WO2013132055A1 - Turbomachine radiale comprenant un élément de réduction de tourbillonnement - Google Patents

Turbomachine radiale comprenant un élément de réduction de tourbillonnement Download PDF

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Publication number
WO2013132055A1
WO2013132055A1 PCT/EP2013/054703 EP2013054703W WO2013132055A1 WO 2013132055 A1 WO2013132055 A1 WO 2013132055A1 EP 2013054703 W EP2013054703 W EP 2013054703W WO 2013132055 A1 WO2013132055 A1 WO 2013132055A1
Authority
WO
WIPO (PCT)
Prior art keywords
flow
swirl
radial
impeller
sealing
Prior art date
Application number
PCT/EP2013/054703
Other languages
German (de)
English (en)
Inventor
Marcus Meyer
Michael HENSGES
Dieter Nass
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2013132055A1 publication Critical patent/WO2013132055A1/fr

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Classifications

    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • 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
    • 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
    • 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
    • F05D2210/00—Working fluids
    • F05D2210/40—Flow geometry or direction
    • F05D2210/42—Axial inlet and radial outlet

Definitions

  • the invention relates to a radial flow machine with at least one impeller side space, which of a
  • Swirl reducing element occur, since this can be negatively influenced by, for example, an axial movement of a shaft.
  • the invention relates to a radial flow machine with at least one impeller side space, which of a swirling flow medium in the flow direction
  • At least one sealing element which is arranged in the impeller side space and seals it downstream, and at least one Swirl reducing element, which is arranged upstream of the at least one sealing element in the impeller side space.
  • Swirl reducing element has at least one flow guide, which forms at least one substantially axial flow channel for the swirling flow medium, and wherein the at least one swirl reducing element effectively immediately upstream of the at least one
  • Seal element is arranged.
  • the swirl can be effectively removed from the flow medium.
  • the arrangement according to the invention is uninfluenced by an axial movement of a shaft of the turbomachine caused, for example, by its thermal expansion or a shaft displacement in a thrust bearing.
  • a gap between a component which is rotatable with the shaft, such as an impeller or a balance piston, and a statically arranged component, such as a stator or a housing, can be reduced compared to prior art constructions.
  • a turbomachine here represents any machine that can be used by a person skilled in the art, such as a compressor or a gas turbine.
  • the terms radial flow machine and turbomachine are used interchangeably below.
  • the impeller side space adjacent, for example, to the impeller and is in particular arranged in an axial direction before and / or after the impeller.
  • the impeller side space is preferably a side space extending in a radial direction.
  • the at least one sealing element is for example a labyrinth seal.
  • downstream here defines an effect and / or an arrangement of a component, such as the at least one sealing element, in the direction of flow according to another structure, such as the impeller side space, and defines an effect and / or an arrangement of a structural component upstream. partly, such as the at least one
  • an element or a channel is to be understood, which / by a targeted selection of at least one property, such as a width, a height, a depth, a curvature, an orientation, a Cross section and / or one
  • the at least one swirl reduction element serves, in particular, to reduce the swirl of the swirling flow of the flow medium. Furthermore, the at least one flow channel of the at least one
  • the at least one flow guiding element and the at least one flow channel are arranged and / or formed such that the flow of the flow medium impinges on the at least one sealing element. Furthermore, the at least one flow-guiding element and the at least one flow channel are arranged and / or formed such that the flow of the flow medium from the at least one
  • Flow guide has at least two extensions, which limit the at least one flow channel.
  • the flow channel can be structurally easily adapted to its function.
  • the extensions are arranged in the circumferential direction of the at least one flow guide before and after the flow channel or limiting these the flow channel in the circumferential direction.
  • Swirl reduction element should not be limited to a round shape. Also conceivable would be an oval, square, square, triangular, square and / or any other form considered by the skilled person to be usable. Instead of circumference and circumferential direction, the terms contour or contour direction could also be used here. For the sake of simplicity, the terms circumferential and circumferential direction will be used in the following text.
  • the radial flow machine has a plurality of flow guide elements, which are arranged uniformly along the circumference of the at least one swirl reducing element.
