US20170321713A1 - Compressor having a sealing channel - Google Patents
Compressor having a sealing channel Download PDFInfo
- Publication number
- US20170321713A1 US20170321713A1 US15/523,838 US201515523838A US2017321713A1 US 20170321713 A1 US20170321713 A1 US 20170321713A1 US 201515523838 A US201515523838 A US 201515523838A US 2017321713 A1 US2017321713 A1 US 2017321713A1
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- United States
- Prior art keywords
- compressor
- rotor
- section
- housing
- recited
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/083—Sealings especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
- F04D17/105—Centrifugal pumps for compressing or evacuating with double suction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
- F04D17/12—Multi-stage pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/056—Bearings
- F04D29/057—Bearings hydrostatic; hydrodynamic
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/10—Shaft sealings
- F04D29/102—Shaft sealings especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
- F04D29/286—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors multi-stage rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/44—Free-space packings
- F16J15/447—Labyrinth packings
- F16J15/4472—Labyrinth packings with axial path
Definitions
- the present invention relates to a compressor.
- a turbocompressor is described in German Patent Application No. DE 10 2012 012 540 A1 that has a first compressor stage having a first compressor impeller, and a second compressor stage having a second compressor impeller.
- the first and second compressor impeller are mounted on a shared shaft, and the shaft is supported contactlessly.
- a sealing gap is configured between the first and second compressor stage.
- a groove is provided in the housing.
- the compressor impeller has a flange that engages into the groove.
- the object of the present invention may be achieved by the compressor in accordance with the present invention.
- An example compressor in accordance with the present invention may have the advantage of enhancing the configuration of the sealing channel between a compressor chamber and a lower-pressure zone.
- an axial force acting on the rotor is reduced.
- Leakage through the sealing channel is also reduced.
- the rotor's resistance to rotation is relatively low.
- the sealing channel has at least two throttling sections; in each of the two throttling sections, in the direction of flow viewed from the compressor chamber to the lower-pressure zone, a first section having a reduced cross section of the sealing channel being first provided, and a second section having an enlarged cross section of the sealing channel being subsequently provided.
- the first section accelerates the leakage flow.
- the second section decelerates the leakage flow and reduces the pressure thereof.
- the rotor and the housing each have a contour in the form of stages.
- the stages are formed and configured in a way that allows the two throttling sections to be realized.
- This specific embodiment has the advantage of permitting a simple and cost-effective manufacturing of graduated contours and a precise realization of the desired function of the two throttling sections.
- the contours have the form of ascending and descending stairs that are associated with one another accordingly in order to form the two throttling sections.
- a first contour has the form of a radial web, and the second contour the form of a radial recess.
- the web engages into the recess.
- both the radial as well as the axial distances between the contours maybe used to form the first and the second section of the throttling sections.
- the recess may be bounded by side walls of different heights, as viewed in a radial direction.
- the web may be bounded by two side walls of different heights, as viewed in an axial direction.
- the first portion of a throttling section is formed by a constriction that is disposed radially relative to an axis of rotation of the rotor and between the compressor impeller and the housing.
- the second portion of the throttling section is realized by an axial distance that, viewed in the axial direction, is disposed parallel to the axis of rotation of the rotor and between the rotor and the housing. The design of the throttling sections is thereby realized with the aid of a compact contour.
- Another specific embodiment provides that at least three or more throttling sections be successively configured in the sealing channel, as viewed in the flow direction. This reduces the leakage through the sealing gap.
- Tests have shown that a very low leakage is achieved at a low resistance to rotation and a high axial force by configuring the contours in the form of a recess and a web.
- the web which engages into the recess, feature a first portion that extends from the housing or the rotor and merges radially into a second portion. Viewed in a plane of an axis of rotation of the rotor, the first portion has a smaller width than the second portion.
- the second portion of the web feature an annular first surface that is disposed radially at the end face and is associated with an annular second surface of the recess that is disposed radially at the end face.
- the first and second surface are oriented mutually in parallel. This further enhances the sealing.
- the rotor features a first compressor impeller on a first side and a second compressor impeller on a second, opposite side.
- two compressor impellers may be used to realize a low-pressure stage and a high-pressure stage.
- the sealing channel is thereby configured between the high-pressure stage and the low-pressure stage.
- the contours provided optimize the sealing channel.
- the compressor impeller may be supported contactlessly in the housing, the sealing channel being configured in the area of the bearing.
- a sealing element is provided that constitutes at least one side of a throttling section, respectively one side of a first or second portion of a throttling section.
- the sealing element is made of a softer material than the housing or the compressor impeller. It is thus possible to improve the sealing.
- the sealing element is formed on the housing; a radial recess being configured on the sealing element, and a radial web, which engages into the recess of the sealing element, being formed on the rotor.
- the compressor may be designed as a turbocompressor.
- FIG. 1 shows a first specific embodiment of a compressor having a rotor including a compressor impeller on one side.
- FIG. 2 shows a second specific embodiment of a compressor having a rotor including two compressor impellers.
- FIG. 3 shows a specific embodiment of a rotor that is supported on a shaft.
- FIG. 4 shows a specific embodiment of a compressor; a sealing element being configured on the rotor.
- FIG. 5 shows a specific embodiment of a compressor; a sealing element being configured on the housing.
- FIG. 6 through 10 show various specific embodiments of contours between the housing and the rotor.
- FIG. 11 through 14 show various specific embodiments of contours in the form of a web and a recess for realizing the sealing channel.
- FIG. 15 shows another specific embodiment of a compressor.
- FIG. 16 shows another specific embodiment of a compressor.
- FIG. 17 shows an additional specific embodiment of a compressor.
- FIG. 18 shows an enlarged representation of the sealing channel of the specific embodiment of FIG. 17 .
- FIG. 19 shows another specific embodiment of a compressor.
- FIG. 1 shows a schematic cross section through a part of a compressor 1 that has a housing 2 and a rotor 3 .
- Rotor 3 is designed to be axially symmetric to an axis of rotation 4 .
- On a first side rotor 3 has a first compressor impeller 5 having rotor blades.
- a first compressor chamber 6 is configured between first compressor impeller 5 and housing 2 .
- first compressor chamber 6 has an annular first intake duct 7 .
- a sealing channel 11 which allows first compressor chamber 6 to communicate with a zone having a lower pressure 12 , is configured between a radial exterior 9 of rotor 3 and an associated interior 10 of housing 2 .
- Rotor 3 may be rotationally mounted in the region of sealing channel 11 , for example, via a contactless bearing in housing 2 .
- rotor 3 may also be connected to a shaft (not shown) that is located in axis of rotation 4 and is rotationally mounted on housing 2 .
- FIG. 2 shows a specific embodiment of a compressor 1 that is fabricated in accordance with the compressor of FIG. 1 ; on a second side, however, rotor 3 having a second compressor impeller 13 having second rotor blades.
- a second compressor chamber 14 is configured between second compressor impeller 13 and housing 2 .
- second compressor chamber 14 has a second intake duct 15 .
