EP4015832A1 - Guidage d'écoulement statique, turbomachine radiale - Google Patents

Guidage d'écoulement statique, turbomachine radiale Download PDF

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Publication number
EP4015832A1
EP4015832A1 EP20215303.7A EP20215303A EP4015832A1 EP 4015832 A1 EP4015832 A1 EP 4015832A1 EP 20215303 A EP20215303 A EP 20215303A EP 4015832 A1 EP4015832 A1 EP 4015832A1
Authority
EP
European Patent Office
Prior art keywords
sfg
flow guide
radial
flow
guide
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.)
Withdrawn
Application number
EP20215303.7A
Other languages
German (de)
English (en)
Inventor
Werner Jonen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens Energy Global GmbH and Co KG
Original Assignee
Siemens Energy Global GmbH and Co KG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens Energy Global GmbH and Co KG filed Critical Siemens Energy Global GmbH and Co KG
Priority to EP20215303.7A priority Critical patent/EP4015832A1/fr
Publication of EP4015832A1 publication Critical patent/EP4015832A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/42Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44Fluid-guiding means, e.g. diffusers
    • F04D29/441Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444Bladed diffusers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08Centrifugal pumps
    • F04D17/10Centrifugal pumps for compressing or evacuating
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00Geometry
    • F05D2250/50Inlet or outlet
    • F05D2250/52Outlet