  • the flow of the flow medium can emerge particularly uniformly from the at least one swirl reduction element. Due to the large number of flow guide elements, this has at least one Swirl reduction also on a variety of extensions and flow channels.
  • the at least two extensions and / or the multiplicity of extensions each have a substantially identical extent in the circumferential direction, as a result of which the exiting flow is particularly homogeneous.
  • the term "essentially the same” should be understood to mean a deviation of the extensions of + 10%
  • an axial extent and a radial extent of the extensions are also essentially the same
  • Swirl reduction element are arranged uniformly, whereby the flow can emerge particularly directional from the at least one swirl reducing element.
  • all flow channels in the circumferential direction each have a substantially equal extent.
  • an axial extent and a radial extent of the flow channels are also essentially the same.
  • each of the at least two extensions and / or the plurality of extensions and the at least one flow channel and / or the plurality of flow channels in the circumferential direction each have a substantially same extent.
  • the swirl of the flow can be reduced structurally simple and particularly efficient.
  • This reduction of the twist increases a resistance of a labyrinth of the at least one sealing element, as a result of which an effect of the labyrinth and thereby advantageously also of the at least one sealing element can be increased.
  • the radial turbomachine preferably has at least one sealing gap in which the at least one sealing element is arranged. Furthermore, it can be advantageous if the at least one swirl reducing element is arranged axially in the flow direction of the flow medium in front of the at least one sealing element. In this way, it can be advantageously achieved that the flow impinges directly on the at least one sealing element or the first labyrinth tip, in particular without having experienced a change of direction. Such a change in direction could, for example, again cause turbulence and thus reduce an effect of the labyrinth of the at least one sealing element, by reducing its resistance.
  • the at least one swirl reducing element is arranged at least partially in the sealing gap. This is to be understood by "at least partially" that at least one
  • Swirl reducing element is arranged in its axial extent to at least 30%, preferably at least 60% and particularly preferably 100% in the sealing gap.
  • the radial flow machine has at least one statically arranged component, in particular the stator or the housing.
  • An advantageous seal of a statically arranged component in particular the stator or the housing.
  • Housing interior can be achieved if the at least one sealing element is arranged on the at least one statically arranged component.
  • the at least one swirl reducing element is arranged on the at least one statically arranged component, whereby a secure positioning is achieved.
  • the radial flow machine has a, in particular rotatable, compensating element, in the form of a compensating piston, wherein the at least one at least one sealing gap is arranged radially between the compensating piston and the at least one statically arranged component, in particular designed as the stator.
  • a leakage caused by a compensation and / or rotational movement of the compensating piston can be minimized and ideally prevented in a structurally simple manner.
  • the term "radially between” should be understood to mean a radial direction starting from an axis of rotation of the turbomachine towards an outer housing of the turbomachine.
  • the radial turbomachine preferably has a rotatable component, for example in the form of an impeller, wherein the at least one sealing gap is arranged radially between the impeller and the at least one statically arranged component, in particular embodied as the housing.
  • the impeller has a wheel disc and a cover disc, wherein the wheel disc is arranged in the radial direction to the axis of rotation or to the shaft of the turbomachine and the cover disc in the radial direction towards the housing.
  • Swirl reducing element arranged on a cover plate side.
  • the at least one swirl reduction element and the at least one statically arranged component are embodied in one piece with one another, as a result of which installation space, assembly outlay and costs can advantageously be saved. This should be understood by the phrase "in one piece" that at least one
  • Swirl reducing element and the at least one statically arranged component are formed by the same component, are formed from a cast and / or only with loss of function of at least one of the components can be separated from each other. This also allows a higher efficiency of Flow machine. In principle, a separate embodiment could also be advantageous. As a result, the at least one swirl reducing element could be easily replaced in the event of damage.
  • a preferred development consists in that the at least one swirl reducing element and the at least one sealing element are made in one piece with each other.
