EP1746256A1 - Diminution des pertes dues au jeu en bout d'aubes dans les turbomachines - Google Patents

Diminution des pertes dues au jeu en bout d'aubes dans les turbomachines Download PDF

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Publication number
EP1746256A1
EP1746256A1 EP05015779A EP05015779A EP1746256A1 EP 1746256 A1 EP1746256 A1 EP 1746256A1 EP 05015779 A EP05015779 A EP 05015779A EP 05015779 A EP05015779 A EP 05015779A EP 1746256 A1 EP1746256 A1 EP 1746256A1
Authority
EP
European Patent Office
Prior art keywords
blade
gap
sealing element
sealing
vane
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Withdrawn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
EP05015779A
Other languages
German (de)
English (en)
Inventor
Christof Fischer
Carmen-Elisabeth Dr. Kachel
Martin Westfahl
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 EP05015779A priority Critical patent/EP1746256A1/fr
Publication of EP1746256A1 publication Critical patent/EP1746256A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • 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
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom

Definitions

  • the invention relates to a turbomachine, which has seen in succession, at least one blade and at least one vane, each spaced with their blade tips to a respective opposite sealing surface, so that a blade gap or a vane gap between the respective blade tips and each associated sealing surfaces is formed.
  • turbomachines are known, for example, as a compressor, steam turbine or gas turbine.
  • the turbomachine has a rotor rotatably mounted about a rotation axis on which the blade is anchored.
  • a stationary component is arranged such that a radial gap is created between the blade tip and the stationary component.
  • the stationary component can be configured, for example, as an inner housing.
  • the inner housing is associated with the guide vane, so that the inner housing is designed as a guide vane carrier.
  • a flow medium flows past the blade substantially along the axis of rotation.
  • the flow of the flow medium includes a lost flow that forms along the radial gap. Loss flow can also be referred to as gap loss.
  • the gap losses arise, for example, in that the flow medium does not follow its predetermined path through the blade lattice formed by the blades and vanes arranged one behind the other, but flows through between the blade tip and the respective sealing surface or radial gap. This leads to a reduction of the technical work and thus to a lower efficiency of the turbomachine.
  • one of the known sealing concepts provides for the use of a labyrinth seal in which stepped labyrinth gaps are formed between the rotating part (rotor, blade tip) and the fixed part (vane support, vane tip).
  • sealing tips are respectively arranged on the rotating and the stationary part, whereby a high degree of turbulence of the flowing through flow medium is to be achieved.
  • the sealing tips between the fixed part and the rotating part are arranged as close to each other as possible, so that only a small axial gap is present.
  • the sealing tips are stretched so that sealing tips of two adjacent stages overlap.
  • a group of sealing tips may be caulked into a corresponding groove by means of a caulking wire.
  • the existing radial gaps depend, for example, greatly on the different thermal expansion (rotating part, stationary part) and the centrifugal force expansion during operation of the turbomachine.
  • the influence of centrifugal force is observed in particular in industrial flow machines with different operating speeds.
  • erosion, d. H. a continuous leaching the gap can also be increased.
  • the selected distance In order to prevent the blade tips from rubbing against the respectively assigned sealing surfaces under all operating conditions, the selected distance, so the radial gap, provided with sufficient tolerances. However, in most operating conditions, this distance does not correspond to the optimum gap dimension with regard to the efficiency of the turbomachine.
  • z. B. also uses a so-called hydraulic gap optimization, in which a thrust bearing is moved, wherein the gap is changed due to a conical shape of the housing. At the same time, however, all gaps are disadvantageously changed at the same time, wherein the gaps in the compressor area are simultaneously increased.
  • the invention has for its object to improve a turbomachine of the type mentioned with simple means to the effect that the efficiency of the turbomachine is increased.
  • the object is achieved by at least one sealing element, which is displaceable at least along the longitudinal direction of the turbomachine, so that at least the blade gap is variable with its gap dimension.
  • the blades are anchored with their blade root in a rotor and extend from their blade root with their blade tip towards a housing of the turbomachine.
