EP3577347A1 - Rückführstömungskanäle für einen mehrstufigen turboverdichter - Google Patents
Rückführstömungskanäle für einen mehrstufigen turboverdichterInfo
- Publication number
- EP3577347A1 EP3577347A1 EP18729651.2A EP18729651A EP3577347A1 EP 3577347 A1 EP3577347 A1 EP 3577347A1 EP 18729651 A EP18729651 A EP 18729651A EP 3577347 A1 EP3577347 A1 EP 3577347A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- flow
- flow channels
- compressor stage
- geometry according
- compressor
- Prior art date
- 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.)
- Granted
Links
- 230000002093 peripheral effect Effects 0.000 claims description 4
- 230000007704 transition Effects 0.000 claims description 3
- 238000011161 development Methods 0.000 description 5
- 230000018109 developmental process Effects 0.000 description 5
- 239000012530 fluid Substances 0.000 description 4
- 238000000926 separation method Methods 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000001934 delay Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
-
- 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
- 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
- F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
-
- 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
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers 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
- F04D29/30—Vanes
Definitions
- the invention relates to a return geometry of a turbocompressor for optimized flow connection of a first and second compressor stage of the turbocompressor.
- the invention is therefore based on the object of providing a return geometry for a turbocompressor, which reduces the risk of flow separation and minimizes the pressure loss.
- a return geometry of a turbocompressor is proposed, which is designed for the flow connection of a first and second compressor stage of the turbocompressor.
- the return geometry has a plurality of circumferentially evenly distributed, at least partially extending in the circumferential direction part spirals, at least partially separate flow channels form the flow connection of the first and second compressor stage.
- return geometry the word component "- geometry” is included, determined by but the resulting flow line through the formation of the flow channels.
- the plurality of flow channels reduces the flow cross-section of each individual flow channel and provides a more uniform inflow into the second compressor stage.
- the maximum extension width, in particular in the radial direction, of each individual channel relative to a single rotationally symmetrical return channel can be increased without large flow separations or backflows occurring at operating points with a low mass flow.
- the flow channels form a plurality of successively arranged manifolds, which deflect the flow between the first and second compressor stage several times. In this way, it is possible to realize from the radial outflow direction of the compressor impeller of the turbo compressor in the first compressor stage an optimal axial flow of the compressor impeller of the second compressor stage.
- Inlet direction which runs counter to the outflow direction
- lead Even more advantageous is the design in which the last seen in the flow direction of the manifold flow channels then directs the flow to the inflow in a second axial direction, which runs counter to the first axial direction.
- the second axial direction corresponds to the suction direction of the compressor impeller of the second compressor stage, so that a predefined inflow through the flow channels exactly to the intake the compressor impeller of the second compressor stage can take place.
- the manifolds each generate a substantially 90 ° deflection.
- the compressor impeller of the second compressor stage may be arranged in the same direction as the compressor impeller of the previous compressor stage, i. the direction of entry is the same for both compressor wheels.
- both compressor wheels may also be arranged in opposite directions, i. in so-called.
- Back to back arrangement which makes sense mainly in two-stage turbocompressors, which formed for example as a spiral Ausströmgeometrie the second compressor stage and the adjoining outlet pipe can be passed through the area between the individual partial spirals of scaffoldfashionometrie.
- the invention is not limited to two-stage turbocompressors, but also applicable to multi-stage designs.
- the flow channels of the partial spirals extend from an inlet region of the first compressor stage, in particular from the outlet region of the impeller of the first compressor stage, to an outlet region of the first compressor stage, in particular to the inlet region of the impeller of the second compressor stage, and extend in the Combine the outlet area to form a circumferentially symmetric total channel.
- the total channel then forms the inflow for or into the second compressor stage.
- an embodiment of the return geometry is characterized in that the individual flow channels in a transition to the overall channel in each case curved walls and / or curved swirl struts respectively.
- the swirl struts are designed to impart a predefined swirl to the flow upon entry into the overall channel, which effectively favors the intake by the compressor wheel of the second compressor stage.
- the return geometry is formed in one embodiment such that the manifold respectively formed in the flow channels, which deflects the flow from the radial outflow in the first axial direction in the direction of the second compressor stage, each having a guide strut, which along of the respective flow channel extends in the radial direction outwards and in the first axial direction.
