• 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:
    A centrifugal compressor (1) comprising: a compressor impeller (10) having a plurality of impeller blades (12) and a compressor housing having a impeller receiving space (21) for the compressor impeller, wherein clearances formed between the impeller blades form a flow passage (30), each impeller vane relative to a rotation axis (R ) has an axial (13) and a radial flow area (15) and a Strömungsumlenkbereich (14) connecting them, the Axialströmungsbereich has a free end (13.1) having a fluid inlet (31) and at an outer edge (16) of the impeller blade a first Outside diameter (D1a) of the compressor impeller (10) defined, and the compressor housing at an axial position of the first outside diameter defines a first inner diameter (D1G) for the impeller receiving space. In order to increase the usable map width, the Axialströmungsbereich has axially at its free end then on the outer edge of a recess portion (16.1), so that an outer diameter reduction is realized, and the compressor housing along an axial extension (Lax-k) of the recess portion has a projection portion (20.1), so that an inner diameter reduction is realized.
    公开号:CH706223B1
    申请号:CH00516/13
    申请日:2013-02-27
    公开日:2016-09-15
    发明作者:Benetschik 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.
    A centrifugal compressor of the type mentioned in the opening paragraph is e.g. known from DE 10 325 980 A1.
    The operating behavior of a centrifugal compressor can be described by a characteristic map, the pressure ratio being represented by the volume or mass flow through which it is passed. The working range in the map of a centrifugal compressor is limited on the one hand by the surge limit and on the other hand by the stuffing limit and the maximum permissible speed of the centrifugal compressor.
    [0004] The surge limit is the area in the characteristic map in which the flow from the impeller blades of the compressor impeller is released due to insufficient volume flow and excessive pressure conditions. When the surge limit is reached, there is a reversal of the fluid flow through the radial compressor until a stable positive volume flow has set in again and pressure builds up again. This process is repeated in quick succession and can lead to noise and damage to the centrifugal compressor.
    The stuffing limit is the achievement of the maximum volume flow, which is limited or predetermined by the fluid inlet cross-section of the radial compressor and the achievement of the speed of sound at the fluid inlet of a flow passage through the compressor impeller.
    The invention is based on the object of providing a radial compressor according to the preamble of claim 1 in such a way that the radial compressor has a larger usable range of characteristics.
    This is achieved with a radial compressor according to claim 1. Further developments of the invention are defined in the dependent claims.
    According to the invention, a radial compressor has a compressor impeller, which has a base body and a plurality of impeller blades arranged thereon, and a compressor housing with an impeller receiving space formed therein, in which the compressor impeller is arranged rotatably about an axis of rotation, with between the respective impeller blades formed interspaces jointly form a flow passage for a fluid to be compressed, each impeller blade having an axial flow area and a radial flow area for the fluid with respect to the axis of rotation as well as a flow deflection area connecting these, the axial flow area having a free end which has a fluid inlet of the flow passage and at one of the The outer edge of the impeller blade facing away from the base body defines a first outer diameter of the compressor impeller, and wherein the compressor housing is at an axial position of the first outer diameter of the compressor ufrades defines a first inner diameter for the impeller receiving space. The radial compressor according to the invention is characterized in that the axial flow area has a recess section axially at its free end on the outer edge of the impeller blade, so that an outer diameter reduction of the compressor impeller is implemented in relation to the first outer diameter of the compressor impeller, and that the compressor housing along an axial Extension of the recess portion of the axial flow area has a protruding portion, so that an inner diameter reduction of the impeller receiving space is realized in relation to the first inner diameter of the impeller receiving space.
    In other words, according to the invention, the outer contour of the compressor impeller in the inlet or inducer area exhibits a contraction in the meridional flow direction.
    Due to this local contraction of the cross section of the flow passage through the compressor impeller available to the fluid flow, the flow through the blading, which occurs at subsonic speed in the definition range of the meridional contraction over the entire load range, is delayed less than in a conventional radial compressor. In this way, when looking at the height of the respective impeller blades, the aerodynamically most heavily loaded outer section is relieved.
    In this way, the pump stability of the radial compressor is increased, so that the operating range (the width of the usable map) is expanded. This additional gain in usable map width can be used in the form of a larger range of variation in the fluid throughput and / or (in any combination) in the form of an increased compressor pressure ratio. With the increased compressor pressure ratio, e.g. an increased pressure can be provided in front of the inlet of a turbocharged internal combustion engine.