  • the at least one swirl reducing element comprises a material which is elastic, resilient and / or abrasive. In this way, it can be ensured that in the event of unintentional touching or rubbing on of the at least one swirl reduction element and of another component, such as the impeller or the impeller
  • the at least one swirl reducing element comprises a material which is less hard than a material of the balance piston and / or the impeller, thereby ensuring that damage to these rotating components is prevented, since the material of at least one
  • Indulge swirl reduction element dodge and / or can adapt.
  • any plastic that is considered suitable by a person skilled in the art may be suitable, which is softer than the material of the balance piston and / or the impeller is.
  • the person skilled in the art taking into account factors or conditions of the turbomachine or its components, such as a gas composition of the flow medium, a temperature or pressure in the region of the at least one swirl reducing element, select the appropriate material independently.
  • Swirl reduction element selected from a group consisting for example of a polyetheretherketone (PEEK), Teflon and a metal having a Mohs hardness less than 4 or an alloy having a Mohs hardness less than 4.
  • PEEK polyetheretherketone
  • Teflon Teflon
  • FIG. 1 shows a section through a preferred embodiment of a radial flow machine according to the invention
  • FIG. 2 shows a swirl reduction element of the turbomachine from FIG. 1 in a perspective view
  • FIG 3 shows a section of the turbomachine of FIG 1 in
  • FIG. 1 shows a section through a preferred embodiment of a radial flow machine 10 according to the invention, in the form of a centrifugal compressor.
  • the turbomachine 10 has, as a static component 42, a housing 48 which encloses a housing interior 50.
  • a rotational axis 52 of the turbomachine 10 extends a shaft 54 around which extend in a circumferential direction 36 at least two rotatable components 56.
  • the rotatable components 56 are formed by a compensating piston 44 and an impeller 46, the impeller 46 being arranged in an axial direction 58 in front of the compensating piston 44.
  • a stator 62 is arranged above the compensating piston 44 as a statically arranged component 42.
  • the housing interior 50 each have an impeller side space 12, 14, which extends in each case in the radial direction 60.
  • the impeller side space 12 is bounded axially by the housing 48 and a top side 64 of the impeller 46 and the impeller side space 14 axially by a wheel disc 66 of the impeller 46 and the stator 62.
  • the flow medium 46 fed to the impeller 46 flows in a flow direction 16 through an impeller passage 68 in the radial direction 60 to the outside and leaves the impeller 46 in the direction of a diffuser (not shown).
  • a portion of the flow medium enters each of the radial impeller side chambers 12, 14 and flows in the direction of the shaft 54 in the direction of flow 16 in the radial direction 60.
  • a direction of the flow direction 16 thus changes locally, depending on how the components are arranged or how the radial flow machine 10 is constructed. Due to a rotation of the impeller 46, the flow medium is swirling, whereby each impeller side space 12, 14 of the swirling flow medium in the flow direction 16 can be flowed through.
  • a sealing element 18, 20 is arranged on one radial end 72 of the impeller side chambers 12, 14, which seals the respective impeller side space 12, 14 downstream.
  • the sealing elements 18, 20 are each formed by a labyrinth seal.
  • the turbomachine 10 per sealing element 18, 20 a sealing gap 38, 40, wherein the sealing gap 38 radially between the balance piston 44 and the statically arranged member 42 and the stator 62 and the Sealing gap 40 is arranged radially between the impeller 46 and the statically arranged component 42 and the housing 48 (see FIGS. 3 and 4).
  • the sealing elements 18, 20 are each arranged on a statically arranged component 42. Furthermore, the turbomachine 10 per sealing element 18, 20 on a swirl reducing element 22, 24, which is respectively upstream of the respective sealing element 18, 20 disposed in the impeller side space 12, 14 and serves to take the swirl from a flow of the flow medium.
  • the swirl reducing element 22, 24 is effective immediately upstream of the sealing element 18, 20 and in particular in the flow direction 16 of the flow medium axially in front of the
  • Sealing element 18, 20 and a first labyrinth tip 74 of the sealing element 18, 20 are arranged.
  • the respective swirl reducing element 22, 24 positioned in the respective sealing gap 38, 40, whereby the
  • Swirl reduction elements 22, 24 are arranged on a respective statically arranged component 42 (see Figures 3 and 4).
  • 2 shows the swirl reduction element 24 of the impeller side space 14, which is arranged radially between the housing 48 and the cover disk 64 of the impeller 46 (see FIG. 4), in a perspective detail representation by way of example for both swirl reduction elements 22, 24. All features described here for the swirl reduction element 24 also apply to the swirl reduction element 22, which is arranged radially between the stator 62 and the compensation piston 44 (see FIG. 3).
