EP1515000A1 - Aubage d'une turbomachine avec un carenage contouré - Google Patents

Aubage d'une turbomachine avec un carenage contouré Download PDF

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Publication number
EP1515000A1
EP1515000A1 EP03103323A EP03103323A EP1515000A1 EP 1515000 A1 EP1515000 A1 EP 1515000A1 EP 03103323 A EP03103323 A EP 03103323A EP 03103323 A EP03103323 A EP 03103323A EP 1515000 A1 EP1515000 A1 EP 1515000A1
Authority
EP
European Patent Office
Prior art keywords
recess
contouring
blades
shrouds
shroud
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.)
Granted
Application number
EP03103323A
Other languages
German (de)
English (en)
Other versions
EP1515000B1 (fr
Inventor
Ralf Dr. Greim
Said Dr. Havakechian
Axel Dr. Pfau
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP03103323.6A priority Critical patent/EP1515000B1/fr
Priority to US10/936,582 priority patent/US7320574B2/en
Publication of EP1515000A1 publication Critical patent/EP1515000A1/fr
Application granted granted Critical
Publication of EP1515000B1 publication Critical patent/EP1515000B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • 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

Definitions

  • the invention relates to a turbomachine whose blading shrouds has, and in particular cavities, in which protrude the shrouds.
  • the blading is for the purpose of containment of Vibrations with shrouds that ring all Connect blade tips of a row of blades. They will both at Blades as well as used on vanes.
  • To one Leakage flow, which flows past the shrouds as small as possible are in the machine inner housing as well as in the shaft recesses or Cavities formed into which the shrouds of the blades or the Protrude vanes.
  • the leakage flow will continue through Labyrinth seals in the cavities limited.
  • Such labyrinth seals are For example, in Figure 1 of this application is shown. She shows you one Detail of a turbomachine, in particular of a blade 1 and her adjacent vanes 2a, 2b.
  • the blade 1 is covered with a shroud. 3 provided in a recess or cavity 4 of the inner housing 5 of the Machine protrudes.
  • a corresponding shroud of a vane protrudes into a similar recess in the shaft.
  • a labyrinth seal arranged for the purpose of curbing Leakage flows, which are indicated by an arrow 6 and outside the Main or working flow 7 between shroud 3 of the blade 1 and Inner housing flows through, is in the cavity 4, a labyrinth seal arranged.
  • This seal consists primarily of a plurality of sealing strips 8, extending from the wall of the inner housing radially inward toward the shroud extend.
  • the shroud 3 with steps in radial Direction designed, the shroud over its circumference a constant Form has.
  • the leakage flow 6 flows through an inlet region into the Cavity 4, between the sealing strip and the shroud through and over a Exit area back to the main flow 7 of the turbomachine.
  • Entry and exit areas result in mixing operations between Leakage flow and main flow, which among other things the main and Disturb working flow and cause power losses.
  • US 4,662,820 to Sasada et al. discloses a labyrinth seal with a gradually designed shroud and several sealing strips.
  • the cavity, in which the shroud protrudes is through inserts 12, 12a or shapes 15,15b formed the inner housing wall.
  • the cavity has thereby in axial and / or radial direction of a changing shape, wherein their shape is constant in the circumferential direction.
  • the stakes serve to close the room reduce, through which a leakage current can flow and thereby the performance to increase the machine.
  • a turbomachine includes blades and vanes each secured in a row of blades to a shaft or inner casing, at least one blade row and at least one row of guide blades each being provided with a shroud.
  • the inner housing and the shaft have cavities into which the shrouds protrude.
  • the cavities, the shrouds or both the cavities and the shrouds have a contouring or a changing profile in the circumferential direction.
  • the contouring consists of periodically repeating elevations and depressions, which are thus uniformly distributed over the circumference and each of the same extent.
  • the contouring has a wavelength, that is a profile section, which repeats itself in the circumferential direction several times.
  • this wavelength is equal to a fraction of the circumferential length of the cavity wall, that is to say the circumferential length either along the inner housing wall or the shaft.
  • the wavelength is equal to a fraction of the circumferential length of this shroud. More specifically, the wavelength corresponds to the circumferential length of the cavity wall or the shroud divided by the simple number of blades or by an integer multiple of the number of blades in the blade row, which is adjacent to the cavity or which is associated with the shroud.
  • a erfingundsgem contouring causes a pressure field, which counteracts stationary and unsteady pressure fields, which would otherwise generate the losses.
  • These are pressure fields created by the presence of the blades together with the absence of vanes between the rows of blades by creating stagnation points at the leading blade edges and blade trailing edges.
  • These pressure fields not only act in the main flow field, but also in the region of the labyrinth in the case of the blade cover strip and in particular in the area of the leakage flow entry in the cavity and the leakage flow exit from the cavity.