    According to one embodiment of the invention, the recess section defines a minimum outer diameter of the compressor impeller, the projection section defining a minimum inner diameter of the impeller receiving space at an axial position of the minimum outer diameter of the compressor impeller.
    According to a further embodiment of the invention, a ratio of the minimum inner diameter of the impeller receiving space to the first outer diameter of the compressor impeller is less than 1. For easier assembly / disassembly of the radial compressor, according to this embodiment of the invention, at least one housing component should be made in several parts.
    According to another embodiment of the invention, the radial flow area has a free end which defines a fluid outlet of the flow passage and a second outer diameter of the compressor impeller on the outer edge of the impeller blade facing away from the base body, with an outer axial extension of each impeller blade from the axial position of the first outer diameter and an axial position of the second outer diameter of the compressor impeller is limited, and wherein a ratio of the axial extension of the recess section to the outer axial extension of the impeller blade is less than 1.
    Preferably, the ratio of the axial extent of the recess portion to the outer axial extent of the impeller blade is less than 0.7. Furthermore, the ratio of the axial extent of the recess section to the external axial extent of the impeller blade is preferably greater than 0.1.
    According to yet another embodiment of the invention, the recess section of the axial flow area extends as far as the flow deflection area of the impeller blade.
    According to one embodiment of the invention, the compressor impeller defines a third outer diameter corresponding to the first outer diameter of the compressor impeller at a transition between the recess section and the flow deflecting area of the impeller blade on the outer edge of the impeller blade facing away from the base body. The recess section thus preferably merges uniformly into a radius of curvature of the flow deflection region.
    According to yet another embodiment of the invention, the compressor housing defines at an axial position of the transition between the recess section and the flow deflecting area of the impeller blade a second inner diameter corresponding to the first inner diameter of the impeller receiving space for the impeller receiving space. The projection section thus preferably merges uniformly into a radius of curvature of a flow deflection area of the impeller receiving space that corresponds to the flow deflection area of the respective impeller blades.
    According to a further embodiment of the invention, the recess section has a concave arcuate contour along its axial extent, the projection section having a convex arcuate contour along its axial extent.
    In the following, the invention is described in more detail on the basis of preferred embodiments and with reference to the accompanying figures. Fig. 1 shows a meridional section of a conventional radial compressor. Fig. 2 shows a meridional section of a radial compressor according to an embodiment of the invention.
    Fig. 1 shows a meridional section of a conventional radial compressor 1 '. The radial compressor 1 'has a compressor impeller 10' with a base body 11 'and a plurality of impeller blades 12' arranged thereon (only one can be seen in the sectional view of FIG. 1) and a compressor housing 20 'with an impeller receiving space 21' formed therein.
    The compressor impeller 10 'is rotatably arranged in the impeller receiving space 21' about an axis of rotation R ', with intermediate spaces (not shown) formed between the respective impeller blades 12' jointly forming a flow passage 30 'for a fluid to be compressed.
    Each impeller blade 12 'has with respect to the axis of rotation R' an axial flow area 13 'and a radial flow area 15' for the fluid as well as a flow deflection area 14 'connecting these.
    The axial flow area 13 'has a free end 13.1' which defines a fluid inlet 31 'of the flow passage 30' and on an outer edge 16 'of the impeller blade 12' facing away from the base body 11 'an outer diameter D1a' of the compressor impeller 10 '.
    The compressor housing 20 'in turn defines an inner diameter D1G' for the impeller receiving space 21 'at an axial position (viewed along the axis of rotation R') of the outer diameter D1a 'of the compressor impeller 10'.
    The outer diameter D1a 'of the compressor impeller 10' and the inner diameter D1G 'for the impeller receiving space 21' remain essentially constant at least up to the beginning of the flow deflection area 14 'of the impeller blade 12', whereby they are dimensioned so that between the outer edge 16 ' the impeller blade 12 'and the compressor housing 20' a small gap is formed.
    FIG. 2 shows a meridional section of a radial compressor 1 according to an embodiment of the invention.