- the guide struts divide the respective flow channel in an advantageous embodiment in the middle, so that both remaining parts of the respective flow channel are flowed through by an equal mass flow. It is also provided in a development that the guide struts extend radially outside a tongue radius of the return geometry, i. relative to a formed by the tongue radius inlet of the respective flow channel radially outwardly spaced.
- an embodiment of the return geometry is also advantageous, in which the flow channels have an axial section, in which the flow is directed in the first axial direction in the direction of the second compressor stage, and the axial section of the flow channels is designed as a diffuser.
- the formation of the respective axial section as a diffuser delays the flow, reduces friction losses and builds up a static pressure.
- the axial section of the return geometry advantageously runs parallel to an axis of rotation of the turbocompressor.
- an embodiment of the return geometry is favorable, in which the flow channels can be assigned to one of the first compressor stage Inflow radial section and one of the second compressor stage have assignable Ausströmradialab Songs, which direct the flow respectively in the inflow direction and in the outflow direction before the flow fluid preferably flows axially from the scaffoldlabgeometrie.
- the embodiment is advantageous, in which the flow channels in the outflow radial section widen in the flow direction with respect to their cross section, so that an acceleration of the flow in the outflow radial section is reduced or even avoided.
- the flow channels of the partial spirals of the return geometry are formed in a compact design by an intermediate disc housing of the turbocompressor, which separates the first compressor stage from the second compressor stage.
- the flow channels may extend in the outer peripheral surface of the washer housing.
- the flow channels of the partial spirals are formed by the intermediate disc housing and the turbo compressor housing, wherein the flow channels are formed by a channel clearance between an outer surface of the intermediate disc housing and an inner wall surface of the turbo compressor housing.
- the flow channels extend in the outer peripheral surface of the intermediate disc housing and are covered by the turbo compressor housing.
- the turbocompressor housing and the intermediate disc housing can also be designed in several parts.
- the washer housing an axial opening for receiving the
- Compressor impeller of the first compressor stage having a Axialö Stammsradius R1 and the flow channels of the sub-spirals 1969cken starting from the tongue radius R2 of the washer housing.
- the tongue radius is set by the factor 1, 4 - 1, 8 is greater than the Axialö Samuelsradius R1. Further enlargement would increase the risk of ner to avoid flow separation.
- the outflow direction of the compressor impeller of the first compressor stage and the inflow direction into the flow channels can thus with respect to the outflow angle and
- Inflow angle are matched.
- the ratio of the extent (a1) of the flow channels of the sub-spirals in the circumferential direction opposite adjacent peripheral portions (a2) is formed without flow channels, so that 0.2 ⁇ a1 / (a1 + a2) ⁇ 0.5.
- the invention further comprises a radial compressor with a recirculation geometry according to one of the above described embodiments.
- Fig. 1 is a schematic view of a turbocompressor
- Fig. 2 is an exploded view of the parts of the turbocompressor
- FIG. 3 shows a plan view of an intermediate disk housing from FIG. 2 with partial spirals which form the flow channels;
- FIG. 4 shows an inlet-side plan view of a schematically illustrated flow geometry resulting from a flow profile;
- FIG. 5 is a side sectional view of the flow geometry of FIG.
- Fig. 6 is a rear plan view of the flow geometry of Fig. 4;
- FIG. 7 is a side view of the flow geometry of FIG .. 4
- FIG. 1 schematically shows a turbocompressor 1 with a turbocompressor housing 3 and an intermediate disk housing 2 accommodated therein.
- a compressor impeller 6 of the first compressor stage is arranged on the flow inlet 4, partially inserted into an axial opening, which axially draws in a flow fluid and discharges radially in the direction of the second compressor stage.
- the compressor impeller 7 of the second compressor stage arranged, which also axially draws the flow fluid and radially in the direction of the outlet 11 of the intermediate disc housing 2 and finally the outlet 12 at the turbo compressor housing 3 blows.
