EP2031184A1 - Dispositif de rupture de tourbillon pour turbomachine - Google Patents

Dispositif de rupture de tourbillon pour turbomachine Download PDF

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Publication number
EP2031184A1
EP2031184A1 EP07017133A EP07017133A EP2031184A1 EP 2031184 A1 EP2031184 A1 EP 2031184A1 EP 07017133 A EP07017133 A EP 07017133A EP 07017133 A EP07017133 A EP 07017133A EP 2031184 A1 EP2031184 A1 EP 2031184A1
Authority
EP
European Patent Office
Prior art keywords
swirl breaker
swirl
housing
rotor
turbomachine
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Withdrawn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
EP07017133A
Other languages
German (de)
English (en)
Inventor
Stefan Dr. Brück
Joachim Dr. Schettel
Michael Kleinhaus
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 EP07017133A priority Critical patent/EP2031184A1/fr
Publication of EP2031184A1 publication Critical patent/EP2031184A1/fr
Withdrawn legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • F05D2250/611—Structure; Surface texture corrugated undulated

Definitions

  • the invention relates to a turbomachine comprising a rotor rotatably mounted about a rotation axis and a housing arranged around the rotor, the housing having a housing inner surface formed opposite the rotor in a circumferential direction, wherein at least one gap is formed between the rotor and the housing inner surface a swirl breaker for reducing a twist of a secondary flow is disposed on the housing inner surface, the swirl breaker having a plurality of swirl breaker walls projecting from the housing inner surface distributed in the circumferential direction.
  • Turbomachines in the context of this invention are, for example, steam turbines, gas turbines or compressors, the invention preferably referring to steam turbines.
  • Turbomachines are characterized by a flow medium. Hydraulic turbines, steam and gas turbines, wind turbines, centrifugal pumps and centrifugal compressors as well as propellers are summarized under the collective term "turbomachinery". All of these machines have in common that they serve the purpose of extracting energy from one fluid in order to drive another machine, or vice versa, to supply energy to a fluid in order to increase its pressure.
  • the energy conversion is indirect and preferably takes the path over the kinetic energy of the fluid.
  • a flow medium flows in a main flow direction which substantially corresponds to the direction of the axis of rotation.
  • the flow medium should ideally only flow through a so-called flow channel, which has so-called guide vanes and rotor blades.
  • the flow channel is formed of different successively arranged guide and moving blades.
  • the flow medium flows through the flow channel on the guide and moving blades passing, whereby the kinetic energy is converted into rotational energy, which leads to a rotation of the rotor.
  • gaps between the housing and the rotor which should be made as small as possible. However, gaps can not be avoided, resulting in undesirable flow through the gaps.
  • a first approach is to arrange so-called sealing lips between the rotating and fixed components.
  • the sealing lips are arranged rotationally symmetrical and act as a kind of barrier to the secondary flow.
  • a secondary flow substantially flowing to the main flow is decelerated.
  • the secondary flow leads in turbomachinery to a further effect, which is undesirable.
  • the secondary flow through the gaps can produce or dampen existing rotor vibrations during operation, which appears depending on the prevailing boundary conditions.
  • This effect is referred to in fluid mechanics as Spalterregulation.
  • this effect is referred to as Dampfanfachung.
  • the direction of the gap branching flow medium portion has different direction components, in addition to the main directional component, which leads along the main flow channel also direction components are present, which are directed in the circumferential direction.
  • This circumferentially directed secondary flow component is also referred to as a spin.
  • the splitter excitation or vaporization depends on the direction and magnitude of this spin of the secondary flow entering the gap.
  • the secondary flow in turbines has the effect that it is more of a stimulating effect instead of a dampening.
  • swirl breaking means components which form a barrier to the secondary flow flowing in the circumferential direction, which is referred to as a swirl.
  • a brake fluid can be injected into the secondary flow in such a way that the swirl is thereby minimized or prevented.
  • the swirl breakers are formed of individual components and incorporated in a suitable manner in the circumferential direction individually into the housing. This leads to a high production cost, which leads to an increased production time.
  • the invention begins, whose task is to introduce a turbomachine with a swirl breaker, wherein the turbomachine can be made faster.
  • Another object of the invention is to provide swirl crushers that can be easily and quickly incorporated into turbomachinery.
  • a turbomachine comprising a rotor rotatably mounted about a rotation axis and a housing arranged around the rotor, the housing having a housing inner surface formed opposite the rotor in a circumferential direction, wherein a spin crusher for reducing a twist of a secondary flow is disposed on the housing inner surface wherein the swirl crusher has a plurality of swirl breaker walls projecting from the inside surface of the housing distributed in the circumferential direction, the swirl breaker being integrally formed with material.
  • the advantage of the invention is, inter alia, that it is now not necessary to produce individual swirl breaker walls, which are then incorporated relatively expensive in the housing interior surface.
  • a component component incorporating a material is obtained, which has a plurality of swirl breaker walls.
  • This built-in component can finally be quickly and easily and thereby inexpensively incorporated into the housing.
  • only one step is required to incorporate several swirl breaker walls in the turbomachine.
  • the swirl breaker walls each have a swirl breaker front wall and a swirl breaker back wall arranged behind it in the circumferential direction.
  • the swirlbreaker front wall is bent about a bend axis with respect to the swirl breaker back wall.