    As FIG. 2 shows, the radial compressor 1 has a compressor impeller 10 with a base body 11 and a plurality of impeller blades 12 arranged thereon (only one can be seen in the sectional view of FIG. 1) and a compressor housing with an impeller receiving space 21 formed therein .
    The compressor impeller 10 is rotatably arranged in the impeller receiving space 21 about an axis of rotation R, with intermediate spaces (not shown) formed between the respective impeller blades 12 jointly forming a flow passage 30 for a fluid to be compressed.
    With respect to the axis of rotation R, each impeller blade 12 has an axial flow area 13 and a radial flow area 15 for the fluid as well as a flow deflection area 14 connecting these.
    The axial flow region 13 has a free end 13.1 which defines a fluid inlet 31 of the flow passage 30 and a first outer diameter D1a of the compressor impeller 10 on an outer edge 16 of the impeller blade 12 facing away from the base body 11.
    The compressor housing for its part defines a first inner diameter D1G for the impeller receiving space 21 at an axial position (viewed along the axis of rotation R) of the first outer diameter D1a of the compressor impeller 10.
    According to the invention, the axial flow area 13 has a recess section 16.1 axially at its free end 13.1 adjoining the outer edge 16 of the impeller blade 12, so that in relation to the first outer diameter D1a of the compressor impeller 10, an outer diameter reduction (by a depth of the recess section 16.1 ) of the compressor impeller 10 is realized.
    In addition, according to the invention, the compressor housing has a protruding section 20.1 along an axial extension Lax-k of the recess section 16.1 of the axial flow area 13, so that in relation to the first inner diameter D1G of the impeller receiving space 21 an inner diameter reduction (by a height of the protruding section 20.1 ) of the impeller receiving space 21 is realized.
    According to an embodiment of the invention as shown in FIG. 2, the recess section 16.1 defines a minimum outside diameter Da-min of the compressor impeller 10, the projection section 20.1 in turn having a minimum inside diameter DG at an axial position of the minimum outside diameter Da-min of the compressor impeller 10 -min of the impeller receiving space 21 is defined.
    Accordingly, the following rule preferably applies:
    A ratio of the minimum inner diameter DG-min of the impeller receiving space 21 to the first outer diameter D1a of the compressor impeller 10 is preferably less than 1.
    Accordingly, the following rule preferably applies:
    In this case, for easier assembly / disassembly of the radial compressor 1, at least one component of the compressor housing is to be designed in at least two parts with a parting line.
    As can be seen from FIG. 2, the radial flow region 15 has a free end 15.1 which defines a fluid outlet 32 of the flow passage 30 and a second outer diameter D2a of the compressor impeller 10 on the outer edge 16 of the impeller blade 12 facing away from the base body 11.
    According to one embodiment of the invention, an outer axial extent Lax-a of each impeller blade 12 (i.e. an overall axial length of the blading at the outer section) is limited by the axial position of the first outer diameter D1a and an axial position of the second outer diameter D2a of the compressor impeller 10.
    According to an embodiment of the invention as shown in FIG. 2, a ratio of the axial extent Lax-k of the recess section 16.1 to the outer axial extent Lax-a of the impeller blade 12 is less than 1. The ratio of the axial extent Lax-k is more preferred of the recess section 16.1 to the outer axial extension Lax-a of the impeller blade 12 is less than 0.7. In addition, the ratio of the axial extent Lax-k of the recess section 16.1 to the external axial extent Lax-a of the impeller blade 12 is preferably greater than 0.1.
    Accordingly, the following rule preferably applies:
    According to an embodiment of the invention as shown in FIG. 2, the recess section 16.1 of the axial flow area 13 extends as far as the flow deflection area 14 of the impeller blade 12.
    Preferably, the compressor impeller 10 defines a third outer diameter D3a corresponding to the first outer diameter D1a of the compressor impeller 10 at a transition between the recess section 16.1 and the flow deflection region 14 of the impeller blade 12 on the outer edge 16 of the impeller blade 12 facing away from the base body 11.
    In addition, at an axial position of the transition between the recess section 16.1 and the flow deflecting region 14 of the impeller blade 12, the compressor housing defines a second inner diameter D2G for the impeller receiving space 21 corresponding to the first inner diameter D1G of the impeller receiving space 21.