- the turbocompressor housing 3 and the intermediate disc housing 2 provide a return geometry for the flow connection of the first and second compressor stage with a plurality of circumferentially uniformly distributed arranged part spirals, the separately extending Strö- form mungskanäle 5 for producing the flow connection from the inlet region of the first compressor stage to the outlet region of the second compressor stage, as can be seen in the exploded view according to Figures 2 and 3.
- the flow channels 5 are each generated by a channel clearance between the outer surface of the intermediate disc housing 2 and the inner wall surface of the turbo compressor housing 3.
- the geometry of the respective flow channels 5 can be determined by both components or, for example, only by the intermediate disc housing 2, as shown in the case.
- the return geometry for the flow connection of the first and second compressor stages is produced by seven partial spirals, each with identical flow channels 5, which extend radially inwardly from the flow inlet 4 and at the same time in the circumferential direction.
- the flow is deflected several times by means provided in the flow channels 5 manifold 15, 16, through the first manifold 15 from a substantially radial outflow direction in a first axial direction in the direction of the second compressor stage and then through the second manifold 16 back into the radial Inflow direction, which runs counter to the outflow direction.
- the third manifold of the flow channels 5 lies within the intermediate disk housing 2 and therefore can not be seen, but then directs the flow to the inflow direction in a second axial direction, which runs counter to the first axial direction.
- a guide strut 8 is provided, which extends in the radial and axial direction over the first manifold 15 away and divides the flow fluid in the respective flow channel 5 during the first deflection center.
- FIGS. 4-7 The geometric design of the flow connection of the return geo In FIGS. 4-7, the geometry of the resulting geometry is shown, that is, in FIGS. 4-7, there are no components, but the geometric shape of the free-flow return geometry resulting from the construction of the turbocompressor housing 3 and, in particular, the intermediate housing 2 shown resulting flow from the first to the second compressor stage. Therefore, the flow representing the shape of the flow channels 5 is marked 5 'in FIGS. 4-7.
- the geometric shape of the intermediate disk housing 2 is designed such that the flow channels 5 extend from the inlet region to the flow inlet 4 of the first compressor stage to the outlet region of the first compressor stage and in the outlet region to a circumferentially symmetrical total channel 9 with a radius R9 and a flow-through Zentraiabites extend the axis of rotation with a radius R10.
- the ratio a1 / (a1 + 2) is set in a range of 0.2-0.5.
- all the flow channels 5 have the same size and the same flow cross-section, but these can also be deviating from one another, so that, for example, the lengths a1 of each flow channel or of some flow channels 5 varies, so that gletting would occur
- the individual flow channels 5 each have curved swirl struts in the transition to the overall channel 9, which impart a swirl to the flow upon entry into the overall channel 9, so that the flow at the outlet into the second compressor stage has a predefined swirl.
- Swirl struts are designated as negative in the flow shown in Fig. 7 by the reference numeral 22 'and have an opening angle a5.
- the flow channels 5 are formed in their axial section z, in which the flow is conducted in the first axial direction in the direction of the second compressor stage, as a diffuser and have a diffuser angle a4, the condition [R5 (z) 2 -R4 (z) 2 ] (a1 - ⁇ - ⁇ ) / 360 ⁇ 2n-R2 b2 is satisfied.
- R5 is the outer radius as a function of the axial coordinate z
- R4 the radius of the inner wall of the flow channel 5 as a function of the axial coordinate z
- R2 the tongue radius or exit radius of the return geometry
- b2 the flow channel width in Ausströmradialabites.
- the diffusion ratio R2 / R1 is set in a range of 1, 4-1, 8.
- the sub-spirals of the flow channels 5 follow with a tongue angle a3 between 60 ° and 80 ° with the tongue radius R11 and a smallest through-flowed surface 27.
- the mounted to improve the deflection guide 8 starts at R3> R2, so that the smallest area flowed through in the respective flow channel 5 is not narrowed further.
- the diffuser angle is formed in the section z2 of the axial section z, which determines a part of the straight axial extension z1.
- Outflow direction portion is smaller than the flow channel widths b6 and b7 in the opposite radial inflow direction portion.
- b6-R6-a1 / 360-n b7-R7.