  • the mixing operations between the main and leakage flow are reduced and thus also reduces the friction and mixing losses caused by the mixing operations.
  • the elevations or depressions of the respective cavity wall and / or the shroud are positioned such that the maxima of those pressure fields which are produced by the adjacent rows of blades are attenuated and the pressure minima between the rows of blades are compensated by increased pressure ,
  • the cavities are both cavities on the inner housing, in which protrude the shrouds of the vanes, as well as to cavities the shaft into which the shrouds of the blades protrude.
  • the Pressure ratios are comparable in both cases.
  • the wavelengths of the contours are matched to the pressure fields, which they compensate. More concretely are their wavelengths according to the Number of blades in a row of blades determined.
  • a contouring a cavity wall has a wavelength equal to the circumferential length of the Cavity divided by the number of blades or by an integer Many times the number of blades in the row of blades, the contouring Upstream or downstream is closest.
  • a contouring of a Deckbands it has a wavelength equal to the circumferential length of the cavity divided by the number of blades or by an integer multiple of the Number of blades in the row of blades that belongs to the shroud.
  • a first preferred embodiment of the invention is the Contouring on the axially extending walls of a cavity, wherein the Elevations and depressions of the contouring extend in the radial direction, that means radially inward or radially outward.
  • the contouring In the case of a shroud cavity in the Area of a blade is the contouring as elevations and depressions to understand the inner casing wall; in the case of a shroud cavity in Area of a vane is as elevations and depressions on the shaft to understand.
  • the contouring extends over the entrance area or over the exit area of the cavity or over both areas. Of the Entry area is the area of the recess in the flow direction up to first sealing strip, the exit area is the area of the recess the last sealing strip in the flow direction.
  • a contouring in the Entry area and / or the exit area is preferred, wherein in others Parting the cavity or in the entire cavity contouring as well is feasible.
  • a contouring in the inlet region of the cavity has a Wavelength, which is adjacent to the number of blades in the upstream lying blade row is tuned.
  • a contouring in the exit area of the Cavity has a wavelength that depends on the number of blades in the downstream is matched adjacent blade row.
  • a second preferred embodiment of the invention is the Contouring on the radially extending walls of a cavity, wherein the Elevations and depressions of the contour extend in the axial direction, the means in direction or opposite direction of the mainstream.
  • the wavelengths are determined analogously to the first embodiment of the invention. This means that the contour in the entrance area has a wavelength that corresponds to the Number of blades in the upstream row of blades is tuned, and a contour in the exit region of the cavity has a Wavelength, which is adjacent to the number of blades in the downstream lying blade row is tuned.
  • the shrouds are contoured, with the Elevations and depressions in the radial direction in and out extend.
  • the shrouds are both stationary and rotating parts with a provided according to the invention contour.
  • This contouring of the shroud additionally compensates for those pressure fields caused by the Blade row are generated, which belongs to the shroud. Accordingly, the Wavelength of such contouring on the number of blades in this Vane row matched.
  • the shroud side walls or - contoured front walls wherein the elevations and depressions in axial Extending direction, that is in the direction of the mainstream or in the Opposite direction.
  • both stationary and rotating parts are with provided a contour according to the invention.
  • the wavelengths of Contours are in turn tuned to the pressure fields that they balance, and are tuned to the number of blades of that row that the Heard coverband.
  • Variants of the invention have any combinations of the four mentioned Versions on, by which the effect of the pressure equalization is further increased.
  • a contour has an arbitrary, periodically repeating shape, the generates a pressure gradient.
  • a preferred shape is a waveform, such as for example, a sinusoidal shape.
  • Other possible shapes are step shapes like Box shapes, triangular shapes, sawtooth or sawtooth-like shapes.
  • the amplitude of the contouring ie the maximum extent of the Elevations and depressions starting from a midline between the Extreme points of the contour, is chosen so that the curvature of the contour is sufficiently pronounced to produce correspondingly high pressure gradients, which can balance the pressure fields.
  • FIG. 2 a shows the same section of a turbomachine as in FIG. 1.
  • the cavity 4 has contouring 10 and 11 here Cavity walls according to the first embodiment of the invention. They are located in this embodiment in the inlet region 12 and outlet region 13 the cavity 4.
  • the view shows a section through the contouring at the height their surveys.
  • the contouring is in the version shown here in Entry area equal to the contouring in the exit area of the cavity.