  • the swirl-reducing element 24 has a plurality of flow-guiding elements 26, 26 ', which are arranged uniformly along a circumference 34 of the swirl-reducing element 22, 24. For a better overview are only two
  • the flow guide 26 forms a substantially axial flow channel 28 for the swirling flow medium.
  • the flow guide 26 has two extensions 30, 32, which limit the flow channel 28 in the circumferential direction 36.
  • Each of the two extensions 30, 32 and the flow channel 28 have in the circumferential direction 36 each one in the
  • Substantially equal extension 38 is substantially equal (although the arrows to illustrate the respective
  • Extension 38, 76, 78 are shown differently in length for reasons of design, this should not restrict the feature of essentially the same extension).
  • This connecting ring 82 is a two-part ring or in other words, it is composed of two parts or two identical half-rings with extensions together (not shown). This allows easy installation of the swirl reduction element 24.
  • another connecting ring could also be provided on an inner circumference of the swirl reduction element 24 (not shown).
  • the swirl reducing member 24 is formed of Teflon, for example, whereby it is made of a material which is less hard compared to a material of the balance piston 44 and the impeller 46, such as stainless steel. As a result, it is elastic and abrasive relative to the balance piston 44 and the impeller 46.
  • FIG. 3 shows a detail of the turbomachine 10 in the region of the balancing piston 44 in a detailed representation (the dimensions of the components are for the better
  • the sealing element 18 is arranged in the sealing gap 38 radially between the balance piston 44 and the stator 62.
  • the swirl reduction element 22 is also arranged in the sealing gap 38, specifically in the flow direction 16, axially in front of the sealing element 18.
  • an extension 30 is shown in a plan view.
  • the sealing element 18 has an unspecified recess in whose profile a corresponding profile of the sealing element 18 can be received, whereby the sealing element 18 and the stator 62 are captively latched together.
  • Swirl reduction element 22 and the statically arranged component 42 and the stator 62 are integrally formed with each other.
  • FIG. 4 shows a further detail of the turbomachine 10 in the region of an impeller 46 in a detailed representation (the dimensions of the components are for better
  • the sealing element 20 is arranged in the sealing gap 40 radially between the impeller 46 and the housing 48. Also, the swirl reducing element 24 is arranged in the sealing gap 40 and in the flow direction 16 axially in front of the
  • the extension 30 is shown in a plan view.
  • the swirl reduction element 24 and the statically arranged component 42 or the housing 48 as well as the swirl reduction element 24 and the sealing element 20 are embodied in one piece with one another (the one-piece design is not shown in FIG. In principle, it would also be conceivable, only that
  • the swirl reduction element 24 and / or the sealing element 20 could be easily replaced in the event of their damage.
  • the swirl reduction elements 22, 24 By means of the swirl reduction elements 22, 24, the swirl can be withdrawn or reduced by the flow medium flowing through the impeller side chambers 12, 14 to the sealing elements 18, 20. As a result, the flow medium exits the swirl reducing element 22, 24 as an axial flow 84 and hits the first one with reduced swirl
  • Labyrinth tip 74 of the sealing element 18, 20 In this way, a resistance of a labyrinth of the sealing elements 18, 20 is increased, which increases the sealing properties of the sealing elements 18, 20 compared to constructions of the prior art. Thus, an efficiency of the turbomachine 10 can be increased and improved.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne une turbomachine radiale (10) comprenant au moins une chambre latérale de roue à aubes (12, 14) dans laquelle peut circuler un fluide d'écoulement tourbillonnant dans le sens d'écoulement (16), au moins un élément d'étanchéité (18, 20) disposé dans la chambre latérale de roue à aubes (12, 14) et rendant celle-ci étanche en aval et au moins un élément de réduction de tourbillonnement (22, 24) disposé en amont de l'élément d'étanchéité (18, 20) dans la chambre latérale de roue à aubes (12, 14). Pour obtenir une réduction efficace du tourbillonnement, il est proposé que ledit élément de réduction de tourbillonnement (22, 24) présente au moins un élément conducteur d'écoulement (26) qui forme au moins un canal d'écoulement (28) pratiquement axial pour le fluide d'écoulement tourbillonnant, et que ledit élément de réduction de tourbillonnement (22, 24) soit disposé opérationnellement directement en amont dudit élément d'étanchéité (18, 20).
PCT/EP2013/054703 2012-03-08 2013-03-08 Turbomachine radiale comprenant un élément de réduction de tourbillonnement WO2013132055A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012203690.3 2012-03-08
DE102012203690 2012-03-08