Definitions

  • the invention relates to an annular static flow guide that extends about an axis along a circumferential direction, in particular for a radial turbomachine, the flow guide guiding a process fluid with an average first main flow velocity defined by a first axial velocity component, a first radial velocity component and a first peripheral velocity component of the process fluid diverts to a second mean main flow velocity defined by a second axial velocity component, a second radial velocity component, and a second peripheral velocity component, providing significant diversion of the process fluid in the flow guide.
  • Centrifugal turbomachines are known as either centrifugal turbocompressors or centrifugal turboexpanders. Unless otherwise stated, the following explanations refer to the compressor version.
  • the invention is for expanders basically just as applicable as for compressors, with a radial turboexpander compared to a radial turbocompressor essentially provides a reverse flow direction of the process fluid.
  • the global market environment demands turbo machines with low investment costs. To reduce costs, it is particularly effective to make the machines more compact. It is particularly important to reduce the required radial space. This measure is usually accompanied by a deterioration in efficiency.
  • the invention has set itself the task of improving the compactness of deflecting flow guides, in particular of return stages, without impairing the aerodynamics disproportionately.
  • the invention proposes a flow guide of the type mentioned at the beginning with the additional features according to claim 1 .
  • the dependent claims contain advantageous developments of the invention.
  • this axis is also the axis of rotation of a rotor or the shaft with the impellers.
  • the flow guide deflects the process fluid in an arc, so that when referring to the deflection, the term "radial” does not refer to the central axis, but to the bend or curvature of the deflection itself.
  • a radial segment means a radial section which is formed separately from at least one other radial section of the flow guide at least along a section of flow through the flow guide by means of a partition or partition.
  • a process fluid to be conducted is generally the flow fluid that is conveyed by the corresponding turbomachine or radial turbomachine or that essentially serves as a drive or output for the operation of the turbomachine.
  • the process fluid to be conducted is the medium that mainly either gives off or absorbs significant technical work.
  • the invention understands the term “in operation” to mean the state of operation of the corresponding machine or turbomachine, during which, for example, the rotor of the machine rotates and technical work is transferred to the flow fluid or away from the flow fluid.
  • the invention does not necessarily understand a parallel flow to mean the geometrically parallel flow of a flow fluid through the various flow channels, but preferably the division of the flow fluid into a plurality of partial flows which flow through the respective flow channels of the flow guide according to the invention next to one another, generally having a common one before the division Formed main flow and are preferably reunited downstream to form a common main flow after the flow control according to the invention.
  • the deflecting flow guide is divided radially into at least two radial segments with regard to the deflection, so that the process fluid is divided into parallel partial flows when it flows through the flow guide.
  • the terms "radial”, “radial segment” relate here to the curvature of the flow guide, due to which the process fluid is deflected by means of the flow guide.
  • the flow guide here describes a curved arc, in the middle course of which a radius can always be defined, which is decisive for the segmentation of the flow guide into radial segments.
  • the flow guidance according to the invention allows the process fluid to flow as desired to carry out deflection without serious flow separations occurring.
  • the radial segmentation prevents the process fluid from flowing radially through the flow guide, so that the deflection is guided better. Accordingly, it is aerodynamically possible to deflect the process fluid "more sharply", so that with improved compactness there is no significantly poorer efficiency.
  • the flow guidance according to the invention enables aerodynamic configurations without violating recognized stress criteria, such as deceleration ratios.
  • An advantageous development of the invention provides that the spatial deflection takes place in the circumferential direction, so that the deflection by a deflection angle of at least 50° essentially changes a circumferential component of the mean flow rate of the process fluid.
  • Another advantageous development of the invention provides that the spatial deflection takes place from radial to axial, so that the deflection by a deflection angle of at least 50° essentially changes a radial component of the mean flow velocity of the process fluid.
  • the radial segments are arranged concentrically to one another, at least in sections. Accordingly, the process fluid in the individual parallel flows through the radial segments undergoes approximately the same deflection in each case, so that the flow pattern is made more uniform downstream of the flow guide according to the invention.
  • the flow guide according to the invention can be designed particularly expediently with guide vanes in the radial segments. In this way, the process fluid is additionally guided and there is even less separation of the flow. In addition, an additional corrective guidance of the flow of the process fluid so that a further flow effect can be achieved - for example the reduction of a swirl component of the flow of the process fluid.
  • the individual radial segments have different numbers of guide vanes from one another.
  • Such an aerodynamic individualization of the radial segments makes sense for better homogenization downstream of the flow guidance as a result of the different space available between the individual radial segments.
  • a configuration of the guide vanes at least partially as splitter blades and/or as rib vanes is particularly effective. In this way, the flow is guided only where it is necessary and elsewhere this flow guidance is omitted, so that flow losses are reduced.
  • a particularly advantageous application of the invention provides that the flow guide is designed as a return stage of a radial compressor.
  • This expedient design of the flow guide provides a substantially axial inflow and a substantially axial outflow.
  • the latter variant can advantageously be provided between two so-called Ax-2-Ax impellers. These impellers have an axial inflow and an axial outflow, with the process fluid being conveyed from radially inwards to further radially outwards in the case of a compressor impeller.
  • the latter variant of a static flow guide according to the invention receives the process fluid flowing axially from the Ax-2-Ax impeller and conveys it back radially further inwards, where it is particularly preferably fed axially to the next impeller stage.