- a second compression channel 16 is provided in housing 2 .
- Second compressor impeller 13 is designed to be axially symmetric to axis of rotation 4 .
- Second compressor chamber 14 communicates via sealing channel 11 with first compressor chamber 6 .
- second intake duct 15 may communicate with first compressor channel 8 via a line that is schematically indicated by an arrow.
- First compressor impeller 5 pre-compresses the medium; a second, higher compression of the pre-compressed medium, that is subsequently output via second compression channel 16 , being achieved by second compressor impeller 13 .
- FIG. 3 shows a specific embodiment of a compressor 1 in accordance with FIG. 2 having a rotor 3 having two compressor impellers 5 , 13 , that are located on opposite sides.
- rotor 3 is rotationally mounted on housing 2 via a shaft 19 .
- the specific embodiment of FIG. 1 may also include a rotor 3 having only one first compressor impeller 5 that is mounted via a corresponding shaft 19 on housing 2 .
- FIG. 4 shows the variant of the compressor of FIG. 2 ; an annular sealing element 17 , which engages into an annular recess 18 of housing 2 , being provided on rotor 3 in the area of sealing channel 11 .
- Sealing element 17 is made of a different material than rotor 3 , for example. In particular, a softer material may be used to manufacture sealing element 17 in order to enhance the desired sealing function. Sealing element 17 may be made of a plastic material, for example. In the case of a compressor 1 , sealing element 17 may also be provided with a rotor 3 having only one first compressor impeller 5 in accordance with the specific embodiment of FIG. 1 .
- FIG. 5 shows another specific embodiment of the compressor of FIG. 2 , an annular sealing element 17 being configured on an inner side 10 of housing 2 . Sealing element 17 engages into an annular second recess 18 of outer side 9 of rotor 3 .
- Compressor 1 of FIG. 1 having a rotor 3 having only a first compressor impeller 5 may likewise feature a sealing element 17 and a recess 18 in accordance with FIG. 5 .
- FIG. 6 through 10 show various graduated contours 21 , 22 of inner side 10 of housing 2 and of outer side 9 of rotor 3 that are associated with one another.
- every contour 21 , 22 may be realized by rotor 3 or by housing 2 .
- every contour 21 , 22 maybe at least partially or completely realized by a sealing element 17 or have a sealing element 17 that is joined to housing 2 , respectively to rotor 3 .
- FIG. 6 shows an enlarged, schematically illustrated detail view of sealing channel 11 that is configured between a first and a second contour 21 , 22 .
- FIG. 6 shows a cross section through a plane of axis of rotation 4 . Both the first and the second contour are designed to be axially symmetric relative to axis of rotation 4 . Axis of rotation 4 may be located below second contour 22 , for example.
- second contour 22 is constituted of rotor 3 or of a sealing element thereof.
- First contour 21 is constituted of inner side of housing 2 or at least partially of a sealing element thereof.
- axis of rotation 4 may also be located above first contour 21 .
- first contour 21 is constituted of rotor 3 or at least partially of a sealing element thereof.
- second contour 22 is constituted of an inner side of housing 2 or at least partially of a sealing element of housing 2 .
- first contour 21 features an annular web 24 in a flow direction 23 from a higher-pressure zone toward a lower-pressure zone.
- the higher-pressure zone may be constituted of first compressor chamber 6 in the case of a rotor 3 having only one first compressor impeller 5 or of second compressor chamber 14 in the case of a rotor 3 having a first and a second compressor impeller 5 , 13 .
- Web 24 has the same radial height on both sides.
- Second contour 22 has a radial recess in the form of a groove 28 . Groove 28 is designed to be wider than web 24 in the axial direction, i.e., parallel to axis of rotation 4 . Moreover, web 24 projects radially into groove 28 .
- first contour 21 has a first annular surface 31 , a second annular surface 32 , and a third annular surface 33 .
- First and third annular surface 31 , 33 are configured at the same radial distance to axis of rotation 4 .
- Second annular surface 32 bounds web 24 ; second annular surface 32 having a greater or smaller distance to axis of rotation 4 than first or third annular surface 31 , 33 , depending on the location of axis of rotation 4 .
- second contour 22 has another first, second and third annular surface 41 , 42 , 43 .
- First and second further annular surface 41 , 42 are configured at the same radial distance to axis of rotation 4 .
- Second further annular surface 42 bounds groove 28 ; second further annular surface 42 having a greater or smaller distance to axis of rotation 4 than further first or third annular surface 41 , 43 , depending on the location of axis of rotation 4 .
- Web 24 has a first axial annular surface 35 and an opposite, second axial annular surface 36 ; relative to flow direction 23 , first, axial annular surface 35 being configured upstream from second, axial annular surface 36 .
- Groove 28 is bounded by a first and a second axial annular surface 45 , 46 . Relative to flow direction 23 , first, axial annular surface 45 is configured upstream from second, axial annular surface 46 .
- Contours 21 , 22 may be subdivided axially into five sections 51 , 52 , 53 , 54 , 55 .
- First section 51 extends in flow direction 23 to further first axial annular surface 45 .
- Second section 52 extends axially from axial annular surface 45 to first axial annular surface 35 .
- Third section 53 extends from first, axial annular surface 35 to second, axial annular surface 36 .
- Fourth section 54 extends from second, axial annular surface 36 to further, second axial annular surface 46 .
- Fifth section 55 extends from further, second axial annular surface 46 to the end of first and second contour 21 , 22 .
- first, third and fifth sections 51 , 53 , 55 radial distances 71 , 72 , 73 between the contours are crucial to influencing the flow in sealing channel 11 .
- second and fourth section 52 , 54 axial distances 81 , 82 between the side surfaces of the contours are important for influencing the flow.
- the radial distances between contours 21 , 22 in first, third and fifth section 51 , 53 , 55 , and the axial distances between contours 21 , 22 in second and in fourth section 52 , 52 may be appropriately selected as a function of the selected specific embodiment, in order to provide at least two, preferably three throttling sections.
- radial distances 71 , 72 , 73 of first, third and fifth section between contours 21 , 22 may be selected to be smaller than axial distances 81 , 82 between contours 21 , 22 in second and fourth section 52 , 54 .
- axial and radial distances 71 , 72 , 73 , 81 , 82 between contours 21 , 22 may be variably defined in order to realize the desired throttling sections. Tests have shown that a cost effective manufacturing of at least the same quality is achieved for the sealing of the sealing channel when radial distances 71 , 72 , 73 in first, third and fifth section 51 , 53 , 55 between the surfaces of contours 21 , 22 are selected to be smaller than axial distances 81 , 82 in second and fourth section 52 , 54 between contours 21 , 22 .
- Axial and/or radial distances 71 , 72 , 73 , 81 , 82 may be within the range of between 10 and 500 ⁇ m or more.
- the length of sealing channel 11 may be within the range of between 1 and 15 mm or more.
- the sections in FIG. 6 may be partitioned to allow web 24 to take up approximately one third of the length of the sealing channel, and the regions to the sides of web 24 each one third of sealing channel 11 .
