater than the radially outer exit angle (β2a).
    [2]
    2. Radial compressor according to claim 1, characterized in that the radially inner exit angle (β2i) by at least 10 ° greater than the radially outer exit angle (β2a).
    [3]
    3. Radial compressor according to claim 1 or 2, characterized in that the radially inner exit angle (β2i) by at least 20 ° greater than the radially outer exit angle (β2a).
    [4]
    4. Radial compressor according to one of claims 1 to 3, characterized in that the radially inner exit angle (β2i) between 20 ° and 45 ° greater than the radially outer exit angle (β2a).
    [5]
    5. Radial compressor according to one of claims 1 to 4, characterized in that the radially inner exit angle (β2i) by at least 30 ° greater than the radially outer exit angle (β2a).
    [6]
    6. Radial compressor according to one of claims 1 to 5, characterized in that the radially inner exit angle (β2i) between 30 ° and 45 ° greater than the radially outer exit angle (β2a).
    [7]
    7. Radial compressor according to one of claims 1 to 6, characterized in that the radially inner exit angle (β2i) is at least 45 °.
    [8]
    8. Radial compressor according to one of claims 1 to 7, characterized in that the radially inner exit angle (β2i) is between 45 ° and 90 °.
    [9]
    9. Radial compressor according to one of claims 1 to 8, characterized by a housing-side recirculation structure (13), via which a recirculating flow upstream of the impeller (10) is miscible with a main flow.
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    同族专利:
    公开号 | 公开日
    DE102012207727B4|2019-04-18|
    DE102012207727A1|2013-11-14|
    CH706524A2|2013-11-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE102018106971A1|2018-03-23|2019-09-26|Man Energy Solutions Se|centrifugal compressors|GB1141198A|1966-03-04|1969-01-29|Colchester Woods|Improvements in or relating to impellers, especially for ventilators|
    DE2414110A1|1974-03-23|1975-10-02|Gutehoffnungshuette Sterkrade|Radial compressor with maximal suction capacity - achieved through reducing impeller blades thickness from the centre to the outside|
    DE2524710B2|1975-06-04|1978-11-02|Gutehoffnungshuette Sterkrade Ag, 4200 Oberhausen|Centrifugal compressor stage|
    EP0112932B1|1982-12-29|1985-06-05|Wilhelm Gebhardt GmbH|Radial ventilator with backwards-curved profiled blades|
    法律状态:
    2018-07-31| PFA| Name/firm changed|Owner name: MAN ENERGY SOLUTIONS SE, DE Free format text: FORMER OWNER: MAN DIESEL AND TURBO SE, DE |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102012207727.8A|DE102012207727B4|2012-05-09|2012-05-09|centrifugal compressors|
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