EP3205883A1 - Roue pour un turbocompresseur centrifuge - Google Patents

Roue pour un turbocompresseur centrifuge Download PDF

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Publication number
EP3205883A1
EP3205883A1 EP16154853.2A EP16154853A EP3205883A1 EP 3205883 A1 EP3205883 A1 EP 3205883A1 EP 16154853 A EP16154853 A EP 16154853A EP 3205883 A1 EP3205883 A1 EP 3205883A1
Authority
EP
European Patent Office
Prior art keywords
track
impeller
imp
blade
bll
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Withdrawn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
EP16154853.2A
Other languages
German (de)
English (en)
Inventor
Christian Woiczinski
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 AG
Original Assignee
Siemens AG
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 AG filed Critical Siemens AG
Priority to EP16154853.2A priority Critical patent/EP3205883A1/fr
Priority to EP17700651.7A priority patent/EP3377773B1/fr
Priority to PCT/EP2017/050626 priority patent/WO2017137207A1/fr
Priority to US16/075,730 priority patent/US10865803B2/en
Publication of EP3205883A1 publication Critical patent/EP3205883A1/fr
Withdrawn legal-status Critical Current

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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
    • F04D29/26—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
    • F04D25/045—Units comprising pumps and their driving means the pump being fluid-driven the pump wheel carrying the fluid driving means, e.g. turbine blades
    • 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
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/713—Shape curved inflexed