- Tests have shown that effective results are obtained at a ratio of radial distance 71 , 72 , 73 in first, third and fifth section 51 , 53 , 55 to an axial distance 81 , 82 in second and fourth section 52 , 54 within the range of between 1:3 or more.
- effective results are obtained at an axial distance 81 , 82 in second and fourth section 52 , 54 of 100 to 200 ⁇ m, and at a radial distance 71 , 72 , 73 in first, third and fifth section 51 , 53 , 55 of between 10 and 30 ⁇ m.
- the axial and radial distances in the sections may be selected to be different or of equal value. Tests have shown that effective results are obtained at radial and/or axial distances of equal value, respectively.
- FIG. 7 shows another specific embodiment of sealing channel 11 ; viewed in flow direction 23 , first contour 21 having a stepped contour having a decreasing thickness, and second contour 22 having a stepped contour having an increasing thickness.
- First and second contour 21 , 22 are designed to be axially symmetric to axis of rotation 4 .
- first contour 21 has a first annular surface 31 , a second annular surface 32 , and a third annular surface 33 .
- First radial annular surface 31 merges via a first axial annular surface 35 into second radial annular surface 32 .
- Second radial annular surface 32 merges via a second axial annular surface 36 into third radial annular surface 33 .
- axis of rotation 4 is located in the middle of second contour 22 .
- Annular surfaces 31 , 32 , 33 are oriented parallel to axis of rotation 4 .
- First annular surface 31 features a smaller distance to axis of rotation 4 than second annular surface 32 .
- Third annular surface 33 features a larger distance to axis of rotation 4 than second annular surface 32 . If axis of rotation 4 is located in the middle of first contour 21 , the radial distance between the annular surfaces and axis of rotation 4 decreases by steps in flow direction 23 .
- second contour 22 has another first, second and third annular surface 41 , 42 , 43 .
- Further first radial annular surface 41 merges via a further first axial annular surface 45 into further second radial annular surface 42 .
- Further second radial annular surface 42 merges via a further second axial annular surface 46 into further third radial annular surface 43 .
- Further first, second and third annular surfaces 41 , 42 , 43 each features an increasing radial distance from axis of rotation 4 . If axis of rotation 4 is located in the middle of first contour 21 , then the radial distance between the annular surfaces and axis of rotation 4 decreases by steps in flow direction 23 .
- first axial annular surface 35 and further first radial annular surface 45 overlap radially in each particular case.
- an axial sealing gap having a first axial distance 81 is formed.
- second, axial annular surface 36 and further, second radial annular surface 46 overlap radially.
- a second axial sealing gap having a second axial distance 82 is formed.
- Contours 21 , 22 may be subdivided axially into five sections 51 , 52 , 53 , 54 , 55 .
- First section 51 extends in flow direction 23 to further first axial annular surface 45 .
- Second section 52 extends axially from axial annular surface 45 to first axial annular surface 35 .
- Third section 53 extends from first axial annular surface 35 to second axial annular surface 36 .
- Fourth section 54 extends from second axial annular surface 36 to further, second axial annular surface 46 .
- Fifth section 55 extends from further, second axial annular surface 46 to the end of first and second contours 21 , 22 .
- first, third and fifth sections 51 , 53 , 55 radial distances 71 , 72 , 73 between the contours are crucial to the influencing of the flow.
- second and fourth sections 52 , 54 axial distances 81 , 82 between the side surfaces of the contours are important for influencing the flow.
- Radial distances 71 , 72 , 73 between contours 21 , 22 in first, third and fifth sections 51 , 53 , 55 , and axial distances 81 , 82 between contours 21 , 22 in second and fourth sections 52 , 54 may be appropriately selected as a function of the selected specific embodiment, in order to provide at least two, preferably three throttling sections.
- radial distances 71 , 72 , 73 of first, third and fifth sections between contours 21 , 22 may be selected to be smaller than axial distances 81 , 82 between contours 21 , 22 in second and fourth sections 52 , 54 .
- axial and radial distances 71 , 72 , 73 , 81 , 82 between contours 21 , 22 may be variably defined in order to realize the desired throttling sections.
- FIG. 8 shows a specific embodiment of a compressor 1 that essentially corresponds to FIG. 6 ; however, first contour 21 being formed on rotor 3 and second contour 22 on housing 2 . Axis of rotation 4 is located in the middle of second contour 22 .
- FIG. 9 shows another specific embodiment of a compressor 1 that is disposed mirror-symmetrically to the specific embodiment of FIG. 7 relative to flow direction 23 .
- FIG. 10 shows another specific embodiment that essentially corresponds to the specific embodiment of FIG. 5 ; however, first and third annular surfaces 31 , 33 having different radial distances to axis of rotation 4 .
- further first annular surface 41 and further third annular surface 43 have different radial heights.
- first axial annular surface 35 and further, first radial annular surface 45 overlap radially in each particular case.
- an axial sealing gap having a first axial distance 81 is formed.
- second axial annular surface 36 and further second, radial annular surface 46 overlap radially.
- a second axial sealing gap having a second axial distance 82 is formed.
- first axial sealing gap is longer than second axial sealing gap.
- the second axial sealing gap may also be configured to be longer.
- FIG. 11 through 14 show different specific embodiments of FIG. 5 ; the specific embodiments differing in the height of web 24 , respectively in the depth of groove 28 .
- radial distances 71 , 72 , 73 between first, second and third annular surface 31 , 32 , 33 and the associated further first, further second, and further third annular surface 41 , 42 , 43 are each equal.
- First axial annular surface 35 and further, first radial annular surface 45 overlap axially.
- an axial sealing gap having a first axial distance 81 is formed.
- second axial annular surface 36 and further, second radial annular surface 46 overlap radially.
- a second, axial sealing gap having a second, axial distance 82 is formed.
- axial sealing gaps 91 , 92 are longer relative to the axis of rotation in FIG. 11 than in FIG. 12 .
- axial sealing gaps are longer relative to the axis of rotation 4 in FIG. 12 than in FIG. 13 ; viewed radially, the sealing gaps in FIG. 13 being longer than in FIG. 11 .
- radial distances 71 , 72 , 73 between first, second and third annular surfaces 31 , 32 , 33 and the associated further first, further second, and further third annular surfaces 41 , 42 , 43 are smaller than in FIG. 11 through 13 .
- Axial distances 81 , 82 between the side walls of groove 28 and the side walls of web 24 may vary within the range of between 50 and 250 ⁇ m, for example.
- Radial distances 71 , 72 , 73 may vary within the range of between 10 and 100 ⁇ m, for example.
- first contour 21 may be configured on the housing and second contour 22 on the rotor, or first contour 21 on the rotor and second contour 22 on the housing.
- first or second contour 21 , 22 i.e., one section of a contour, in particular web 24 may be configured in the form of a sealing element 17 .
- entire first and/or second contour 21 , 22 may also be formed on a sealing element 17 .