  • the flow guide is designed as a diffuser for arrangement between an impeller and a junction with radial inflow and essentially axial outflow is.
  • the axial outflow takes place in a junction, with the impeller radially feeding the process fluid into the flow guide upstream of the flow guide.
  • This arrangement is preferred for use in a geared compressor stage.
  • a mean inlet diameter D2 and a maximum outside diameter D are defined by the flow guide, where the following applies: 1 , 3 ⁇ D / D 2 ⁇ 1 , 5.
  • figure 1 shows a schematic longitudinal section through a flow guide SFG according to the invention, which radially receives a process fluid PFL from the outflow of an impeller IMP of a radial turbomachine RTM, which is designed as a radial compressor CMP, and deflects it in an axial direction in order to flow it axially into a downstream junction COL to let.
  • the flow guide SFG is ring-shaped and part of a stator STT of the radial turbomachine, which is preferably designed as a radial compressor CMP RTM, the annular shape extending around an axis X, which is also the axis of rotation RTX of the impeller IMP.
  • the impeller IMP is in this case designed as an open impeller IMP without a cover disk.
  • the impeller IMP is also designed without a shroud, with the blades BLD being connected directly to a hollow shaft SFT.
  • the process fluid PFL flows through the arrangement along a main flow direction, which is identified in the drawings as an arrow at different locations of the flow.
  • the flow guide SFG is designed in such a way that during operation it guides the process fluid PFL at an average first main flow velocity MV1, the first main flow velocity MV1 being defined by a first axial velocity component AV1, a first radial velocity component RV1 and a first peripheral velocity component CV1 (the relationships between MV1, RV1, AV1, RV1 are simplified only in figure 2 shown).
  • the flow guide SFG deflects the process fluid PFL into a second average main flow velocity MV2.
  • the second mean main flow velocity is defined by a second axial velocity component AV2, a second radial velocity component RV2 and a second peripheral velocity component CV2 (the relationships between MV2, RV2, AV2, CV2 are simplified only in figure 2 shown).
  • the deflecting flow guide SFG is divided radially into at least two annular channels RSG by means of radial guides RGE, so that the process fluid PFL is divided into parallel partial flows PPF when it flows through the flow guide SFG, so that the spatially deflecting flow guide SFG is designed in such a way that a deflection angle ⁇ of this deflection is at least 50° and a delay in the middle Main flow velocity is at least 30%.
  • the deflection angle can be a deflection in the circumferential direction; in particular, the process fluid flowing out of an impeller can be freed from a circumferential component of the flow.
  • the flow guide SFG or the flow guided by it meets these conditions of deflection and deceleration at the outlet - it is also according to the invention if these conditions (deflection angle ⁇ (e.g. in the circumferential direction or from radial to axial) of this deflection at least 50° and a delay in the average main flow velocity of at least 30%) is achieved in the course of the flow in a section of the flow guide SFG, since the flow guide SFG has then reached a corresponding deflection.
  • deflection angle
  • the flow according to the invention passes the flow guide largely free of detachment despite a high aerodynamic load.
  • the flow guide SFG is divided radially into at least two radial segments RSG with regard to the deflection, so that the process fluid PFL is divided into parallel partial flows PPF as it flows through the flow guide SFG.
  • the examples in the figures each show 4 radial segments RSG, which are defined from one another by means of three radial guides RGE. In this way, cross flows in the radial direction are avoided, ie in a direction transverse to the deflection, so that in the flow guide SFG there is a forced, best possible approximation to a flow with little separation.
  • Such a flow guide or an arrangement of the impeller IMP, the flow guide SFG and a combination COL, which is designed as a spiral VLT in connection with a geared compressor GTC, is particularly expedient.
  • FIG 1 such a design is indicated, with the radial turbomachine RTM being attached to a gearbox GBX and the impeller IMP being attached to a shaft end of a pinion shaft PNS.
  • the pinion shaft PNS is driven by a large wheel of a drive shaft DRS.
  • the large wheel BGR preferably drives further pinion shafts PNS, which are also connected to radial turbomachines RTM in a manner that is not shown.
  • a preferred application of the invention provides that a geared compressor GTC is provided with a gear box GBX, with a radial turbomachine RTM being attached to the gear box GBX, which has a flow guide SFG according to the invention.
  • the flow guide SFG is preferably arranged downstream of an impeller IMP and upstream of a junction COL.
  • the individual radial segments RSG are largely arranged concentrically at least in sections and are separated from one another by means of radial guides RGE.
  • the radial guides RGE can also be referred to as radial guide vanes, which extend from an entry edge LE to an exit edge TE along a flow direction.
  • the figure 2 shows a detail of a special embodiment of a radial turbomachine RTM or a radial turbocompressor CMP.
  • the shaft SFT is preferably hollow in this case.
  • Both the impeller IMP—essentially the blades BLD here—and the recirculation stage RST have essentially axial inflows and outflows.
  • the blades BLD of the impellers IMP have leading edges LEI and trailing edges TEI.
  • the guide vanes VNS of the flow guide SFG downstream of an impeller IMP have leading edges LE and trailing edges TE.
  • the axial step length LSG--defined by the distance between the leading edges LEI of the blades BLD of two consecutive impellers IMP-- is preferably designed in relation to the mean maximum flow channel diameter DMM such that: 0.6 ⁇ LSG/DMM ⁇ 0.8.
  • Each of these radial segments RSG can be equipped with different numbers of guide vanes VNS.
  • Figure 3 is expressly based on a section in figure 2 Related, but can just as well as a section through the flow guide SFG figure 1 be understood.
  • the number of vanes of the guide vanes VNS can also vary from the inlet to the outlet of the flow guide SFG for at least one or all of the radial segments RSG.
  • Splitter blades and/or ribbed guide vanes can also be used as guide vanes VNS.
  • the flow guide SFG is geometrically complex, it can be manufactured in a technically simple and cost-effective manner, for example using additive manufacturing methods.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP20215303.7A 2020-12-18 2020-12-18 Guidage d'écoulement statique, turbomachine radiale Withdrawn EP4015832A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20215303.7A EP4015832A1 (fr) 2020-12-18 2020-12-18 Guidage d'écoulement statique, turbomachine radiale