  • the rotor can rotate about its axis of rotation or axis of rotation, so that the blade and the rotor can also be referred to as a rotating part of the turbomachine.
  • the vanes are anchored with their Leitschaufelfuß in an inner housing associated with the housing, wherein the inner housing may also be referred to as a vane carrier.
  • the vanes extend from their vane root with their vane tip toward the rotor.
  • the vane may also be referred to as a stationary component that does not rotate.
  • the blade tip is slightly spaced from the vane carrier so that the blade clearance is formed between the blade tip and the sealing surface formed by the vane carrier.
  • the vane tip is spaced from the rotor so that a vane gap is formed between the vane tip and the rotor.
  • the sealing element is assigned to the guide blade carrier, so that the blade gap can be changed with its gap dimension.
  • the sealing element of the blade tip is associated with the guide blade.
  • a corresponding counterpart preferably a cross-section conical counterpart is provided on the rotor.
  • the sealing element has an abutment side and a sealing side opposite thereto.
  • the sealing element is adapted with its sealing side of the respective configuration of the blade tip, wherein the sealing side seen in cross section with respect to the rotational or axis of rotation is preferably designed conical.
  • the sealing element is oriented with its sealing side to the respective blade tip.
  • the sealing element is oriented with its sealing side to the correspondingly associated side of the rotor shaft arranged on the counterpart.
  • turbomachines operate in different operating conditions, so that an optimal gap setting can be achieved that the sealing element is assigned a drive for axial adjustment.
  • the drive can be realized by mechanical, electrical or electro-magnetic or hydraulic systems, so that scratching in critical operating conditions can be avoided by the gap dimension is adjusted or increased in time. This also allows faster load changes of the turbomachine.
  • the sealing element is configured in each case as a separate annular segment and assigned as a separate component either the guide vane and / or the vane tip.
  • the column of individual stages can thus be advantageously changed by axially displaceable circular segments, which are each separately controllable or displaceable.
  • the sealing element is designed as a guide blade carrier, wherein the guide vane carrier is advantageously associated with a drive for axial adjustment.
  • the gap or gap dimensions of several successive stages of the turbomachine with a sealing element (vane carrier) can be adjusted or adjusted specifically or individually, with a real-time measurement of the column is required.
  • a stronger bevel of the respective blade tips directly affects a required displacement.
  • a radial change in diameter by the drive made available adjusting mechanism can be done.
  • the change in diameter refers in the context of the invention to a corresponding configuration of the guide blade carrier, in particular to the configuration of the blade tip associated sealing surface of the guide blade carrier, so that the gap is adjusted according to the direction of displacement.
  • the inventive design of the turbomachine in particular by the axially adjustable sealing element, ie the separate annular segment or the trained as a guide blade carrier sealing element, an active control or regulation of the gap dimension is provided.
  • This results in a gap optimization so that a higher efficiency of the turbomachine can be achieved by optimal gap dimensions with which loss mass flows (gap losses) can be minimized by the Verstellmechanismusses (sealing element, drive) can be selectively influenced or adjusted.
  • an optimum gap can be set in any operating state of the turbomachine. Furthermore erosion phenomena can be compensated.
  • the sealing element according to the invention or the gap optimization according to the invention can preferably be used at high-pressure, medium-pressure and low-pressure stages of steam turbines, wherein gap optimization is of course also possible with gas turbines or compressors.
  • FIG. 1 shows a turbomachine 1, which is shown in the embodiment shown in the embodiment of a steam turbine.
  • the turbomachine 1 has in its longitudinal direction (double arrow 2) following one behind the other at least one blade 3 and at least one vane 4, each with their blade tips 6, 7 spaced to a respective opposite sealing surface 8, 9, so that a blade gap 11 and a vane gap 12 is formed between the respective vane tips and the respective associated sealing surfaces 8, 9.
  • the rotor blades 3 are connected in the illustrated embodiment via wheel discs 13 with a rotor 14.
  • the rotor 14 is rotatably mounted and rotates about its axis of rotation 16, so that the rotor 14 can be referred to with the blades 3 as a rotating part.