  • In further Designs can be the contouring in the entry area of those in the Differ exit area. This can be for example inclined Canal walls will be the case.
  • contours 10 and 11 are made of solid parts that differ from the original inner housing wall radially inwardly toward the shroud 3 out extend. They are by appropriate shaping of the inner housing as integral part of the inner housing wall or by post-processing of the cavity feasible by mounting insert rings. The use of insert rings also allows retrofitting an existing machine.
  • the shroud 3 has a contour with elevations 14 and 15 which extend in the radial direction to the contouring 10, 11 out.
  • the contouring 10 in the inlet region 12 compensates in the circumferential direction for the pressure fields of the blade row with blades 2a.
  • the contouring 11 in the exit region 13 compensates for the pressure fields of the blade row with blades 2b.
  • Figure 2b shows a view of the machine along its shaft axis in the direction of the main flow.
  • the blades 2a and the contouring 10 in the inlet region of the cavity in the circumferential direction are shown. They have a waveform with a wavelength L 1 equal to the total circumferential length divided by the number of blades 2a of the upstream blade row or the distance between two adjacent stator blades 2a.
  • the wavelength L 1 may also be equal to the circumferential length divided by an integer multiple of the mentioned number of blades, that is to say only half or a quarter of this size.
  • the contouring 11 in the exit region of the cavity has a wavelength corresponding to the number of blades 2b of the downstream blade row. Therefore, the wavelengths of contouring 10 and 11 may be different.
  • the wavelengths of the shroud contour 14 in the inlet region 12 and the shroud contour 15 in the exit region 13 are determined (analogously to the wavelengths of the contours 10 and 11) in accordance with the number of rotor blades 1.
  • the maxima of the elevations of the contouring 10 are in With respect to the upstream vanes 2a positioned to the Optimize pressure compensation as much as possible. Accordingly, in the exit area 13 the maxima of the elevations of the contour 11 with respect to the downstream lying guide vanes 2b positioned. (The positioning of the maxima and their amplitudes are described in more detail below using the example according to FIG. 3b shown.)
  • FIG. 3a shows a section of a Turbomachine according to Figures 1 and 2a, wherein like reference numerals are used for the same machine parts.
  • the second embodiment of Invention is a contouring on the radially extending wall of the Cavity 4 in the form of elevations and depressions 20 in the inlet region 12th and elevations and depressions 21 in the exit area 13
  • Contours 20 and 21 are in this example as an insert ring with realized wave-shaped contour, which is attached to the inner housing wall. Alternatively, they can also be an integral part of the cavity.
  • the end faces of the shroud 3 are also provided with a contouring 22 in the inlet region 12 and a contouring 23 in the outlet region 13. Again, these can be realized by integral shaping of the shroud or by mounting a correspondingly shaped and attached to the shroud ring.
  • FIG. 3b shows the waveform of the contouring 20-23 of FIG. 3a in the circumferential direction by projection of the cavity 4 onto a surface.
  • the wavelength L1 of the contour 20 at the radially extending cavity wall in the inlet region here is equal to the distance between two adjacent blades 2a of the upstream blade row or equal to the total circumference of the cavity divided by the number of blades.
  • the wavelength L2 of the contour 21 in the exit region of the cavity is equal to the distance between two adjacent blades 2b of the downstream row of blades. Accordingly, the wavelength L3 of the contours 22 and 23 at the shroud end faces is equal to the distance between two adjacent blades 1, to which the shroud belongs.
  • the largest survey of the waveforms of all contours are at the height of the blades, to which the contour is tuned.
  • the contours each have an amplitude A equal to the extent an elevation or depression is starting from a midline between Elevation and center line.
  • the amplitude is in a predetermined ratio to the original cavity height of the inlet region 12.
  • the amplitudes A of the Elevations and depressions on the shrouds are also in one predetermined ratio to the original axial distance between shroud and cavity wall.
  • Figure 4 shows another possible shape of the contour applied to the Cavity contour of Figure 3a.
  • a waveform owns the contour here a rounded sawtooth 20 ', 21', 22 ', 23', wherein the position of the Maxima of the sawtooth shape 20 'to the position of the blades 2a of the upstream adjacent blade row, those of the contour 21 'on the position of the blades 2b of the downstream row of blades, and those of the contour 22 'and 23' the position of the blades 1 are tuned.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP03103323.6A 2003-09-09 2003-09-09 Aubage d'une turbomachine avec un carenage contouré Expired - Lifetime EP1515000B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP03103323.6A EP1515000B1 (fr) 2003-09-09 2003-09-09 Aubage d'une turbomachine avec un carenage contouré
US10/936,582 US7320574B2 (en) 2003-09-09 2004-09-09 Turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03103323.6A EP1515000B1 (fr) 2003-09-09 2003-09-09 Aubage d'une turbomachine avec un carenage contouré