  • Sheet metal strip can be used as a flexible material for the swirl crusher. Basically, a band of this suitable material is sufficient, which is bent in different places in such a way that protruding swirl breaker walls are created. This gives the entire installation component, which ultimately only has to be installed in a groove in the turbomachine, thereby minimizing the production time.
  • the swirl breaker walls are advantageously directed along the axis of rotation.
  • the sealing strip is thus bent such that the kinks are formed perpendicular to the front edge of the sealing strip.
  • the sealing tape can be used for different housing inner diameter.
  • the swirl breaker is termed ISI, ISI, CS, CS, CS, CS, CS, CS, CS, CS, CS, CS, CS, CS, CS, CS
  • an additional bend is made which is substantially perpendicular to the bend to the swirl breaker walls.
  • the resulting embodiment leads to a barrier for the secondary flow in the main flow direction, which substantially corresponds to the axis of rotation.
  • the secondary flow has directional components to be described in a complicated manner, it greatly depends on the boundary conditions which form of the swirl breaker is suitable.
  • a swirl breaker wall is conceivable, which has rounded corners, has a triangular shape or has further geometric shapes.
  • the swirlbreaker front wall and the swirl breaker back wall are spaced near the groove, which results in the swirlbreaker front wall and the swirlbreaker back wall being substantially similar to an inverted V-shape.
  • the FIG. 1 shows a steam turbine 1 as an embodiment of a turbomachine. Further examples of a turbomachine are a gas turbine or a compressor.
  • the steam turbine 1 comprises an outer housing 2, which is designed as a pot housing. To outer housing 2, a lid 3 is arranged with fastening means. Within the outer housing 2, an inner housing 4 is arranged.
  • the inner housing 4 has guide vanes 5. For the sake of clarity is in the FIG. 1 only one vane provided with the reference numeral 5.
  • the steam turbine 1 has an inflow opening 6 through which steam flows as a flow medium during operation. The flow medium flows through a flow channel 7 past the guide vanes 5.
  • a rotor 8 is rotatably mounted about a rotation axis 9.
  • the rotor 8 comprises rotor blades arranged on the rotor surface 10. For the sake of clarity is in the FIG. 1 only one blade provided with the reference numeral 10.
  • the rotor 8 further includes a thrust balance piston 11, which is usually in high-pressure turbine part with a special Blading is used.
  • the steam flowing through the steam turbine 1 releases its energy to the rotor 8, so to speak, which leads to a rotation of the rotor 8.
  • the rotation of the rotor 8 is used, for example, to drive generators or pumps.
  • FIG. 2 is a section of a turbomachine shown.
  • the FIG. 2 shows a portion of a blade 10.
  • the blade 10 has a shroud 12 on. Opposite the shroud 12, a part of the inner housing 4 is shown.
  • the inner housing 4 has sealing lips 13, which are arranged rotationally symmetrically in the circumferential direction. Between the housing 4 and a shroud surface 14, a gap 15 is formed. A flow of the flow medium through this gap is perceived as a loss that should be prevented or minimized.
  • the majority of the flow medium flows along the main flow 16, substantially along the axis of rotation 9. In conical flow channels, the main flow direction is not necessarily along the axes of rotation 9. A comparatively small proportion of the main flow 16 branches in the radial direction 17 to the gap 15.
  • the secondary flow in addition to a radial flow component, also has a flow component which takes place in the circumferential direction 18.
  • a swirl breaker 19 is incorporated into a groove 20.
  • the groove 20 is milled on a housing inner surface 21.
  • the swirl breaker 19 is firmly clamped by means of a Stemm Federationes 22 in the groove 20.
  • FIG. 3 is a side view of the already wedged swirl breaker 19 shown in the groove 20.
  • the caulking pieces 22 are selected in size and material to provide a suitable force to hold the twist crusher 19 firmly in the groove 20.
  • FIG. 4 is a side view seen in the circumferential direction.
  • the swirl crusher 19 is in this case in the Width selected so that it can be easily and quickly incorporated by the Stemm consultancy 22 in the groove 20.
  • FIG. 5 a swirl breaker 19 is shown.
  • the swirl breaker 19, as in FIG. 5 is bent around a first edge 23 so that a swirl breaker front wall 24 and a swirl breaker back wall 25 are formed. Overall, this forms a swirl breaker wall 26, which is arranged distributed in the circumferential direction in the inner housing 4.
  • the swirl breaker 19 is bent around a second edge 27 and a third edge 28, so that an intermediate piece 29 is formed.
  • the Stemm choir 22 is placed on the intermediate piece 29 and fixed with suitable power transmission devices in the groove 20.
  • FIG. 6 a not yet produced swirl crusher 19 is shown.
  • a suitable band 30 of suitable flexible material Prior to bending the swirl breaker 19 about the first edge 23 and around the second edge 24 and around the third edge 28, a suitable band 30 of suitable flexible material is first cut to a suitable length. The length depends on the turbomachine to be improved. The band 30 is then bent around the first edge 23 and around the second edge 24 and around the edge 28 such that the swirl crusher 19 has an appearance as shown in FIG FIG. 5 is shown.
  • FIG. 7 illustrated embodiment of the swirl crusher 19 differs from the swirl crusher 19 FIG. 5 in that, in addition to the swirl breaker walls 26, a sealing lip 31 is additionally manufactured.
  • This additional sealing lip 31 is obtained by using a tape, as in the FIG. 8 is shown, which has a filler material for the sealing lip 31, the band is bent around a fourth edge 32, so that after bending a swirl breaker with an appearance according to FIG. 7 arises.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07017133A 2007-08-31 2007-08-31 Dispositif de rupture de tourbillon pour turbomachine Withdrawn EP2031184A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07017133A EP2031184A1 (fr) 2007-08-31 2007-08-31 Dispositif de rupture de tourbillon pour turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07017133A EP2031184A1 (fr) 2007-08-31 2007-08-31 Dispositif de rupture de tourbillon pour turbomachine