  • the rotating part is accommodated in a housing 17, wherein the housing 17 is associated with an inner housing 18.
  • the inner housing 18 is referred to below as a vane carrier 18.
  • the vane 4 is anchored in the vane support 18, wherein the vane support 18 is designed as a rigid component.
  • the turbomachine 1 is designed mirror-inverted to a central axis X, so that only one side will be described below with reference to the central axis X.
  • the turbomachine 1 shown by way of example comprises three rotor blades 3, which are spaced apart in the longitudinal direction 2 of the turbomachine 1.
  • the turbomachine 1 may also have more or fewer blades 3.
  • the blades 3 are connected with their blade root 19 to the rotor 14, and extend with their blade tip 6 toward the guide blade carrier 18.
  • the blade tip 6 is spaced from the guide blade carrier 18, so that the blade gap 11 is formed.
  • the rotor blade tip 6 opposite surface of the vane support 18 forms the blade tip 6 associated sealing surface.
  • the spaced apart in the longitudinal direction 2 blades 3 have a different radial extent, so that the illustrated turbomachine 1 has three turbine stages.
  • the blade 3 closest to the center axis X has the smallest radial extent with respect to the blade 3 located on the outside of the center axis X.
  • the blade 3 closest to the central axis X may also be referred to as La-2, the following blade 3 being designated La-1 and the outer blade 3 being La-0. This corresponds to the usual designation, in which La-0 is always the farthest from the central axis X row.
  • the vane 4 is anchored with its Leitschaufelfuß in the vane support 18 and extends from the Leitschaufelfuß with its vane tip 7 in the direction of the rotor 14 and in the direction of the wheel disks 13th
  • the vane tips 7 are spaced from the rotor 14 and the wheel disc 13 so that the vane gap 12 is formed.
  • the turbomachine 1 is supplied in the illustrated embodiment, steam or a medium.
  • the vapor or the medium flows radially into the center region 20 in the turbomachine 1 and flows axially out of the turbomachine 1 after passing through the blade grid formed by the rotor blades 3 and guide vanes 4.
  • the resulting vapor or medium direction or flow direction is shown in FIG. 2 by means of the arrow 21.
  • the medium or the steam flows on the non-illustrated side opposite to the illustrated flow direction 21, that is, as shown for example from the central axis X in the direction of La-0. Therefore, the respective flow direction 21 could also be equated with the respective orientation of the longitudinal direction (double arrow) 2.
  • the steam or other flow medium can be both between the Blade tip 6 and the guide blade carrier 18 as well as between the vane tip 7 and the rotor 14 and the wheel discs 13 flow through, so that gap losses occur, leading to a reduction of technical work and thus to a lower efficiency of the turbomachine 1.
  • a sealing element 22 is provided, which is shown by way of example in FIG.
  • the sealing element 22 is displaceable back and forth along the longitudinal direction 2 of the turbomachine 1, so that in the embodiment shown in Figure 2, the blade gap 11 is variable with its gap.
  • the sealing element 22 is associated with the guide blade carrier 18 as a separate component and has an abutment side 23 and a sealing side 24 opposite thereto.
  • the sealing side 24 is configured in the illustrated embodiment with respect to the axis of rotation 16 in cross-section conical, wherein the opposite plant side 23 seen in cross-section is designed to be substantially rectilinear.
  • the sealing element 22 is oriented with its sealing side 24 in the direction of the blade tip 6, which is designed conically in accordance with the sealing side 24 in cross-section.
  • a recess 26 is made in the guide blade carrier 18.
  • the recess 26 is preferably rectangular in cross-section and open in the direction of the blade 3.
  • FIG. 2 shows a representation which is not true to scale, so that distorted size relationships arise, in particular between the recess 26 and the sealing element 22.
  • the recess 26 is configured such that the sealing element 22 can be received with an associated drive, so that the sealing element 22 is preferably located completely in the recess 26 with its drive in a rest position. Of course, the sealing element 22 in the rest position also one-sided protrude from the recess 26.
  • the drive is not shown in the selected representation in Figure 2, but can be realized by means of mechanical, electrical or electro-magnetic or hydraulic systems. The drive causes an axial displacement of the sealing element 22 along the longitudinal direction 2.
  • the sealing element 22 is in a first use position 27, wherein the sealing element 22 is shown in the first use position 27 with full strokes.
  • a second use position 28 is shown in dashed lines in FIG.