Definitions

  • the invention relates to an impeller of a turbocompressor, for rotation about an axis, comprising an inlet cross section for substantially axial inflow of a process fluid into the impeller, comprising an outlet cross section for substantially radial outlet of the process fluid from the impeller, comprising a wheel disc having a hub-side Umlenkkontur from the axial flow direction to the radial flow direction, comprising paddles attached to the wheel disc defining flow channels from an entrance edge to a circumferential exit edge over at least a portion of the process fluid flow path through the impeller, each paddle at a tip end extension end proximate the wheel disc a line-like inner track extending in the flow direction is defined, such that on both sides the inner track has orthogonal equal distances to a blade surface on a pressure side or a suction side of the blade v Oro, wherein the blade at a distal end to the wheel distal end defines a linear outer track extending in the flow direction, such that on both sides of the outer track orthogonal e
  • turbocompressors are already out of the DE 10 2013 207 220 B3 known.
  • This turbo compressor type is also referred to as a centrifugal compressor, because the conveyed process fluid is accelerated radially outward in the impeller as a result of centrifugal forces.
  • mechanical energy is added to the gas or the process fluid for the purpose of compaction by means of a rotating blading of the impeller.
  • the aspirated process fluid is delayed within the flow channels of the impeller formed between the individual blades relative to the movement of the impeller and thus compressed according to the physical laws of fluid mechanics to a higher pressure level. Since the impeller is moving at a high speed, the fluid is further retarded after flowing out of the impeller in the radial direction in a subsequent diffuser and additionally compressed in this way according to the laws of Bernoulli.
  • this definition surface This, beyond the boundaries of the leading edge, trailing edge, wheel disc and cover disc outgoing 3-dimensional figure consisting of a pressure side and a suction side is referred to as a definition surface.
  • this definition surface of the blade is used, which by means of the angular distribution at the Wheel disc and the cover plate and the blade thickness distribution is described. Within certain limits, partial surfaces are extracted from this definition surface, depending on the wheel disc and cover disc geometry, and used in an individual impeller design.
  • Geometrical indications such as axial, radial, tangential or circumferential direction always refer to a rotational axis of the impeller, unless the reference is otherwise stated.
  • the invention has set itself the task of developing an impeller for a turbocompressor such that the efficiency over conventional wheels for the same purpose is improved.
  • a local extremum of the meridional angle of the inner track is present in the range between 10% and 90% of the relative blade length.
  • relative blade lengths chosen by the invention allows for the inclusion of positions of the inner track and the outer track with respect to the respective relative distances to the leading edge and trailing edge.
  • the invention provides an advantageous geometry of wheels both for so-called closed wheels (wheels with a cover plate) and for so-called open wheels, which have no cover plate.
  • the preferred embodiment of the invention are impellers with a Cover disc, which defines the flow channels adjacent to the extension end edges of the blades and is attached to the blades in the region of the end extension edges of the blades.
  • the designs that are made here for closed wheels and partially relate to a cover plate also apply to open wheels that have no cover plate.
  • the linear inner track extends along an end face of the blades that is distal from the wheel disc between the leading edge and the trailing edge.
  • the open flow channels of the open impeller border on a stator contour, sealing the openings distal to the wheel disc, so that the fluidic boundary conditions are similar for purposes of the invention.
  • the geometry according to the invention is particularly advantageous if the course of the meridional angle is monotonically decreasing between 10% and 90% of the relative blade length of the outer track.
  • the findings of the invention indicate that the efficiency of the impeller can be increased if, in contrast to the inner track, the outer track has no local extremum in the angular course along the relative blade length.
  • An advantageous development of the invention provides that in the range between 10% and 90% of the relative blade lengths, the maximum difference between the inner track and the outer track for a specific position along the relative blade lengths of the meridional angle between 10 ° and 25 °.
  • the meridional angle distribution on the inner track and the outer track differ significantly.
  • the maximum difference in this context does not mean the highest possible difference, but the highest actually occurring difference.
  • the invention thus provides in this advantageous development that an actual maximum difference occurs, which is between 10 ° and 25 ° between the inner track.
  • Particularly advantageous is the fluidic Efficiency when the location of the maximum difference between the inner and outer tracks is between 15% and 45% of the relative blade length.
  • trailing edge of the blades is not inclined with respect to a meridional plane. Accordingly, it is proposed that the trailing edge of the blade enclose an angle with a meridional plane between 0 ° to 5 °.
  • the blade inlet edge forms an angle between 35 ° to 45 °, preferably 41 ° with a radial plane.
  • the leading edge of the blade is accordingly set back slightly with respect to the inflow into the impeller.
  • a particularly advantageous embodiment of the invention provides that in the range between 10% to 90% of the relative blade length, the course of the meridional angle of the inner track has a turning point between 40% to 80% of the relative blade length.
