EP3377773B1 - Roue pour un turbocompresseur centrifuge - Google Patents

Roue pour un turbocompresseur centrifuge Download PDF

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Publication number
EP3377773B1
EP3377773B1 EP17700651.7A EP17700651A EP3377773B1 EP 3377773 B1 EP3377773 B1 EP 3377773B1 EP 17700651 A EP17700651 A EP 17700651A EP 3377773 B1 EP3377773 B1 EP 3377773B1
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EP
European Patent Office
Prior art keywords
blade
track
impeller
imp
angle
Prior art date
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Active
Application number
EP17700651.7A
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German (de)
English (en)
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EP3377773A1 (fr
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 Energy Global GmbH and Co KG
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Siemens Energy Global GmbH and Co KG
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Publication of EP3377773A1 publication Critical patent/EP3377773A1/fr
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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 turbo compressor, for rotation about an axis, comprising an inlet cross section for the essentially axial inflow of a process fluid into the impeller, comprising an outlet cross section for the essentially radial exit of the process fluid from the impeller, comprising a wheel disk which has a hub-side deflection contour defined from the axial flow direction to the radial flow direction, comprising blades attached to the wheel disc defining flow channels from a leading edge to a trailing edge circumferentially over at least a portion of the flow path of the process fluid through the impeller, each blade at a span end edge proximal to the wheel disc defines a linear inner track extending in the direction of flow, such that on both sides of the inner track there are orthogonal equal distances to a blade surface on a pressure side or a suction side of the blade, with the blade defining a linear outer track extending in the direction of flow at an end edge of extension distal to the wheel disk, such that on both sides of the outer
  • turbo compressors are already from the DE 10 2013 207 220 B3 known.
  • This turbo compressor type will also referred to as a centrifugal compressor, because the process fluid being transported is accelerated radially outwards in the impeller as a result of centrifugal forces.
  • mechanical energy is added to the gas or the process fluid for the purpose of compression by means of rotating blading of the impeller.
  • the sucked-in process fluid is decelerated relative to the movement of the impeller within the flow channels of the impeller formed between the individual blades and is thus compressed to a higher pressure level in accordance with the physical laws of fluid mechanics. Since the impeller moves at a high speed, the fluid, after flowing out of the impeller, is further decelerated in the radial direction in a subsequent diffuser and is additionally compressed in this way in accordance with Bernoulli's laws.
  • the documents EP 2 020 509 A2 , EP 2189 663 A2 , JP H02 37297 U each show a generic prior art.
  • the JP 2004 027894 A shows a three-dimensional impeller blade design of a centrifugal turbomachine.
  • the JP 2014 109193 A shows an impeller of a turbo compressor with the features of the preamble of claim 1.
  • the 3-dimensional figure extending beyond the trailing edge, wheel disc and cover disc and consisting of a pressure side and a suction side is referred to as the definition surface.
  • This definition area of the blade which is described by means of the angular distribution on the wheel disk and the cover disk and the blade thickness distribution, is used for the purpose of order processing. Within certain limits, sub-areas are extracted from this definition area - depending on the wheel disc and cover disc geometry - and used in an individual impeller design.
  • Geometric information such as axial, radial, tangential or circumferential direction always refers to an axis of rotation of the impeller, unless the reference is stated otherwise.
  • the invention has set itself the task of further developing an impeller for a turbo compressor in such a way that the efficiency is improved compared to conventional impellers for the same purpose.
  • relative blade lengths chosen by the invention allows the positions of the inner track and the outer track to be related in terms of their respective relative distances or proximity to the leading edge and trailing edge.
  • the invention offers an advantageous geometry of impellers both for so-called closed impellers (impellers with a cover disk) and for so-called open impellers that do not have a cover disk.
  • the preferred embodiment of the invention are impellers having a shroud defining the flow passages adjacent the blade span edges and attached to the blades in the region of the blade span edges.
  • the explanations that are made here for closed impellers and in part refer to a shroud also apply to open impellers that do not have a shroud.
  • the linear inner track extends along an end edge of the vanes that extends distally from the wheel disk between the leading edge and the trailing edge.
  • the open flow channels of the open impeller adjoin a stator contour, closing the openings distal to the wheel disc, so that the flow-related boundary conditions are similar for the purposes of the invention.
  • the geometry according to the invention is particularly advantageous when the progression of the meridional angle falls monotonously 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 does not have a local extremum in the angle profile along the relative blade length.
  • the maximum difference between the inner track and the outer track for a specific position along the relative blade lengths of the meridional angle is between 10° and 25°. It is the particular finding of the invention that the meridional angle distribution on the inner track and the outer track differ significantly. With the maximum In this context, difference does not mean the highest possible difference, but rather the highest difference that actually occurs. The invention therefore provides that there is an actual maximum difference of between 10° and 25° between the inner track and the outer track.