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EP1515000A1 true EP1515000A1 (fr) 2005-03-16
EP1515000B1 EP1515000B1 (fr) 2016-03-09

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US7481615B2 (en) * 2005-03-26 2009-01-27 Halla Climate Control Corp. Fan and shroud assembly
EP2031184A1 (fr) * 2007-08-31 2009-03-04 Siemens Aktiengesellschaft Dispositif de rupture de tourbillon pour turbomachine
EP2055902A1 (fr) * 2007-10-31 2009-05-06 Siemens Aktiengesellschaft Turbine de centrale thermique comprenant une aube mobile et un aube statorique
EP2136033A1 (fr) * 2007-03-29 2009-12-23 IHI Corporation Paroi de turbomachine et turbomachine
DE102009042857A1 (de) * 2009-09-24 2011-03-31 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine mit Deckband-Labyrinthdichtung
EP2607626A1 (fr) * 2011-12-20 2013-06-26 MTU Aero Engines GmbH Turbomachine et étage de turbomachine
EP2607625A1 (fr) * 2011-12-20 2013-06-26 MTU Aero Engines GmbH Turbomachine et étage de turbomachine
EP2770165A1 (fr) * 2013-02-20 2014-08-27 Siemens Aktiengesellschaft Joint doté de rayure, turbomachine équipée d'un tel joint et son procédé de fabrication
WO2014127954A1 (fr) * 2013-02-20 2014-08-28 Siemens Aktiengesellschaft Joint nervuré pour turbomoteur, turbomoteur et procédé de fabrication d'un joint nervuré pour turbomoteur
EP2937515A1 (fr) * 2010-03-23 2015-10-28 United Technologies Corporation Moteur à turbine à gaz doté d'une plateforme de pale de rotor contourée à surface non axisymétrique
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US9976433B2 (en) 2010-04-02 2018-05-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured rotor blade platform
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US10036266B2 (en) 2012-01-17 2018-07-31 United Technologies Corporation Method and apparatus for turbo-machine noise suppression
JP5643245B2 (ja) * 2012-02-27 2014-12-17 三菱日立パワーシステムズ株式会社 ターボ機械
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US8926283B2 (en) 2012-11-29 2015-01-06 Siemens Aktiengesellschaft Turbine blade angel wing with pumping features
WO2014115706A1 (fr) * 2013-01-23 2014-07-31 三菱重工業株式会社 Mécanisme d'étanchéité et machine tournante pourvue d'un mécanisme d'étanchéité
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US20160208823A1 (en) * 2015-01-19 2016-07-21 Hamilton Sundstrand Corporation Shrouded fan rotor
US20170211407A1 (en) * 2016-01-21 2017-07-27 General Electric Company Flow alignment devices to improve diffuser performance
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EP1067273A1 (fr) * 1999-07-06 2001-01-10 ROLLS-ROYCE plc Configuration d'une bande de recouvrement des aubes de turbine

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US3893782A (en) * 1974-03-20 1975-07-08 Westinghouse Electric Corp Turbine blade damping
DE2462465A1 (de) * 1974-03-21 1977-04-28 Maschf Augsburg Nuernberg Ag Einrichtung zum dynamischen stabilisieren des laeufers eines verdichters
JPS5669402A (en) * 1979-11-09 1981-06-10 Hitachi Ltd Structure of blade train with shroud
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EP1067273A1 (fr) * 1999-07-06 2001-01-10 ROLLS-ROYCE plc Configuration d'une bande de recouvrement des aubes de turbine

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US7481615B2 (en) * 2005-03-26 2009-01-27 Halla Climate Control Corp. Fan and shroud assembly
US9051840B2 (en) 2007-03-29 2015-06-09 Ihi Corporation Wall of turbo machine and turbo machine
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US20050100439A1 (en) 2005-05-12
EP1515000B1 (fr) 2016-03-09
US7320574B2 (en) 2008-01-22

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