Publications (1)

Publication Number Publication Date
WO2013132055A1 true WO2013132055A1 (fr) 2013-09-12

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160298481A1 (en) * 2015-04-10 2016-10-13 United Technologies Corporation Rotating labyrinth m-seal

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH655357A5 (en) * 1981-09-28 1986-04-15 Sulzer Ag Method and device for reducing the axial thrust in turbo machines
US6129507A (en) * 1999-04-30 2000-10-10 Technology Commercialization Corporation Method and device for reducing axial thrust in rotary machines and a centrifugal pump using same
US20080181762A1 (en) * 2007-01-30 2008-07-31 Technology Commercialization Corporation Method and device for reducing axial thrust and radial oscillations and rotary machines using same
US20090004032A1 (en) * 2007-03-29 2009-01-01 Ebara International Corporation Deswirl mechanisms and roller bearings in an axial thrust equalization mechanism for liquid cryogenic turbomachinery
WO2012001995A1 (fr) * 2010-06-28 2012-01-05 三菱重工業株式会社 Dispositif d'étanchéité et machine fluidique comprenant celui-ci
EP2472123A1 (fr) * 2010-12-30 2012-07-04 Nuovo Pignone S.p.A. Systèmes et procédés de frein à spirale conique

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH655357A5 (en) * 1981-09-28 1986-04-15 Sulzer Ag Method and device for reducing the axial thrust in turbo machines
US6129507A (en) * 1999-04-30 2000-10-10 Technology Commercialization Corporation Method and device for reducing axial thrust in rotary machines and a centrifugal pump using same
US20080181762A1 (en) * 2007-01-30 2008-07-31 Technology Commercialization Corporation Method and device for reducing axial thrust and radial oscillations and rotary machines using same
US20090004032A1 (en) * 2007-03-29 2009-01-01 Ebara International Corporation Deswirl mechanisms and roller bearings in an axial thrust equalization mechanism for liquid cryogenic turbomachinery
WO2012001995A1 (fr) * 2010-06-28 2012-01-05 三菱重工業株式会社 Dispositif d'étanchéité et machine fluidique comprenant celui-ci
EP2472123A1 (fr) * 2010-12-30 2012-07-04 Nuovo Pignone S.p.A. Systèmes et procédés de frein à spirale conique

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160298481A1 (en) * 2015-04-10 2016-10-13 United Technologies Corporation Rotating labyrinth m-seal
US10502080B2 (en) * 2015-04-10 2019-12-10 United Technologies Corporation Rotating labyrinth M-seal

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