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20215303.7A EP4015832A1 (fr) 2020-12-18 2020-12-18 Guidage d'écoulement statique, turbomachine radiale

Publications (1)

Publication Number Publication Date
EP4015832A1 true EP4015832A1 (fr) 2022-06-22

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EP20215303.7A Withdrawn EP4015832A1 (fr) 2020-12-18 2020-12-18 Guidage d'écoulement statique, turbomachine radiale

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4336049A1 (fr) * 2022-09-12 2024-03-13 Hamilton Sundstrand Corporation Diffuseur à canal variable

Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2419669A (en) * 1942-05-08 1947-04-29 Fed Reserve Bank Diffuser for centrifugal compressors
US3043229A (en) * 1957-05-27 1962-07-10 Worthington Corp Twin volute pump
AT295727B (de) * 1969-11-20 1972-01-10 Wilson Eng Co Inc Lee Eintrittsverteiler für Kreiselgebläse
DE3024769A1 (de) * 1980-06-30 1982-01-28 AOA Apparatebau Gauting GmbH, 8035 Gauting Leitkoerper bzw. luftleitkoerper fuer stroemungsmaschinen
DE3430307A1 (de) 1983-09-22 1985-04-04 Dresser Industries, Inc., Dallas, Tex. Diffusorbauweise fuer einen kreiselkompressor
US5105616A (en) 1989-12-07 1992-04-21 Sundstrand Corporation Gas turbine with split flow radial compressor
EP0592803B1 (fr) 1992-10-15 1997-03-05 MAN Gutehoffnungshütte Aktiengesellschaft Compresseur à arbres multiples et transmission
EP2055964A1 (fr) * 2007-04-20 2009-05-06 Mitsubishi Heavy Industries, Ltd. Compresseur centrifuge
US20100272564A1 (en) 2009-04-27 2010-10-28 Man Turbo Ag Multi stage radial compressor
GB2485835A (en) 2010-11-29 2012-05-30 Corac Group Plc Axially overlapping compressor impeller stages
WO2014072288A1 (fr) 2012-11-06 2014-05-15 Nuovo Pignone Srl Compresseur centrifuge avec aube à canal de retour torsadé
JP2014118925A (ja) 2012-12-19 2014-06-30 Ihi Corp 遠心圧縮機,インペラ,及びインペラの製造方法
DE102014203251A1 (de) 2014-02-24 2015-08-27 Siemens Aktiengesellschaft Rückführstufe für eine Radialturbomaschine
EP3364039A1 (fr) 2017-02-21 2018-08-22 Siemens Aktiengesellschaft Étage de retour
US20180274376A1 (en) * 2017-03-27 2018-09-27 General Electric Company Diffuser-deswirler for a gas turbine engine

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2419669A (en) * 1942-05-08 1947-04-29 Fed Reserve Bank Diffuser for centrifugal compressors
US3043229A (en) * 1957-05-27 1962-07-10 Worthington Corp Twin volute pump
AT295727B (de) * 1969-11-20 1972-01-10 Wilson Eng Co Inc Lee Eintrittsverteiler für Kreiselgebläse
DE3024769A1 (de) * 1980-06-30 1982-01-28 AOA Apparatebau Gauting GmbH, 8035 Gauting Leitkoerper bzw. luftleitkoerper fuer stroemungsmaschinen
DE3430307A1 (de) 1983-09-22 1985-04-04 Dresser Industries, Inc., Dallas, Tex. Diffusorbauweise fuer einen kreiselkompressor
US5105616A (en) 1989-12-07 1992-04-21 Sundstrand Corporation Gas turbine with split flow radial compressor
EP0592803B1 (fr) 1992-10-15 1997-03-05 MAN Gutehoffnungshütte Aktiengesellschaft Compresseur à arbres multiples et transmission
EP2055964A1 (fr) * 2007-04-20 2009-05-06 Mitsubishi Heavy Industries, Ltd. Compresseur centrifuge
US20100272564A1 (en) 2009-04-27 2010-10-28 Man Turbo Ag Multi stage radial compressor
GB2485835A (en) 2010-11-29 2012-05-30 Corac Group Plc Axially overlapping compressor impeller stages
WO2014072288A1 (fr) 2012-11-06 2014-05-15 Nuovo Pignone Srl Compresseur centrifuge avec aube à canal de retour torsadé
JP2014118925A (ja) 2012-12-19 2014-06-30 Ihi Corp 遠心圧縮機,インペラ,及びインペラの製造方法
DE102014203251A1 (de) 2014-02-24 2015-08-27 Siemens Aktiengesellschaft Rückführstufe für eine Radialturbomaschine
EP3364039A1 (fr) 2017-02-21 2018-08-22 Siemens Aktiengesellschaft Étage de retour
US20180274376A1 (en) * 2017-03-27 2018-09-27 General Electric Company Diffuser-deswirler for a gas turbine engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4336049A1 (fr) * 2022-09-12 2024-03-13 Hamilton Sundstrand Corporation Diffuseur à canal variable

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