  • the geometry recognized as advantageous in this manner contributes to a further improvement in the efficiency of the fluid mechanics on the blade of the impeller according to the invention.
  • the profile of a blade thickness distribution of the inner track in the direction of flow should preferably be monotonically increasing.
  • the blade thickness distribution on the outer track can be selected substantially constant.
  • FIG. 1 shows an axial plan view of an inventive impeller IMP, comprising a cover plate COV, blades B and a wheel disc HW.
  • the axis of rotation X is indicated, around which the impeller rotates in operation along a direction of rotation ROT.
  • a meridional section II-II along a meridional plane MPL is given, which in FIG. 2 is reproduced.
  • the individual blades B each have a pressure side PRS and a suction side SCS.
  • axial plan view shows the viewer the leading edge LE of the blade B.
  • Each vane B has a line-like inner track IT extending in the direction of flow at an extension end edge IE which is proximal to the wheel disc HW such that orthogonal distances to a vane surface on the pressure side PRS or the suction side SCS of the vane B are present on both sides of the inner track.
  • Each blade B has at a distance to the wheel HW distal end edge OE extending in the flow direction linear outer track, such that on both sides of the outer track orthogonal equal distances to the blade surface on the pressure side PRS and the suction side SCS are present.
  • These corresponding inner and outer tracks on the blades can also be defined such that these tracks are respectively the set of centers of circles inscribed in the blade profiles.
  • FIG. 3 shows in each case as a function of the relative blade length BLL in the upper diagram area the course of the meridional angle for the inner lane IT and the outer lane OT and in the lower diagram area the derivative of the meridional angle MA 'to the relative blade length BL for the inner lane IT and the outer lane OT.
  • the blade leading edge LE here forms an angle LEA of 41 ° with a radial plane RP.
  • the leading edge of the blade B is accordingly set back slightly.
  • FIG. 4 shows the blade thickness distribution as a course over the relative blade length BLL for the inner track IT and the outer track OT.
  • FIG. 5 shows details of such a sharpening at an entry edge of a wheel disc or cover disk in a schematic Circumferential tangential section from radial view.
  • the example shown there is dimensioned in such a way: parameter wheel disc cover disc SDS 2.42 mm SRS 3.73 mm LZ 11.2 mm 12.0 mm LU 4.7 mm 2.5 mm SU 3.1 mm 1.8 mm
  • SDS blade thickness cover disc COV
  • LU transition thickness SU: Transition length.
  • FIGs of Figures 3 and 4 each show a course that is continued on both sides beyond the 0% or 100% position of the relative blade length BLL.
  • This is a definition surface that is bounded in the concrete impeller by the inner and outer extension end edge OE, IE, the leading edge LE and the trailing edge TE of the blade B, respectively.
  • the findings according to the invention on the distribution of the meridional angle MA for a blade B, also in conjunction with the blade thickness distribution for the inner track IT and the outer track OT, apply essentially independently of the section of this definition surface, provided that certain limits are not exceeded. Within limits, an extrapolation of this area can also take place.
  • the description of the blades B by means of the distribution of the meridional angle MA and the thickness distribution over the extension of the blades B in the direction of flow and the relative blade length BLL results in a connection of the inner track and the outer track by means of the thickness distribution spanned blade profiles by means of straight lines to a three-dimensional surface in the room, which can be produced by means of a flank milling process.
  • the three-dimensional blade spanned by the so-called regular straight line between the outer and inner blade profiles is basically preferred, although a geometry other than a straight line is also conceivable according to the invention, for example an arc defined by means of a polygon or splines and support points.
  • the inventive design of the blade B of an impeller IMP looks after FIG. 3 in that between about 10% to 60% of the relative blade length BLL there is a local extreme LEX of the meridional angle MA of the inner track IT.
  • this local extremum LEX is between 25% to 45% of the relative blade length BLL.
  • Particularly preferred is - as in FIG. 3 , the first diagram shown - the course of the meridional angle MA for the outer track OT monotonically decreasing between 10% to 90% of the relative blade length.
  • there is a difference in the meridional angle MA between the inner track IT and the outer track OT which increases to a maximum difference DLTM along the relative blade length, this actual maximum difference, between 10 ° and 25 °.
  • this maximum difference DLTM occurs in the range between 15% to 45% of the relative blade length BLL.
  • a further particularly preferred embodiment of the invention shown in the exemplary embodiment provides that the course of the meridional angle MA of the inner track IT has a point of inflection TP in the range between 40% and 80% of the relative blade length BLL.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP16154853.2A 2016-02-09 2016-02-09 Roue pour un turbocompresseur centrifuge Withdrawn EP3205883A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP16154853.2A EP3205883A1 (fr) 2016-02-09 2016-02-09 Roue pour un turbocompresseur centrifuge
EP17700651.7A EP3377773B1 (fr) 2016-02-09 2017-01-13 Roue pour un turbocompresseur centrifuge
PCT/EP2017/050626 WO2017137207A1 (fr) 2016-02-09 2017-01-13 Rotor pour turbocompresseur centrifuge
US16/075,730 US10865803B2 (en) 2016-02-09 2017-01-13 Impeller wheel for a centrifugal turbocompressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16154853.2A EP3205883A1 (fr) 2016-02-09 2016-02-09 Roue pour un turbocompresseur centrifuge