  • the sealing element 22 is displaced by means of the drive along the longitudinal direction 2 in the direction of the moving blade 3 or in the direction of its blade tip 6 and thus alters the blade gap 11 between the blade tip 6 and the guide blade carrier 18 or the sealing surface 8 formed by the guide blade carrier 18.
  • FIG. 2 shows only a detail from FIG. 1, the blades La-0 and La-1 with the guide blade Le-0 arranged between them being shown here.
  • the sealing element 22 is designed as a separate circular ring segment which can be displaced axially along the longitudinal direction 2 via the drive.
  • the sealing element 22 can be moved continuously by means of the drive in the direction of the rotor blade 3, so that the rotor blade gap 11 is largely minimized, but at least reduced. Scrubbing of the blades 3 is prevented.
  • the flow medium or the steam can no longer flow unused through the originally existing column 11,12, but follows the intended flow path or the intended steam or flow direction 21 through the blade grid.
  • gap losses are significantly reduced, whereby the efficiency of the turbomachine 1 is significantly increased.
  • the respective gap dimensions of the respective turbine stages may of course be different in their extent.
  • a sealing element 22 adapted to the respective gap dimension can be provided for each turbine stage. This is shown correspondingly in FIG. If one compares, for example, the sealing element 22, which is associated with the turbine stage La-0, with the sealing element 22, which is associated with the turbine stage La-1, then it will be noted that the respective sealing element 22 is adapted to the existing gap size by for the Turbine stage La-1, a smaller in cross-section sealing element 22 is provided as for the turbine stage La-0.
  • each turbine stage is separately adjustable with respect to the respective required gap dimensions, for example, to prevent tarnishing.
  • the drive can e.g. be connected to a control member, so that a fast control or adjustment of the respective operating conditions adapted gap dimension or faster load changes of the turbomachine 1 are possible.
  • the vane tip 7 In order to prevent the flow medium from flowing through the vane gap 12 and thus resulting in gap losses, it is of course also possible for the vane tip 7 to be assigned a corresponding sealing element 22 so that the vane gap 7 can be changed (FIG. 3).
  • This sealing element 22 would also have a drive, wherein the sealing element 22 would be arranged with its drive in an introduced in the guide vane 4 recess.
  • the guide vane tip 7 associated sealing element 22 also has a Plant side 23 and a sealing side 24, wherein the sealing side 24 is preferably oriented to the rotor 14.
  • the rotor 14 is associated with a corresponding counterpart 29, for example, a conical counterpart 29, seen in cross-section, which has a side 31 corresponding to the sealing side 24.
  • the sealing element 22 is configured, for example, as a separate annular segment, so that the same effect is achieved as previously described.
  • the sealing element 22 is designed as a vane carrier 18.
  • the vane support 18 would have a dual function. First, this would wear the vanes 4.
  • the guide blade carrier 18 as a sealing element, the gap dimensions active controlling or rules.
  • a drive for axial adjustment would be assigned to the guide blade carrier 18 so that the gap dimension can be influenced or adjusted by the axial adjustment of the guide blade carrier 18 along the longitudinal direction 2 so that gap losses are also reduced, as a result of which the efficiency of the turbomachine 1 is considerably increased could.
  • the separate sealing element 22 is arranged laterally relative to the central axis 20 with respect to the rotor blade gap 11.
  • the sealing element 22 is preferably infinitely displaced from the lateral position in the direction of the blade tip 6 or oriented away from it in the direction of the guide blade 4, depending on which gap dimension is required to avoid, for example, a tarnish for controlling or controlling the gap ,
  • the invention is therefore not on the embodiment shown in the figure 2 limited, but also includes equally effective embodiments in which a gap optimization to increase the efficiency of the turbomachine 1 can be achieved.
  • the invention could also be applied to shaft seals.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP05015779A 2005-07-20 2005-07-20 Diminution des pertes dues au jeu en bout d'aubes dans les turbomachines Withdrawn EP1746256A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05015779A EP1746256A1 (fr) 2005-07-20 2005-07-20 Diminution des pertes dues au jeu en bout d'aubes dans les turbomachines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05015779A EP1746256A1 (fr) 2005-07-20 2005-07-20 Diminution des pertes dues au jeu en bout d'aubes dans les turbomachines