- b6 is the flow channel width adjacent to the second bend 16 at the radius R6 and b7 the flow channel width immediately before the third bend at the radius R7, according to FIG. 6.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102017114232.0A DE102017114232A1 (de) | 2017-06-27 | 2017-06-27 | Rückführgeometrie eines Turboverdichters |
PCT/EP2018/064772 WO2019001910A1 (de) | 2017-06-27 | 2018-06-05 | Rückführstömungskanäle für einen mehrstufigen turboverdichter |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3577347A1 true EP3577347A1 (de) | 2019-12-11 |
EP3577347B1 EP3577347B1 (de) | 2022-04-27 |
Family
ID=62323080
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18729651.2A Active EP3577347B1 (de) | 2017-06-27 | 2018-06-05 | Turboverdichter mit rückführstömungskanälen |
Country Status (5)
Country | Link |
---|---|
US (1) | US11519424B2 (de) |
EP (1) | EP3577347B1 (de) |
CN (1) | CN207406386U (de) |
DE (1) | DE102017114232A1 (de) |
WO (1) | WO2019001910A1 (de) |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US984189A (en) * | 1908-06-27 | 1911-02-14 | William C Brown | Centrifugal and turbine pump and the like. |
US2748713A (en) * | 1952-03-21 | 1956-06-05 | Buchi Alfred | Multi-stage centrifugal pump or blower |
US2900126A (en) * | 1953-08-29 | 1959-08-18 | Austin Motor Co Ltd | Centrifugal compressors |
CH331941A (de) * | 1955-01-27 | 1958-08-15 | Buechi Alfred J Dipl Ing | Verfahren zur Herstellung eines Satzes von Zentrifugalfördermaschinen und nach diesem Verfahren hergestellter Maschinensatz |
GB854127A (en) * | 1957-06-28 | 1960-11-16 | Power Jets Res & Dev Ltd | Improvements in or relating to radial-flow compressors and turbines |
US3171353A (en) * | 1962-02-27 | 1965-03-02 | Kenton D Mcmahan | Centrifugal fluid pump |
US4531356A (en) * | 1981-06-15 | 1985-07-30 | The Garrett Corporation | Intake vortex whistle silencing apparatus and methods |
US6062028A (en) * | 1998-07-02 | 2000-05-16 | Allied Signal Inc. | Low speed high pressure ratio turbocharger |
US6540481B2 (en) * | 2001-04-04 | 2003-04-01 | General Electric Company | Diffuser for a centrifugal compressor |
EP1405708A4 (de) | 2001-07-03 | 2007-09-05 | Top Kk | Verfahren zur herstellung eines aussenrohrs eines injektors |
US20070036662A1 (en) * | 2005-08-05 | 2007-02-15 | C.R.F Societa Consortilla Per Azioni | Multistage motor-compressor for the compression of a fluid |
US8181462B2 (en) * | 2009-06-23 | 2012-05-22 | Honeywell International Inc. | Turbocharger with two-stage compressor, including a twin-wheel parallel-flow first stage |
JP5611307B2 (ja) | 2012-11-06 | 2014-10-22 | 三菱重工業株式会社 | 遠心回転機械のインペラ、遠心回転機械 |
JP6133748B2 (ja) | 2013-10-09 | 2017-05-24 | 三菱重工業株式会社 | インペラ及びこれを備える回転機械 |
AT516978B1 (de) * | 2015-03-26 | 2018-04-15 | Avl List Gmbh | Mehrstufiger abgasturbolader |
-
2017
- 2017-06-27 DE DE102017114232.0A patent/DE102017114232A1/de not_active Withdrawn
- 2017-08-25 CN CN201721072459.8U patent/CN207406386U/zh active Active
-
2018
- 2018-06-05 EP EP18729651.2A patent/EP3577347B1/de active Active
- 2018-06-05 WO PCT/EP2018/064772 patent/WO2019001910A1/de unknown
-
2019
- 2019-11-15 US US16/685,147 patent/US11519424B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
CN207406386U (zh) | 2018-05-25 |
US20200080569A1 (en) | 2020-03-12 |
EP3577347B1 (de) | 2022-04-27 |
DE102017114232A1 (de) | 2018-12-27 |
US11519424B2 (en) | 2022-12-06 |
WO2019001910A1 (de) | 2019-01-03 |
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