  • the aerodynamic efficiency is particularly advantageous if, as provided according to the invention, the location of the maximum difference between the inner track and the outer track is in the range between 15% and 45% of the relative blade length.
  • the trailing edge of the blades is not inclined relative to a meridional plane. Accordingly, it is proposed that the trailing edge of the blade encloses an angle with a meridional plane of between 0° and 5°.
  • the invention provides that the blade leading edge forms an angle of between 35° to 45°, preferably 41°, with a radial plane. Accordingly, the leading edge of the blade is set back somewhat compared to the inflow into the impeller.
  • a particularly advantageous development of the invention provides that the course of the meridional angle of the inner track has a turning point between 40% and 80% of the relative blade length.
  • the geometry recognized as being advantageous in this way contributes to a further improvement in the efficiency of the flow mechanics on the blade of the impeller according to the invention.
  • the profile of a blade thickness distribution of the outer track should preferably be monotonically increasing in the direction of flow.
  • the blade thickness distribution on the inner track can be chosen to be essentially constant.
  • figure 1 shows an axial top view of an impeller IMP according to the invention, comprising a cover disk COV, blades B and a wheel disk HW.
  • the axis of rotation X is indicated, about which the impeller rotates along a direction of rotation ROT during operation.
  • a meridional section II-II along a meridional plane MPL is indicated in a radial direction, which in figure 2 is reproduced.
  • the individual blades B each have a pressure side PRS and a suction side SCS. in the in figure 1 In the axial top view shown, the viewer can see the leading edge LE of the blade B.
  • each blade B has a linear inner track IT extending in the direction of flow on an end edge IE that is proximal to the wheel disk HW, in such a way that the same orthogonal distances to a blade surface on the pressure side PRS or the suction side SCS of the blade B are present on both sides of the inner track.
  • Each blade B has a line extending in the direction of flow on an end edge OE that is distal to the wheel disk HW Outer track on, such that on both sides of the outer track are orthogonally equal distances to the blade surface on the pressure side PRS and to the suction side SCS.
  • These corresponding inner tracks and outer tracks on the blades can also be defined in such a way that these tracks are each the set of center points of circles inscribed in the blade profiles.
  • the figure 3 shows the course of the meridional angle for the inner track IT and the outer track OT in the upper part of the diagram as a function of the relative blade length BLL and in the lower part of the diagram the derivation of the meridional angle MA ⁇ according to the relative blade length BL for the inner track IT and the outer track OT.
  • the blade leading edge LE forms an angle LEA of 41° with a radial plane RP.
  • leading edge of shovel B is set back a little bit.
  • the diagram of figure 4 shows the blade thickness distribution as a curve over the relative blade length BLL for the inner track IT and the outer track OT.
  • FIG. 5 shows details of such a sharpening on a leading edge of a wheel disk or cover disk in a schematic circumferential tangential section from a radial perspective.
  • the example shown there is dimensioned as follows: parameter wheel disk cover disk SDS 2.42mm SRS 3.73mm LZ 11.2mm 12.0mm LU 4.7mm 2.5mm SU 3.1mm 1.8mm
  • FIGs of Figures 3 and 4 each show a curve that continues on both sides beyond the 0% or 100% position of the relative blade length BLL.
  • This is a definition surface that is bounded by the inner and outer extension end edges OE, IE, the leading edge LE and the trailing edge TE of the blade B in the specific impeller.
  • the findings according to the invention regarding the distribution of the meridional angle MA for a blade B, also in connection with the blade thickness distribution for the inner track IT and the outer track OT, apply essentially independently of the section from this definition area provided certain limits are not exceeded. Within limits, this area can also be extrapolated.
  • the description of the blades B by means of the distribution of the meridional angle MA and the thickness distribution over the extent of the blades B in the direction of flow or the relative blade length BLL leads to a three-dimensional surface when the blade profiles spanned by the inner track and the outer track are connected by means of the thickness distribution by means of straight lines in space, which can be produced by means of a flank milling process.
  • the three-dimensional blade spanned by means of so-called control lines between the outer and inner blade profiles is fundamentally preferred, with a geometry other than a straight line also being conceivable in accordance with the invention, for example an arc defined by a polygon or splines and vertices.
  • the design of the blade B of an impeller IMP according to the invention is as follows figure 3 suggest that between about 10% and 90% of the relative blade length BLL there is a local extremum LEX of the meridional angle MA of the inner track IT.
  • This local extremum LEX is preferably between 25% and 45% of the relative blade length BLL.
  • 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 being between 10° and 25°.
  • this maximum difference DLTM occurs in the range between 15% and 45% of the relative blade length BLL.
  • the mean extent of the trailing edge TE of the blade B is at an angle with a meridional plane MPL of about 0° includes or is parallel to this meridional plane MPL.
  • This angular deviation from the meridional plane MPL of the trailing edge TE should preferably be less than 5°.
  • Another particularly preferred embodiment of the invention shown in the exemplary embodiment provides that the profile of the meridional angle MA of the inner track IT has a turning point 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)