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EP1746256A1 true EP1746256A1 (fr) 2007-01-24

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2206889A1 (fr) * 2009-01-13 2010-07-14 Siemens Aktiengesellschaft Procédé de réduction de jeu des extrémités des aubes par un rotor déplaçable et turbine à gaz associée
EP2597265A1 (fr) * 2011-11-28 2013-05-29 Siemens Aktiengesellschaft Aube directrice pour une turbomachine pouvant s'écouler de manière axiale
US8540487B2 (en) 2009-07-01 2013-09-24 Rolls-Royce Plc Actuatable seal for aerofoil blade tip
CN103388493A (zh) * 2012-05-10 2013-11-13 通用电气公司 内涡轮壳轴向移动
US8727709B2 (en) 2009-09-28 2014-05-20 Rolls-Royce Plc Casing component
EP3511526A1 (fr) * 2018-01-12 2019-07-17 United Technologies Corporation Dispositif d'étanchéité et moteurs à turbine à gaz

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3227418A (en) * 1963-11-04 1966-01-04 Gen Electric Variable clearance seal
GB2024336A (en) * 1978-05-30 1980-01-09 Rolls Royce Gas turbine rotor tip clearance control apparatus
US4863345A (en) * 1987-07-01 1989-09-05 Rolls-Royce Plc Turbine blade shroud structure
US5203673A (en) * 1992-01-21 1993-04-20 Westinghouse Electric Corp. Tip clearance control apparatus for a turbo-machine blade
US20020071763A1 (en) * 2000-12-07 2002-06-13 Herbert Brandl Device for setting the gap dimension for a turbomachine
US20020150469A1 (en) * 2001-03-23 2002-10-17 Hans-Thomas Bolms Turbine
US20020164246A1 (en) * 2001-04-12 2002-11-07 Christian Scholz Gas turbine with axially mutually displaceable guide parts
US20030012644A1 (en) * 2001-04-05 2003-01-16 Dodd Alec G. Gas turbine engine system

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3227418A (en) * 1963-11-04 1966-01-04 Gen Electric Variable clearance seal
GB2024336A (en) * 1978-05-30 1980-01-09 Rolls Royce Gas turbine rotor tip clearance control apparatus
US4863345A (en) * 1987-07-01 1989-09-05 Rolls-Royce Plc Turbine blade shroud structure
US5203673A (en) * 1992-01-21 1993-04-20 Westinghouse Electric Corp. Tip clearance control apparatus for a turbo-machine blade
US20020071763A1 (en) * 2000-12-07 2002-06-13 Herbert Brandl Device for setting the gap dimension for a turbomachine
US20020150469A1 (en) * 2001-03-23 2002-10-17 Hans-Thomas Bolms Turbine
US20030012644A1 (en) * 2001-04-05 2003-01-16 Dodd Alec G. Gas turbine engine system
US20020164246A1 (en) * 2001-04-12 2002-11-07 Christian Scholz Gas turbine with axially mutually displaceable guide parts

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2206889A1 (fr) * 2009-01-13 2010-07-14 Siemens Aktiengesellschaft Procédé de réduction de jeu des extrémités des aubes par un rotor déplaçable et turbine à gaz associée
US8540487B2 (en) 2009-07-01 2013-09-24 Rolls-Royce Plc Actuatable seal for aerofoil blade tip
US8727709B2 (en) 2009-09-28 2014-05-20 Rolls-Royce Plc Casing component
EP2597265A1 (fr) * 2011-11-28 2013-05-29 Siemens Aktiengesellschaft Aube directrice pour une turbomachine pouvant s'écouler de manière axiale
CN103388493A (zh) * 2012-05-10 2013-11-13 通用电气公司 内涡轮壳轴向移动
EP2662534A3 (fr) * 2012-05-10 2015-06-17 General Electric Company Systèm de contrôle de jeu pour une turbine et turbine associée
US9488062B2 (en) 2012-05-10 2016-11-08 General Electric Company Inner turbine shell axial movement
EP3511526A1 (fr) * 2018-01-12 2019-07-17 United Technologies Corporation Dispositif d'étanchéité et moteurs à turbine à gaz
US10760442B2 (en) 2018-01-12 2020-09-01 Raytheon Technologies Corporation Non-contact seal with angled land
EP4279770A3 (fr) * 2018-01-12 2024-02-21 RTX Corporation Dispositif d'étanchéité pour moteurs à turbine à gaz

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