- FIG. 15 shows a portion of a compressor 1 ; housing 2 having a sealing element 17 that extends between compressor impellers 5 , 13 .
- sealing element 17 On a front side, sealing element 17 has a circumferentially extending groove 28 and thus the form of second contour 22 .
- first contour 21 Configured on rotor 3 is first contour 21 having web 24 that extends into groove 28 of second contour 22 .
- Formed in this specific embodiment are further axial distances 83 , 84 between compressor impellers 5 , 13 and sealing element 17 within the range of between 50 and 250 ⁇ m, for example.
- radial distances 71 , 72 , 73 between first and second contour 21 , 22 are configured in the region of first, third, and fifth section 51 , 53 , 55 within the range of between 10 and 30 ⁇ m.
- axial distances 81 , 82 are configured between first and second contour 21 , 22 in the region of second and fourth section 52 , 54 within the range of between 50 and 250 ⁇ m.
- first contour 21 may likewise be configured in the form of a sealing element or at least of a different material than the rotor and compressor impellers 5 , 13 thereof.
- first contour 21 may be fabricated of a separate component that is secured to rotor 3 .
- FIG. 16 shows another specific embodiment that essentially corresponds to the specific embodiment of FIG. 15 ; however, the depth of the recess being smaller on the inner side of sealing element 17 .
- the axial and radial distances are retained.
- the depth of the recess may be within the range of 1 mm.
- first contour 21 may be machined from the material of rotor 3 , as shown in the illustrated example.
- FIG. 17 shows a portion of a compressor 1 having a design similar to that of FIG. 15 ; however, first contour 21 being formed on housing 2 and second contour 22 on rotor 3 .
- first contour 21 has the distinctive feature that web 24 has a first web portion 61 that merges radially inwardly toward axis of rotation 4 into a second web portion 62 .
- the diameter of first web portion 61 is smaller than that of second web portion 62 .
- the diameter of first web portion 61 may be half of that of second web portion 62 , for example.
- second web portion 62 has a smaller width than sealing element 17 that projects into the clearance space between compressor impellers 5 , 13 .
- sealing element 17 may have an annular recess 63 in fifth section 55 that provides for a one-sided flattening of sealing element 17 .
- housing 2 may also feature first contour 21 .
- second contour 22 may also be at least partially realized by a sealing element 17 .
- FIG. 18 shows an enlarged representation of FIG. 17 ; in first section 51 , there being a first small radial distance 71 between first and second contour 21 , 22 .
- the cross section subsequently widens in the area of second section 52 which is additionally enlarged by the thinner formation of first web portion 61 .
- third section 53 there is again a small, radial second distance 72 between contours 21 , 22 .
- An enlarged cross section is subsequently again provided by the small width of first web portion 61 in fourth section 54 .
- fifth section 55 the overlapping of the first and second contour is shortened axially in comparison to first section 51 .
- sealing element 17 in this area has an annular recess 63 in the form of a chamfer.
- a relatively large space for expanding the medium is provided in the area of chamfer 63 .
- this specific embodiment achieves more space for expanding the medium downstream of the radial sealing gaps realized by radial distances 71 , 72 , 73 .
- the radial gap seals used are insensitive to axial deformations or forces.
- the specific embodiment of FIGS. 17 and 18 provides a substantial acceleration three times through sections 51 , 53 and 55 and a corresponding subsequent deceleration of the leakage medium in sections 52 , 53 and 56 .
- the acceleration is achieved in radial sealing gaps that are located on the smallest possible radii.
- the subsequent deceleration is achieved by a deceleration of the flow cross section following the acceleration.
- the leakage medium is considerably accelerated in first section 51 ; a deceleration being achieved in second section 52 .
- the leakage medium is accelerated, in turn, in third section 53 , and is again decelerated in fourth section 54 .
- an acceleration takes place in fifth section 55 , and, again, a deceleration in sixth section 56 .
- FIG. 19 shows another specific embodiment of a compressor 1 that essentially corresponds to the specific embodiment of FIG. 17 ; in contrast to FIG. 17 , however, the compressor only having a first compressor impeller 5 .
- the shapes illustrated in the figures for the surfaces that bound sealing channel 11 are shown as contours that have an angular cross section.
- the angular contours may also be formed as rounded contours.
- convex and/or concave contours may, therefore, oppose one another to form sealing channel 11 .
- groove 28 and/or web 24 may have rounded edges in cross section, so that a concave and a convex shape oppose one another in order to form sealing channel 11 .
- recess 18 and/or sealing element 17 may have rounded edges in cross section, so that a concave and a convex shape oppose one another in order to form sealing channel 11 .
- the stepped structures of FIGS. 7 and 8 may likewise have rounded corners in cross section.
- concave and convex surfaces, which bound sealing channel 11 oppose one another.
- first and/or second and/or third annular surface 31 , 32 , 33 may also be oriented to not be parallel to axis of rotation 4 .
- first and/or second and/or third annular surface 31 , 32 , 33 may be oriented obliquely to axis of rotation 4 at different angles.
- further first and/or further second and/or further third annular surface 41 , 42 , 43 which are shown parallel to the axis of rotation in the figures, may also be oriented to not be parallel to axis of rotation 4 .
- further first and/or further second and/or further third annular surface 41 , 42 , 43 may be oriented at different rotational angles to axis of rotation 4 .
- first and/or second axial annular surface 35 , 36 may be oriented at angles not equal to 90° to axis of rotation 4 .
- first and/or further second axial annular surface 45 , 46 may also be oriented at angles not equal to 90° to axis of rotation 4 .
Abstract
A compressor having a housing and a rotor, the rotor having a compressor impeller at least on one side; a compressor chamber being configured between the compressor impeller and the housing; the rotor being rotationally mounted; an annular sealing channel being configured between the rotor and the housing; the sealing channel being routed from the compressor chamber to a lower-pressure zone; at least two throttling sections being provided in the sealing channel; in each of the two throttling sections, in the direction of flow viewed from the compressor chamber to the lower-pressure zone, a first section having a reduction in the cross section of the sealing channel being first provided, and a second section having an enlargement of the cross section of the sealing channel being subsequently provided.
Description
- The present invention relates to a compressor.
- A turbocompressor is described in German Patent Application No. DE 10 2012 012 540 A1 that has a first compressor stage having a first compressor impeller, and a second compressor stage having a second compressor impeller. The first and second compressor impeller are mounted on a shared shaft, and the shaft is supported contactlessly. A sealing gap is configured between the first and second compressor stage. To seal the sealing gap, a groove is provided in the housing. In addition, the compressor impeller has a flange that engages into the groove.
- It is an object of the present invention to provide a compressor that will feature an enhanced sealing of the sealing channel.
- The object of the present invention may be achieved by the compressor in accordance with the present invention.
- Specific embodiments of the present invention are described herein.
- An example compressor in accordance with the present invention may have the advantage of enhancing the configuration of the sealing channel between a compressor chamber and a lower-pressure zone. In particular, an axial force acting on the rotor is reduced. Leakage through the sealing channel is also reduced. Moreover, the rotor's resistance to rotation is relatively low.