Claims (8)

  1. Roue (IMP) mobile d'un turbocompresseur (TCO) pour la rotation autour d'un axe (X), comprenant une section (IN) transversale d'entrée pour l'afflux sensiblement axial d'un fluide (PF) de processus dans la roue (IMP) mobile, comprenant une section (EX) transversale de sortie pour la sortie essentiellement radiale du fluide (PF) de processus de la roue (IMP) mobile,
    comprenant un disque (HW) de roue, qui définit un contour de déviation, du côté du moyeu, de la direction d'écoulement axiale à la direction d'écoulement radiale,
    comprenant des aubes (B) montées sur le disque (HW) de roue, qui, au moins sur une partie du chemin d'écoulement du fluide (PF) de processus dans la roue (IMP) mobile, définissent dans la direction périphérique des canaux (FC) d'écoulement d'un bord (LE) d'entrée à un bord (TE) de sortie,
    dans laquelle chaque aube (B) définit, à un bord (IE) d'extrémité d'étendue proximal par rapport au disque (HW) de roue, une trace (IT) intérieure linéaire, s'étendant dans la direction d'écoulement, de manière à avoir, des deux côtés de la trace intérieure, orthogonalement de mêmes distances à une surface de l'aube à l'intrados (PRS) et à l'extrados (SCS) de l'aube (B),
    dans laquelle l'aube (B) définit, à un bord (OE) d'extrémité d'étendu distale par rapport au disque (HW) de roue, une trace extérieure linéaire, s'étendant dans la direction d'écoulement, de manière à avoir, des deux côtés de la trace (OT) extérieure, orthogonalement de mêmes distances à la surface de l'aube à l'intrados (PRS) et à l'extrados (SCS) de l'aube (B),
    dans laquelle une longueur (BLL) relative de l'aube, pour chaque position sur une trace (T), qui est une trace (IT) intérieure ou une trace (OT) extérieure, sont définies respectivement comme une proportion de la longueur de l'aube se trouvant en amont de cette position, par rapport à toute la longueur de l'aube de la trace (T) concernée, à savoir trace (IT) intérieure ou trace (OT) extérieure,
    dans laquelle un angle (MA) méridien, pour chaque position d'une trace (T), est définit comme l'angle formé en amont entre un plan (MPL) méridien passant par cette position et une tangente à la trace (T),
    dans laquelle, dans la plage comprise entre 10 % et 90 % de la longueur (BLL) relative de l'aube, il y a un extrémum (LEX) local de l'angle (MA) méridien de la trace (IT) intérieure,
    dans laquelle le bord (LE) d'entrée de l'aube forme, avec un plan (RP) radial un angle (LEA) allant de 35° à 45°, caractérisée
    en ce que, dans la plage comprise entre 10 % et 90 % de la longueur (BLL) relative de l'aube, la différence (DLTM) maximum entre la trace (IT) intérieure et la trace (OT) extérieure, pour une position définie le long des longueurs (BLL) relatives d'aube de l'angle (MA) méridien, est compris entre 10° et 25°, dans lequel la différence (DLTM) maximum, entre la trace (IT) intérieure et la trace (OT) extérieure le long des longueurs (BLL) relatives d'aube de l'angle (MA) méridien, est dans la plage comprise entre 15 % et 45 % des longueurs (BLL) relatives de l'aube.
  2. Roue (IMP) mobile suivant la revendication 1, dans laquelle l'extrémum (LEX) local de la courbe de l'angle (MA) méridien de la trace (IT) intérieure représente entre 25 % et 45 % de la longueur (BLL) relative de l'aube.
  3. Roue (IMP) mobile suivant la revendication 1, dans laquelle la courbe de l'angle (MA) méridien diminue de manière monotone entre 10 % et 90 % de la longueur (BLL) relative de l'aube de la trace (OT) extérieure.
  4. Roue (IMP) mobile suivant la revendication 1, dans laquelle la roue (IMP) mobile a un flasque (COV) avant, qui définit les canaux (FC) d'écoulement au voisinage des bords (OE) d'extrémité d'étendue et qui est monté sur les aubes (B) dans la partie des bords (OE) d'extrémité d'étendue.
  5. Roue (IMP) mobile suivant la revendication 1, dans laquelle l'étendue médiane du bord (TE) de sortie de l'aube (B) fait un angle avec un plan (MPL) méridien compris entre 0° et 5°, de préférence de 0°.
  6. Roue (IMP) mobile suivant la revendication 1, dans laquelle la courbe de l'angle (MA) méridien de la trace (IT) intérieure a un point (TP) d'inflexion entre 40 % et 80 % de la longueur (BLL) relative de l'aube.
  7. Roue (IMP) mobile suivant la revendication 1, dans laquelle, dans la plage comprise entre 10 % et 90 % des longueurs (BLL) relatives de l'aube, la courbe d'une répartition (BT) d'épaisseur d'aube de la trace (OT) extérieure est croissante, de manière monotone, dans la direction d'écoulement.
  8. Roue (IMP) mobile suivant la revendication 1, dans laquelle le bord (LE) d'entrée de l'aube fait un angle (LEA) de 41° avec un plan (RP) radial.
EP17700651.7A 2016-02-09 2017-01-13 Roue pour un turbocompresseur centrifuge Active EP3377773B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP16154853.2A EP3205883A1 (fr) 2016-02-09 2016-02-09 Roue pour un turbocompresseur centrifuge
PCT/EP2017/050626 WO2017137207A1 (fr) 2016-02-09 2017-01-13 Rotor pour turbocompresseur centrifuge