    Finally, according to a further embodiment of the invention as shown in FIG. 2, the recess section 16.1 can have a concave arcuate contour along its axial extension Lax-k, the projection section 20.1 along its axial extension (which is essentially the same as the axial extension Lax -k of the recess section 16.1) can have a convex arcuate contour.
    In the context of the invention, any outer diameter of the compressor impeller 10 and any inner diameter of the impeller receiving space 21 are dimensioned such that a small gap is formed between the outer edge 16 of the impeller blade (s) 12 and the compressor housing.
    In summary, according to the invention, the outer contour of the compressor impeller 10 in the inducer area (in the axial flow section 13) has a contraction applied in the meridional flow direction, i.e. the minimum outer radius or the minimum outer diameter Da-min of the compressor impeller 10 is located meridionally downstream of the leading edge of the blading, i.e. meridional downstream of the free end 13.1 of the axial flow section 13 or of the fluid inlet 31.
    In this way, the pumping stability of the radial compressor 1 is increased, so that the operating range (the width of the usable characteristic map) is expanded. This additional gain in usable map width can be used in the form of a larger range of variation in the fluid throughput and / or (in any combination) in the form of an increased compressor pressure ratio.
    Thus, e.g. an extended engine operating range of an internal combustion engine that is turbo-charged by means of the radial compressor 1 can be covered and / or an increase in its boost pressure can be achieved.
    List of reference symbols
    1 ', 1 radial compressor 10', 10 compressor impeller 11 ', 11 base body 12', 12 impeller blade (s) 13 ', 13 axial flow area 13.1', 13.1 free end 14 ', 14 flow deflection area 15', 15 radial flow area 15.1 free end 16 ́, 16 outer edge 16.1 recess section 20 ́ compressor housing 20.1 protruding section 21 ́, 21 impeller receiving space 30 ́, 30 flow passage 31 ́, 31 fluid inlet 32 fluid outlet D1a ́ outer diameter of compressor impeller D1G ́ inner diameter of impeller receiving space D1a first outer diameter of compressor impeller D2a second outer diameter of compressor impeller outer D3a -min minimum outer diameter of compressor impeller D1G first inner diameter of impeller receiving space D2G second inner diameter of impeller receiving space DG-min minimum inner diameter of impeller receiving space Lax-k axial extension of recess section Lax-a outer axial extension of impeller blade R ', R axis of rotation
    权利要求:
    Claims (10)
    [1]
    1. Radial compressor (1) with:a compressor impeller (10) having a base body (11) and a plurality of impeller blades (12) disposed thereon, anda compressor housing having an impeller receiving space (21) formed therein in which the compressor impeller (10) is rotatably disposed about an axis of rotation (R), wherein interspaces formed between the respective impeller blades (12) together form a flow passage (30) for a fluid to be compressed .wherein each impeller vane (12) has an axial flow area (13) and a fluid radial flow area (15) with respect to the rotation axis (R) and a flow deflection area (14) connecting them;wherein the Axialströmungsbereich (13) has a free end (13.1) having a fluid inlet (31) of the flow passage (30) and on a base body (11) facing away from outer edge (16) of the impeller blade (12) has a first outer diameter (D1a) of Compressor wheel (10) defined, andwherein the compressor housing defines a first inner diameter (D1G) for the impeller receiving space (21) at an axial position of the first outer diameter (D1a) of the compressor impeller (10),characterized in that the Axialströmungsbereich (13) axially at its free end (13.1) then at the outer edge (16) of the impeller blade (12) has a recess portion (16.1), so that with respect to the first outer diameter (D1a) of the compressor impeller ( 10) an outer diameter reduction of the compressor impeller (10) is realized, and in that the compressor housing along an axial extension (Lax-k) of the recess portion (16.1) of the Axialströmungsbereichs (13) has a projection portion (20.1), so that with respect to the first inner diameter (D1G) of the impeller receiving space (21), an inner diameter reduction of the impeller receiving space (21) is realized.
    [2]
    Second radial compressor (1) according to claim 1, wherein the recess portion (16.1) defines a minimum outer diameter (Da-min) of the compressor wheel (10), and wherein the projection portion (20.1) at an axial position of the minimum outer diameter (Da-min) the compressor impeller (10) defines a minimum inner diameter (DG-min) of the impeller receiving space (21).