- These advantages are achieved in that the sealing channel has at least two throttling sections; in each of the two throttling sections, in the direction of flow viewed from the compressor chamber to the lower-pressure zone, a first section having a reduced cross section of the sealing channel being first provided, and a second section having an enlarged cross section of the sealing channel being subsequently provided. The first section accelerates the leakage flow. The second section decelerates the leakage flow and reduces the pressure thereof. By serially positioning the two throttling sections, the desired sealing is achieved in the context of a small axial force on the compressor impeller and a negligible loss of compressor output.
- In one specific embodiment, the rotor and the housing each have a contour in the form of stages. The stages are formed and configured in a way that allows the two throttling sections to be realized. This specific embodiment has the advantage of permitting a simple and cost-effective manufacturing of graduated contours and a precise realization of the desired function of the two throttling sections.
- In one specific embodiment, the contours have the form of ascending and descending stairs that are associated with one another accordingly in order to form the two throttling sections.
- In another specific embodiment, a first contour has the form of a radial web, and the second contour the form of a radial recess. The web engages into the recess. As a function of the selected distances, both the radial as well as the axial distances between the contours maybe used to form the first and the second section of the throttling sections.
- Moreover, depending on the specific embodiment selected, the recess may be bounded by side walls of different heights, as viewed in a radial direction. Analogously, the web may be bounded by two side walls of different heights, as viewed in an axial direction.
- In another specific embodiment, the first portion of a throttling section is formed by a constriction that is disposed radially relative to an axis of rotation of the rotor and between the compressor impeller and the housing. The second portion of the throttling section is realized by an axial distance that, viewed in the axial direction, is disposed parallel to the axis of rotation of the rotor and between the rotor and the housing. The design of the throttling sections is thereby realized with the aid of a compact contour.
- Another specific embodiment provides that at least three or more throttling sections be successively configured in the sealing channel, as viewed in the flow direction. This reduces the leakage through the sealing gap.
- Tests have shown that a very low leakage is achieved at a low resistance to rotation and a high axial force by configuring the contours in the form of a recess and a web.
- Another specific embodiment provides that the web, which engages into the recess, feature a first portion that extends from the housing or the rotor and merges radially into a second portion. Viewed in a plane of an axis of rotation of the rotor, the first portion has a smaller width than the second portion.
- Another specific embodiment provides that the second portion of the web feature an annular first surface that is disposed radially at the end face and is associated with an annular second surface of the recess that is disposed radially at the end face. In particular, the first and second surface are oriented mutually in parallel. This further enhances the sealing.
- Depending on the specific embodiment selected, the rotor features a first compressor impeller on a first side and a second compressor impeller on a second, opposite side. In this specific embodiment, two compressor impellers may be used to realize a low-pressure stage and a high-pressure stage. The sealing channel is thereby configured between the high-pressure stage and the low-pressure stage. In this specific embodiment as well, the contours provided optimize the sealing channel.
- Depending on the specific embodiment selected, the compressor impeller may be supported contactlessly in the housing, the sealing channel being configured in the area of the bearing.
- In another specific embodiment, a sealing element is provided that constitutes at least one side of a throttling section, respectively one side of a first or second portion of a throttling section. The sealing element is made of a softer material than the housing or the compressor impeller. It is thus possible to improve the sealing.
- In another specific embodiment, the sealing element is formed on the housing; a radial recess being configured on the sealing element, and a radial web, which engages into the recess of the sealing element, being formed on the rotor. Thus, an enhanced sealing is provided.
- Depending on the specific embodiment selected, the compressor may be designed as a turbocompressor.
- The present invention is described in greater detail below with reference to the figures.
-
FIG. 1 shows a first specific embodiment of a compressor having a rotor including a compressor impeller on one side. -
FIG. 2 shows a second specific embodiment of a compressor having a rotor including two compressor impellers. -
FIG. 3 shows a specific embodiment of a rotor that is supported on a shaft. -
FIG. 4 shows a specific embodiment of a compressor; a sealing element being configured on the rotor. -
FIG. 5 shows a specific embodiment of a compressor; a sealing element being configured on the housing. -
FIG. 6 through 10 show various specific embodiments of contours between the housing and the rotor. -
FIG. 11 through 14 show various specific embodiments of contours in the form of a web and a recess for realizing the sealing channel. -
FIG. 15 shows another specific embodiment of a compressor. -
FIG. 16 shows another specific embodiment of a compressor. -
FIG. 17 shows an additional specific embodiment of a compressor. -
FIG. 18 shows an enlarged representation of the sealing channel of the specific embodiment ofFIG. 17 . -
FIG. 19 shows another specific embodiment of a compressor. -
FIG. 1 shows a schematic cross section through a part of acompressor 1 that has ahousing 2 and arotor 3.Rotor 3 is designed to be axially symmetric to an axis ofrotation 4. On a first side,rotor 3 has afirst compressor impeller 5 having rotor blades. Afirst compressor chamber 6 is configured betweenfirst compressor impeller 5 andhousing 2. In the illustrated exemplary embodiment,first compressor chamber 6 has an annularfirst intake duct 7. In response to rotation ofrotor 3 about axis ofrotation 4, a medium is drawn in viafirst intake duct 7, compressed byfirst compressor impeller 5, and output via afirst compression channel 8. A sealingchannel 11, which allowsfirst compressor chamber 6 to communicate with a zone having alower pressure 12, is configured between aradial exterior 9 ofrotor 3 and an associatedinterior 10 ofhousing 2. -
Rotor 3 may be rotationally mounted in the region of sealingchannel 11, for example, via a contactless bearing inhousing 2. Depending on the specific embodiment selected,rotor 3 may also be connected to a shaft (not shown) that is located in axis ofrotation 4 and is rotationally mounted onhousing 2. -
FIG. 2 shows a specific embodiment of acompressor 1 that is fabricated in accordance with the compressor ofFIG. 1 ; on a second side, however,rotor 3 having asecond compressor impeller 13 having second rotor blades. In addition, asecond compressor chamber 14 is configured betweensecond compressor impeller 13 andhousing 2. Furthermore,second compressor chamber 14 has asecond intake duct 15. In addition, asecond compression channel 16 is provided inhousing 2.Second compressor impeller 13 is designed to be axially symmetric to axis ofrotation 4.Second compressor chamber 14 communicates via sealingchannel 11 withfirst compressor chamber 6. In addition,second intake duct 15 may communicate withfirst compressor channel 8 via a line that is schematically indicated by an arrow. This makes it possible for two compressor stages to be realized in acompressor 1 with the aid of arotor 3.First compressor impeller 5 pre-compresses the medium; a second, higher compression of the pre-compressed medium, that is subsequently output viasecond compression channel 16, being achieved bysecond compressor impeller 13. - In a schematic representation,
FIG. 3 shows a specific embodiment of acompressor 1 in accordance withFIG. 2 having arotor 3 having twocompressor impellers rotor 3 is rotationally mounted onhousing 2 via ashaft 19. Analogously, the specific embodiment ofFIG. 1 may also include arotor 3 having only onefirst compressor impeller 5 that is mounted via a correspondingshaft 19 onhousing 2. - In a schematic representation,