Publications (1)

Publication Number Publication Date
EP2031184A1 true EP2031184A1 (fr) 2009-03-04

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ID=39198680

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07017133A Withdrawn EP2031184A1 (fr) 2007-08-31 2007-08-31 Dispositif de rupture de tourbillon pour turbomachine

Country Status (1)

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EP (1) EP2031184A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2428649A1 (fr) * 2010-09-10 2012-03-14 Siemens Aktiengesellschaft Dispositif de rupture de tourbillon dans un courant de fuite d'une turbomachine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2462465A1 (de) * 1974-03-21 1977-04-28 Maschf Augsburg Nuernberg Ag Einrichtung zum dynamischen stabilisieren des laeufers eines verdichters
EP0122892A1 (fr) * 1983-03-18 1984-10-24 Fläkt Aktiebolag Procédé de fabrication d'une couronne d'aubes directrices pour le passage de retour dans les ventilateurs axiaux
US5489186A (en) * 1991-08-30 1996-02-06 Airflow Research And Manufacturing Corp. Housing with recirculation control for use with banded axial-flow fans
GB2340189A (en) * 1998-08-04 2000-02-16 Siemens Plc A turbomachine shroud seal having baffles
EP1069315A2 (fr) * 1999-07-15 2001-01-17 Hitachi, Ltd. Turbomachines
EP1515000A1 (fr) * 2003-09-09 2005-03-16 ALSTOM Technology Ltd Aubage d'une turbomachine avec un carenage contouré

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2462465A1 (de) * 1974-03-21 1977-04-28 Maschf Augsburg Nuernberg Ag Einrichtung zum dynamischen stabilisieren des laeufers eines verdichters
EP0122892A1 (fr) * 1983-03-18 1984-10-24 Fläkt Aktiebolag Procédé de fabrication d'une couronne d'aubes directrices pour le passage de retour dans les ventilateurs axiaux
US5489186A (en) * 1991-08-30 1996-02-06 Airflow Research And Manufacturing Corp. Housing with recirculation control for use with banded axial-flow fans
GB2340189A (en) * 1998-08-04 2000-02-16 Siemens Plc A turbomachine shroud seal having baffles
EP1069315A2 (fr) * 1999-07-15 2001-01-17 Hitachi, Ltd. Turbomachines
EP1515000A1 (fr) * 2003-09-09 2005-03-16 ALSTOM Technology Ltd Aubage d'une turbomachine avec un carenage contouré

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2428649A1 (fr) * 2010-09-10 2012-03-14 Siemens Aktiengesellschaft Dispositif de rupture de tourbillon dans un courant de fuite d'une turbomachine
WO2012032105A1 (fr) * 2010-09-10 2012-03-15 Siemens Aktiengesellschaft Élément suppresseur de tourbillonnement disposé dans l'écoulement de fuite d'une turbomachine
CN103109041A (zh) * 2010-09-10 2013-05-15 西门子公司 在流体机械的泄漏流中的涡旋破坏件
CN103109041B (zh) * 2010-09-10 2015-11-25 西门子公司 在泄漏流中具有涡旋破坏件的流体机械

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