    [3]
    3. Radial compressor (1) according to claim 2, wherein a ratio of minimum inner diameter (DG-min) of the impeller receiving space (21) to the first outer diameter (D1 a) of the compressor impeller (10) is less than 1.
    [4]
    4. Radial compressor (1) according to one of claims 1 to 3, wherein the radial flow region (15) has a free end (15.1) having a fluid outlet (32) of the flow passage (30) and on the main body (11) facing away from outer edge (16 ) of the impeller vane (12) defines a second outer diameter (D2a) of the compressor impeller (10), wherein an outer axial extent (Lax-a) of each impeller vane (12) from the axial position of the first outer diameter (D1a) and an axial position of the second Outside diameter (D2a) of the compressor impeller (10) is limited, and wherein a ratio of axial extent (Lax-k) of the recessed portion (16.1) to the outer axial extent (Lax -a) of the impeller blade (12) is less than 1.
    [5]
    5. Radial compressor (1) according to claim 4, wherein the ratio of axial extent (Lax-k) of the recessed portion (16.1) to the outer axial extent (Lax -a) of the impeller blade (12) is less than 0.7.
    [6]
    6. Radial compressor (1) according to claim 4 or 5, wherein the ratio of axial extent (Lax-k) of the recess portion (16.1) to the outer axial extent (Lax-a) of the impeller blade (12) is greater than 0.1.
    [7]
    7. Radial compressor (1) according to one of claims 1 to 6, wherein the recessed portion (16.1) of the Axialströmungsbereichs (13) extends to the Strömungsumlenkbereich (14) of the impeller blade (12).
    [8]
    8. Radial compressor (1) according to claim 7, wherein the compressor impeller (10) at a transition between the recess portion (16.1) and the Strömungsumlenkbereich (14) of the impeller blade (12) on the base body (11) facing away from outer edge (16) of the impeller blade ( 12) defines a third outer diameter (D3a) corresponding to the first outer diameter (D1a) of the compressor impeller (10).
    [9]
    9. A radial compressor (1) according to claim 8, wherein the compressor housing (20) at an axial position of the transition between the recessed portion (16.1) and the Strömungsumlenkbereich (14) of the impeller blade (12) has a first inner diameter (D1G) of the impeller receiving space (21 ) corresponding second inner diameter (D2G) defined for the impeller receiving space (21).
    [10]
    10. Radial compressor (1) according to one of claims 1 to 9, wherein the recess portion (16.1) along its axial extent (Lax-k) has a concave arcuate contour, and wherein the projection portion (20.1) along its axial extent a convex arcuate contour having.
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    同族专利:
    公开号 | 公开日
    DE102012203801A1|2013-09-12|
    CH706223A2|2013-09-13|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4257733A|1978-12-26|1981-03-24|Carrier Corporation|Diffuser control|
    DE10223876A1|2002-05-29|2003-12-11|Daimler Chrysler Ag|Compressor, for the turbo charger of an IC motor, has a covering ring at the compressor wheel, radially around the wheel paddles, to form tunnel air flow channels between the paddles between the ring and the hub|
    DE10325980A1|2003-06-07|2004-12-23|Daimlerchrysler Ag|Exhaust gas turbocharger for internal combustion engine has at least one nozzle for subjecting wheel back to cooling fluid arranged close to rotation axis of compressor wheel|
    DE102007035966A1|2007-07-30|2009-02-05|Bosch Mahle Turbosystems Gmbh & Co. Kg|Radial compressor for a turbocharger|
    JP5039673B2|2008-02-27|2012-10-03|三菱重工業株式会社|Strut structure of turbo compressor|
    DE102008026744A1|2008-06-04|2009-01-22|Daimler Ag|Blower for an internal combustion engine's exhaust gas turboblower has a blower casing and a blower wheel fitted inside the blower casing|DE102013020826A1|2013-12-17|2015-06-18|Man Diesel & Turbo Se|Radial compressor stage|
    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
    DE201210203801|DE102012203801A1|2012-03-12|2012-03-12|Centrifugal compressor for combustion engine, has projection portion provided along axial extension of recess portion, so that inner diameter reduction of wheel receiving space is realized based on inner diameter of receiving space|
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