FIG. 4 shows the variant of the compressor ofFIG. 2 ; anannular sealing element 17, which engages into anannular recess 18 ofhousing 2, being provided onrotor 3 in the area of sealingchannel 11. Sealingelement 17 is made of a different material thanrotor 3, for example. In particular, a softer material may be used to manufacture sealingelement 17 in order to enhance the desired sealing function. Sealingelement 17 may be made of a plastic material, for example. In the case of acompressor 1, sealingelement 17 may also be provided with arotor 3 having only onefirst compressor impeller 5 in accordance with the specific embodiment ofFIG. 1 . -
FIG. 5 shows another specific embodiment of the compressor ofFIG. 2 , anannular sealing element 17 being configured on aninner side 10 ofhousing 2. Sealingelement 17 engages into an annularsecond recess 18 ofouter side 9 ofrotor 3.Compressor 1 ofFIG. 1 having arotor 3 having only afirst compressor impeller 5 may likewise feature a sealingelement 17 and arecess 18 in accordance withFIG. 5 . -
FIG. 6 through 10 show various graduatedcontours inner side 10 ofhousing 2 and ofouter side 9 ofrotor 3 that are associated with one another. Depending on the specific embodiment selected, everycontour rotor 3 or byhousing 2. In addition, everycontour element 17 or have a sealingelement 17 that is joined tohousing 2, respectively torotor 3. -
FIG. 6 shows an enlarged, schematically illustrated detail view of sealingchannel 11 that is configured between a first and asecond contour FIG. 6 shows a cross section through a plane of axis ofrotation 4. Both the first and the second contour are designed to be axially symmetric relative to axis ofrotation 4. Axis ofrotation 4 may be located belowsecond contour 22, for example. In this specific embodiment,second contour 22 is constituted ofrotor 3 or of a sealing element thereof.First contour 21 is constituted of inner side ofhousing 2 or at least partially of a sealing element thereof. Depending on the specific embodiment selected, axis ofrotation 4 may also be located abovefirst contour 21. Accordingly,first contour 21 is constituted ofrotor 3 or at least partially of a sealing element thereof. Accordingly,second contour 22 is constituted of an inner side ofhousing 2 or at least partially of a sealing element ofhousing 2. These variants also hold for the followingFIG. 7 through 10 . - In cross section,
first contour 21 features anannular web 24 in aflow direction 23 from a higher-pressure zone toward a lower-pressure zone. The higher-pressure zone may be constituted offirst compressor chamber 6 in the case of arotor 3 having only onefirst compressor impeller 5 or ofsecond compressor chamber 14 in the case of arotor 3 having a first and asecond compressor impeller Web 24 has the same radial height on both sides.Second contour 22 has a radial recess in the form of agroove 28.Groove 28 is designed to be wider thanweb 24 in the axial direction, i.e., parallel to axis ofrotation 4. Moreover,web 24 projects radially intogroove 28. - In
flow direction 23, viewed axially,first contour 21 has a firstannular surface 31, a secondannular surface 32, and a thirdannular surface 33. First and thirdannular surface rotation 4. Secondannular surface 32bounds web 24; secondannular surface 32 having a greater or smaller distance to axis ofrotation 4 than first or thirdannular surface rotation 4. - In
flow direction 23, viewed axially,second contour 22 has another first, second and thirdannular surface annular surface rotation 4. Second furtherannular surface 42bounds groove 28; second further annularsurface 42 having a greater or smaller distance to axis ofrotation 4 than further first or thirdannular surface rotation 4. -
Web 24 has a first axialannular surface 35 and an opposite, second axialannular surface 36; relative to flowdirection 23, first, axialannular surface 35 being configured upstream from second, axialannular surface 36.Groove 28 is bounded by a first and a second axialannular surface direction 23, first, axialannular surface 45 is configured upstream from second, axialannular surface 46. -
Contours sections First section 51 extends inflow direction 23 to further first axialannular surface 45.Second section 52 extends axially from axialannular surface 45 to first axialannular surface 35.Third section 53 extends from first, axialannular surface 35 to second, axialannular surface 36.Fourth section 54 extends from second, axialannular surface 36 to further, second axialannular surface 46.Fifth section 55 extends from further, second axialannular surface 46 to the end of first andsecond contour - In first, third and
fifth sections channel 11. In second andfourth section axial distances - The radial distances between
contours fifth section contours fourth section contours axial distances contours fourth section radial distances contours fifth section contours axial distances fourth section contours - Axial and/or radial distances 71, 72, 73, 81, 82 may be within the range of between 10 and 500 μm or more. Moreover, the length of sealing
channel 11 may be within the range of between 1 and 15 mm or more. In addition, the sections inFIG. 6 may be partitioned to allowweb 24 to take up approximately one third of the length of the sealing channel, and the regions to the sides ofweb 24 each one third of sealingchannel 11. - Tests have shown that effective results are obtained at a ratio of
radial distance fifth section axial distance fourth section axial distance fourth section radial distance fifth section -
FIG. 7 shows another specific embodiment of sealingchannel 11; viewed inflow direction 23,first contour 21 having a stepped contour having a decreasing thickness, andsecond contour 22 having a stepped contour having an increasing thickness. First andsecond contour rotation 4. Inflow direction 23, viewed axially,first contour 21 has a firstannular surface 31, a secondannular surface 32, and a thirdannular surface 33. First radialannular surface 31 merges via a first axialannular surface 35 into second radialannular surface 32. Second radialannular surface 32 merges via a second axialannular surface 36 into third radialannular surface 33. In the selected variant, axis ofrotation 4 is located in the middle ofsecond contour 22.Annular surfaces rotation 4. Firstannular surface 31 features a smaller distance to axis ofrotation 4 than secondannular surface 32. Thirdannular surface 33 features a larger distance to axis ofrotation 4 than secondannular surface 32. If axis ofrotation 4 is located in the middle offirst contour 21, the radial distance between the annular surfaces and axis ofrotation 4 decreases by steps inflow direction 23. - In
flow direction 23, viewed axially,second contour 22 has another first, second and thirdannular surface annular surface 41 merges via a further first axialannular surface 45 into further second radialannular surface 42. Further second radialannular surface 42 merges via a further second axialannular surface 46 into further third radialannular surface 43. Further first, second and thirdannular surfaces rotation 4. If axis ofrotation 4 is located in the middle offirst contour 21, then the radial distance between the annular surfaces and axis ofrotation 4 decreases by steps inflow direction 23. - In the illustrated specific embodiment, first axial
annular surface 35 and further first radialannular surface 45 overlap radially in each particular case. Thus, an axial sealing gap having a firstaxial distance 81 is formed. Moreover, second, axialannular surface 36 and further, second radialannular surface 46 overlap radially. Thus, a second axial sealing gap having a secondaxial distance 82 is formed. -
Contours sections First section 51 extends inflow direction 23 to further first axialannular surface 45.Second section 52 extends axially from axialannular surface 45 to first axialannular surface 35.Third section 53 extends from first axialannular surface 35 to second axialannular surface 36.Fourth section 54 extends from second axialannular surface 36 to further, second axialannular surface 46.Fifth section 55 extends from further, second axialannular surface 46 to the end of first andsecond contours fifth sections fourth sections axial distances - Radial distances 71, 72, 73 between
contours fifth sections axial distances contours fourth sections contours axial distances contours fourth sections radial distances contours -
FIG. 8 shows a specific embodiment of acompressor 1 that essentially corresponds toFIG. 6 ; however,first contour 21 being formed onrotor 3 andsecond contour 22 onhousing 2. Axis ofrotation 4 is located in the middle ofsecond contour 22. -