Publications (1)

Publication Number Publication Date
EP3205883A1 true EP3205883A1 (fr) 2017-08-16

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EP16154853.2A Withdrawn EP3205883A1 (fr) 2016-02-09 2016-02-09 Roue pour un turbocompresseur centrifuge
EP17700651.7A Active EP3377773B1 (fr) 2016-02-09 2017-01-13 Roue pour un turbocompresseur centrifuge

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP17700651.7A Active EP3377773B1 (fr) 2016-02-09 2017-01-13 Roue pour un turbocompresseur centrifuge

Country Status (3)

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US (1) US10865803B2 (fr)
EP (2) EP3205883A1 (fr)
WO (1) WO2017137207A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110259721A (zh) * 2019-06-13 2019-09-20 西北工业大学 一种具有高压比的离心式压气机叶轮
GB2576564A (en) * 2018-08-24 2020-02-26 Rolls Royce Plc Turbomachinery
US11111793B2 (en) 2018-08-24 2021-09-07 Rolls-Royce Plc Turbomachinery
US11111792B2 (en) 2018-08-24 2021-09-07 Rolls-Royce Plc Turbomachinery

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017223791A1 (de) 2017-12-27 2019-06-27 Siemens Aktiengesellschaft Wellendichtungsanordnung einer Turbomaschine, Turbomaschine
US11428154B2 (en) * 2018-12-19 2022-08-30 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Nozzle vane
WO2020206918A1 (fr) * 2019-04-08 2020-10-15 中山宜必思科技有限公司 Ventilateur centrifuge vers l'arrière
US11421702B2 (en) 2019-08-21 2022-08-23 Pratt & Whitney Canada Corp. Impeller with chordwise vane thickness variation

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0237297U (fr) * 1988-09-01 1990-03-12
JP2004027894A (ja) * 2002-06-24 2004-01-29 Mitsubishi Heavy Ind Ltd オープン羽根車
EP2020509A2 (fr) * 2007-08-03 2009-02-04 Hitachi Plant Technologies, Ltd. Compresseur centrifuge, roue de compresseur centrifuge et son procédé de fonctionnement
EP2189663A2 (fr) * 2008-11-21 2010-05-26 Hitachi Plant Technologies, Ltd. Compresseur centrifuge
DE102013207220B3 (de) 2013-04-22 2014-09-18 Siemens Aktiengesellschaft Turbomaschine

Family Cites Families (6)

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Publication number Priority date Publication date Assignee Title
JP6034162B2 (ja) * 2012-11-30 2016-11-30 株式会社日立製作所 遠心式流体機械
WO2016151689A1 (fr) * 2015-03-20 2016-09-29 三菱重工業株式会社 Compresseur centrifuge et turbocompresseur le comprenant
ITUB20153620A1 (it) * 2015-09-15 2017-03-15 Nuovo Pignone Tecnologie Srl Girante per turbomacchina ad elevata rigidezza, turbomacchina comprendente detta girante e metodo di produzione
DE102015012259A1 (de) * 2015-09-19 2016-04-07 Daimler Ag Turbinenrad für eine Turbine eines Abgasturboladers
US20180142557A1 (en) * 2016-11-19 2018-05-24 Borgwarner Inc. Turbocharger impeller blade stiffeners and manufacturing method
JP6806551B2 (ja) * 2016-12-14 2021-01-06 株式会社豊田中央研究所 遠心圧縮機、ターボチャージャ

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0237297U (fr) * 1988-09-01 1990-03-12
JP2004027894A (ja) * 2002-06-24 2004-01-29 Mitsubishi Heavy Ind Ltd オープン羽根車
EP2020509A2 (fr) * 2007-08-03 2009-02-04 Hitachi Plant Technologies, Ltd. Compresseur centrifuge, roue de compresseur centrifuge et son procédé de fonctionnement
EP2189663A2 (fr) * 2008-11-21 2010-05-26 Hitachi Plant Technologies, Ltd. Compresseur centrifuge
DE102013207220B3 (de) 2013-04-22 2014-09-18 Siemens Aktiengesellschaft Turbomaschine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2576564A (en) * 2018-08-24 2020-02-26 Rolls Royce Plc Turbomachinery
GB2576564B (en) * 2018-08-24 2021-01-13 Rolls Royce Plc Supercritical carbon dioxide compressor
US11111793B2 (en) 2018-08-24 2021-09-07 Rolls-Royce Plc Turbomachinery
US11111792B2 (en) 2018-08-24 2021-09-07 Rolls-Royce Plc Turbomachinery
CN110259721A (zh) * 2019-06-13 2019-09-20 西北工业大学 一种具有高压比的离心式压气机叶轮

Also Published As

Publication number Publication date
EP3377773B1 (fr) 2023-05-31
WO2017137207A1 (fr) 2017-08-17
US10865803B2 (en) 2020-12-15
EP3377773A1 (fr) 2018-09-26
US20190032671A1 (en) 2019-01-31

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