Publications (2)

Publication Number Publication Date
EP3377773A1 EP3377773A1 (fr) 2018-09-26
EP3377773B1 true EP3377773B1 (fr) 2023-05-31

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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

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EP16154853.2A Withdrawn EP3205883A1 (fr) 2016-02-09 2016-02-09 Roue pour un turbocompresseur centrifuge

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

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DE102017223791A1 (de) 2017-12-27 2019-06-27 Siemens Aktiengesellschaft Wellendichtungsanordnung einer Turbomaschine, Turbomaschine
GB2576565B (en) 2018-08-24 2021-07-14 Rolls Royce Plc Supercritical carbon dioxide compressor
GB2576564B (en) * 2018-08-24 2021-01-13 Rolls Royce Plc Supercritical carbon dioxide compressor
GB201813819D0 (en) 2018-08-24 2018-10-10 Rolls Royce Plc Turbomachinery
JP6970310B2 (ja) * 2018-12-19 2021-11-24 三菱重工エンジン＆ターボチャージャ株式会社 ノズルベーン
MX2021010819A (es) * 2019-04-08 2021-10-01 Zhongshan Ebs Tech Co Ltd Ventilador centrifugo con paletas hacia atras.
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
US11421702B2 (en) 2019-08-21 2022-08-23 Pratt & Whitney Canada Corp. Impeller with chordwise vane thickness variation

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Publication number Publication date
EP3377773A1 (fr) 2018-09-26
US20190032671A1 (en) 2019-01-31
WO2017137207A1 (fr) 2017-08-17
US10865803B2 (en) 2020-12-15
EP3205883A1 (fr) 2017-08-16

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