FIG. 9 shows another specific embodiment of acompressor 1 that is disposed mirror-symmetrically to the specific embodiment ofFIG. 7 relative to flowdirection 23. -
FIG. 10 shows another specific embodiment that essentially corresponds to the specific embodiment ofFIG. 5 ; however, first and thirdannular surfaces rotation 4. Analogously, further firstannular surface 41 and further thirdannular surface 43 have different radial heights. In the illustrated specific embodiment, first axialannular surface 35 and further, first radialannular surface 45 overlap radially in each particular case. Thus, an axial sealing gap having a firstaxial distance 81 is formed. Moreover, second axialannular surface 36 and further second, radialannular surface 46 overlap radially. Thus, a second axial sealing gap having a secondaxial distance 82 is formed. Viewed radially, first axial sealing gap is longer than second axial sealing gap. Depending on the variant selected, the second axial sealing gap may also be configured to be longer.FIG. 11 through 14 show different specific embodiments ofFIG. 5 ; the specific embodiments differing in the height ofweb 24, respectively in the depth ofgroove 28. InFIG. 11 through 13 , radial distances 71, 72, 73 between first, second and thirdannular surface annular surface annular surface 35 and further, first radialannular surface 45 overlap axially. Thus, an axial sealing gap having a firstaxial distance 81 is formed. Moreover, second axialannular surface 36 and further, second radialannular surface 46 overlap radially. Thus, a second, axial sealing gap having a second,axial distance 82 is formed. - Viewed radially,
axial sealing gaps FIG. 11 than inFIG. 12 . Viewed radially, axial sealing gaps are longer relative to the axis ofrotation 4 inFIG. 12 than inFIG. 13 ; viewed radially, the sealing gaps inFIG. 13 being longer than inFIG. 11 . - In
FIG. 14 , radial distances 71, 72, 73 between first, second and thirdannular surfaces annular surfaces FIG. 11 through 13 . Axial distances 81, 82 between the side walls ofgroove 28 and the side walls ofweb 24 may vary within the range of between 50 and 250 μm, for example. Radial distances 71, 72, 73 may vary within the range of between 10 and 100 μm, for example. - As a function of the selected specific embodiment, in
FIG. 11 through 14 ,first contour 21 may be configured on the housing andsecond contour 22 on the rotor, orfirst contour 21 on the rotor andsecond contour 22 on the housing. - Moreover, depending on the specific embodiment selected, at least one portion of first or
second contour particular web 24 may be configured in the form of a sealingelement 17. Moreover, entire first and/orsecond contour element 17. - In a schematic part sectional view,
FIG. 15 shows a portion of acompressor 1;housing 2 having a sealingelement 17 that extends betweencompressor impellers element 17 has acircumferentially extending groove 28 and thus the form ofsecond contour 22. Configured onrotor 3 isfirst contour 21 havingweb 24 that extends intogroove 28 ofsecond contour 22. Formed in this specific embodiment are furtheraxial distances compressor impellers element 17 within the range of between 50 and 250 μm, for example. Furthermore, radial distances 71, 72, 73 between first andsecond contour fifth section axial distances second contour fourth section - Moreover, viewed radially, the depth of
groove 28 may be within the range of between 0.5 and 3 mm or more. Accordingly, the length ofweb 24 is adapted for attaining desired,second radial distance 72 inthird section 53. Depending on the specific embodiment selected,first contour 21 may likewise be configured in the form of a sealing element or at least of a different material than the rotor andcompressor impellers first contour 21 may be fabricated of a separate component that is secured torotor 3. -
FIG. 16 shows another specific embodiment that essentially corresponds to the specific embodiment ofFIG. 15 ; however, the depth of the recess being smaller on the inner side of sealingelement 17. The axial and radial distances are retained. In particular, the depth of the recess may be within the range of 1 mm. Moreover,first contour 21 may be machined from the material ofrotor 3, as shown in the illustrated example. - In a schematic representation,
FIG. 17 shows a portion of acompressor 1 having a design similar to that ofFIG. 15 ; however,first contour 21 being formed onhousing 2 andsecond contour 22 onrotor 3. Moreover,first contour 21 has the distinctive feature thatweb 24 has afirst web portion 61 that merges radially inwardly toward axis ofrotation 4 into asecond web portion 62. In the axial direction, the diameter offirst web portion 61 is smaller than that ofsecond web portion 62. Viewed in the axial direction of axis ofrotation 4, the diameter offirst web portion 61 may be half of that ofsecond web portion 62, for example. Moreover, viewed in the axial direction of the axis of rotation,second web portion 62 has a smaller width than sealingelement 17 that projects into the clearance space betweencompressor impellers flow direction 23, sealingelement 17 may have anannular recess 63 infifth section 55 that provides for a one-sided flattening of sealingelement 17. In place of sealingelement 17,housing 2 may also featurefirst contour 21. Moreover,second contour 22 may also be at least partially realized by a sealingelement 17. - In a schematic representation,
FIG. 18 shows an enlarged representation ofFIG. 17 ; infirst section 51, there being a firstsmall radial distance 71 between first andsecond contour second section 52 which is additionally enlarged by the thinner formation offirst web portion 61. Inthird section 53, there is again a small, radialsecond distance 72 betweencontours first web portion 61 infourth section 54. Infifth section 55, the overlapping of the first and second contour is shortened axially in comparison tofirst section 51. This is accomplished, for example, in that sealingelement 17 in this area has anannular recess 63 in the form of a chamfer. Thus, in asixth section 56, a relatively large space for expanding the medium is provided in the area ofchamfer 63. In spite of the small installation space, this specific embodiment achieves more space for expanding the medium downstream of the radial sealing gaps realized byradial distances - The radial gap seals used are insensitive to axial deformations or forces. The specific embodiment of
FIGS. 17 and 18 provides a substantial acceleration three times throughsections sections first section 51; a deceleration being achieved insecond section 52. The leakage medium is accelerated, in turn, inthird section 53, and is again decelerated infourth section 54. Correspondingly, an acceleration takes place infifth section 55, and, again, a deceleration insixth section 56. -
FIG. 19 shows another specific embodiment of acompressor 1 that essentially corresponds to the specific embodiment ofFIG. 17 ; in contrast toFIG. 17 , however, the compressor only having afirst compressor impeller 5. - The shapes illustrated in the figures for the surfaces that bound sealing
channel 11 are shown as contours that have an angular cross section. The angular contours may also be formed as rounded contours. In particular, convex and/or concave contours may, therefore, oppose one another to form sealingchannel 11. In particular,groove 28 and/orweb 24 may have rounded edges in cross section, so that a concave and a convex shape oppose one another in order to form sealingchannel 11. In addition,recess 18 and/or sealingelement 17 may have rounded edges in cross section, so that a concave and a convex shape oppose one another in order to form sealingchannel 11. Similarly, the stepped structures ofFIGS. 7 and 8 may likewise have rounded corners in cross section. Here as well then, concave and convex surfaces, which bound sealingchannel 11, oppose one another. - Moreover, the surfaces in the figures that bound sealing
channel 11 in the radial direction and are illustrated parallel to axis ofrotation 4, i.e., first and/or second and/or thirdannular surface rotation 4. In particular, first and/or second and/or thirdannular surface rotation 4 at different angles. Moreover, further first and/or further second and/or further thirdannular surface rotation 4. In particular, further first and/or further second and/or further thirdannular surface rotation 4. - Furthermore, the surfaces of the figures that bound sealing
channel 11 in the axial direction and are shown in the figures orthogonally to the axis of rotation, may also be configured to not be orthogonal to axis ofrotation 4. For example, the surfaces may be oriented at different angles to axis ofrotation 4. In particular, first and/or second axialannular surface rotation 4. Further first and/or further second axialannular surface rotation 4.
Claims (15)
1-14. (canceled)
15. A compressor, comprising:
a housing;
a rotor having a compressor impeller at least on one side, the rotor being rotationally mounted;
a compressor chamber configured between the compressor impeller and the housing; and
an annular sealing channel configured between the rotor and the housing, the sealing channel being routed from the compressor chamber to a lower-pressure zone, at least two throttling sections being provided in the sealing channel, in each of the two throttling sections, in the direction of flow viewed from the compressor chamber to the lower-pressure zone, a first section having a reduction in the cross section of the sealing channel being first provided, and a second section having an enlarged cross section of the sealing channel being subsequently provided.
16. The compressor as recited in claim 15 , wherein two contours are provided between the rotor and the housing in the sealing channel, wherein, viewed in a plane of an axis of rotation of the rotor, the contours having steps, the steps of the contours being formed in such a way that the two throttling sections are realized by the steps of the contours.
17. The compressor as recited in claim 16 , wherein the contours are in the form of ascending and descending stairs.
18. The compressor as recited in claim 16 , wherein the contours are in the form of at least a radial web and at least a radial recess, the web engaging into the recess.
19. The compressor as recited in claim 18 , wherein the recess is bounded by side walls of different heights, as viewed axially, and wherein the web has side walls of different heights, as viewed radially.
20. The compressor as recited in claim 15 , wherein the first portion of the throttling section is formed by a constriction that is disposed radially relative to an axis of rotation of the rotor and between the rotor and the housing, and the second portion of the throttling section is realized by an axial distance that, viewed in the axial direction, is disposed parallel to the axis of rotation of the rotor and between the rotor and the housing.
21. The compressor as recited in claim 15 , wherein at least three or more throttling sections are provided in the sealing channel, as viewed in the flow direction.
22. The compressor as recited in claim 18 , wherein the web, extending from the housing or the rotor, has a first section that merges into a second section, wherein viewed in a plane of an axis of rotation of the rotor, the first section has a smaller width than the second section.
23. The compressor as recited in claim 22 , wherein the second section has an annular first surface that is disposed radially at the end face and that is associated with an annular second surface, which is disposed radially at the end face, of a recess in the form of a radial groove, wherein the first and second surface are oriented mutually in parallel.
24. The compressor as recited in claim 15 , wherein the compressor impeller is configured on a first side of the rotor, a further compressor impeller is configured on a second side of the rotor opposite the first side, the further compressor impeller constituting a high pressure stage, and the compressor impeller constituting a low-pressure stage, the further compressor impeller being positioned in a further compressor chamber of the housing, and the sealing channel being formed between the compressor chamber and the further compressor chamber thereof.
25. The compressor as recited in claim 15 , wherein the rotor is rotationally mounted on the housing via a contactless bearing, and the sealing channel is configured in the area of the bearing.
26. The compressor as recited in claim 15 , wherein a sealing element is configured on at least one of the rotor and the housing, the sealing element being formed of a softer material than the rotor or the housing, and the sealing element constitutes at least one side of at least one throttling section.
27. The compressor as recited in claim 26 , wherein the sealing element is configured on the housing, a radial recess is configured in the sealing element, and a radial web, which engages into the recess, is formed on the rotor.
28. The compressor as recited in claim 15 , wherein the compressor is a turbocompressor.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
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DE102014224283.5 | 2014-11-27 | ||
DE102014224283.5A DE102014224283A1 (en) | 2014-11-27 | 2014-11-27 | Compressor with a sealing channel |
PCT/EP2015/072258 WO2016082979A1 (en) | 2014-11-27 | 2015-09-28 | Compressor with a sealing duct |
Publications (1)
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US20170321713A1 true US20170321713A1 (en) | 2017-11-09 |
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US15/523,838 Abandoned US20170321713A1 (en) | 2014-11-27 | 2015-09-28 | Compressor having a sealing channel |
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EP (1) | EP3224479A1 (en) |
KR (1) | KR20170089857A (en) |
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US20170175754A1 (en) * | 2015-12-21 | 2017-06-22 | General Electric Company | Apparatus for pressurizing a fluid within a turbomachine and method of operating the same |
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DE102017220623A1 (en) | 2017-11-17 | 2019-05-23 | Robert Bosch Gmbh | Side channel compressor for a fuel cell system for conveying and / or sealing a gaseous medium |
KR102474772B1 (en) * | 2018-01-11 | 2022-12-05 | 한화파워시스템 주식회사 | Compressor |
CN110985373B (en) * | 2019-11-22 | 2022-04-19 | 中国航发西安动力控制科技有限公司 | Servo labyrinth seal structure |
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
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US20170175754A1 (en) * | 2015-12-21 | 2017-06-22 | General Electric Company | Apparatus for pressurizing a fluid within a turbomachine and method of operating the same |
US10718346B2 (en) * | 2015-12-21 | 2020-07-21 | General Electric Company | Apparatus for pressurizing a fluid within a turbomachine and method of operating the same |
Also Published As
Publication number | Publication date |
---|---|
DE102014224283A1 (en) | 2016-06-02 |
WO2016082979A1 (en) | 2016-06-02 |
CN107002694A (en) | 2017-08-01 |
EP3224479A1 (en) | 2017-10-04 |
KR20170089857A (en) | 2017-08-04 |
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