EP0799973B1 - Contour de paroi pour une turbomachine axiale - Google Patents

Contour de paroi pour une turbomachine axiale Download PDF

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Publication number
EP0799973B1
EP0799973B1 EP96810199A EP96810199A EP0799973B1 EP 0799973 B1 EP0799973 B1 EP 0799973B1 EP 96810199 A EP96810199 A EP 96810199A EP 96810199 A EP96810199 A EP 96810199A EP 0799973 B1 EP0799973 B1 EP 0799973B1
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EP
European Patent Office
Prior art keywords
blade
rotor
stator
stage
flow
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.)
Expired - Lifetime
Application number
EP96810199A
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German (de)
English (en)
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EP0799973A1 (fr
Inventor
Franz Kreitmeier
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Alstom SA
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Alstom SA
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 SA filed Critical Alstom SA
Priority to EP96810199A priority Critical patent/EP0799973B1/fr
Priority to DE59609405T priority patent/DE59609405D1/de
Priority to US08/818,978 priority patent/US5791873A/en
Priority to JP08249797A priority patent/JP4180131B2/ja
Publication of EP0799973A1 publication Critical patent/EP0799973A1/fr
Application granted granted Critical
Publication of EP0799973B1 publication Critical patent/EP0799973B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • 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
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • the invention relates to a multi-stage blading axially flowed turbomachine. It affects in particular the design of the channel contour in the bladed area and is applicable for blades with tip seal or those with cover plate or cover band seal.
  • the stator-side waveform can be formed in that the contour in the area of the guide blade root is oriented towards the machine longitudinal axis and in the area of the blade tip is directed away from the machine longitudinal axis. Accordingly, the waveform on the rotor side is then formed in that the contour in the area of the guide vane tip is oriented toward the machine longitudinal axis and in the area of the blade root is directed away from the machine longitudinal axis. According to an older proposal discussed in DE 579989 C, a reduction in the gap losses while at the same time improving the guidance of the fluid working medium is achieved by the arrangement of curved guide plates with an inclination that changes between the guide and barrel rows.
  • GB 2075130 A relates to a generic solution for designing the flow path in a compressor section of a gas turbine engine.
  • the stator-side and rotor-side walls of the flow path are equipped with such a contour, which is intended to shift the load distribution of the rotor blades in the direction of the blade height by causing the flow to follow this channel contour without tearing.
  • the redistribution of the aerodynamic load should result in an increase in the stage efficiency.
  • the channel walls in the area of the blade roots have an incline with respect to the machine longitudinal axis, whereas in the areas with respect to the blade tips they run parallel to the machine longitudinal axis.
  • the flow-limiting walls form a kink angle in each case in the distance between the guide vane row and the rotor blade row.
  • the invention is based, with a blading the task to create a channel contour of the type mentioned at the beginning, in which the step efficiency is achieved through geometric measures as well as the step load can be increased.
  • this object is achieved in that the rotor-side and / or stator-side flow-limiting wall of the flowed channel directly at the outlet of the blades is provided with a kink angle, which is so is dimensioned that the outflow from the blades is homogenized with respect to total pressure and outflow angle and that this wall at least approximately in the entrance area of the Guide blades of the following stage with a counter-kink angle is provided.
  • the re-inflow effect of the labyrinth mass flow in the main channel can be improved by the fact that in the Labyrinth exits between the blade cover plates that open in the axial gap a step and the guide vane feet the next stage and between the guide vane cover plates and the blade feet of the same one Stage in the general, prevailing in the blade channel Flow direction.
  • the labyrinth chamber after the last sealing gap is also reduced to additional losses to avoid.
  • FIG. 1 are the first 3, each from a guide row Le and a row of runs La existing stages of low-pressure blading shown.
  • the one with her feet 21 in turns of the rotor 9 used blades La1, La2 and La3 are provided with cover plates 16 at their blade ends.
  • the radially outer contours of the cover plates depend on Running row geometrically differently graded. Under education of labyrinths 15 they seal with their steps against sealing strips, which are arranged in the stator 9 in a suitable manner are.
  • the feet 13 in the stator 8 used guide blades Le1, Le2 and Le3 are on their Provide blade ends with cover plates 20.
  • the radially inner The contours of the cover plates are geometrical depending on the guide row graded differently. Forming labyrinths 19 seal with their steps against sealing strips, which in the Rotor 9 are arranged in a suitable manner. Between the first and second stages in the stator 8 is a radially outward directed removal 30 provided.
  • the flow through channel 50 has the conical as the starting position running outer contour 51 on the stator and the cylindrical running inner contour 52 on the rotor. However, neither is mandatory. Regardless of the actual course of the walls in any case, the outer flow-limiting contour 10 in the area of the airfoil through those facing the canal Cover plate 16 of the blades La1, La2, La3 and in Area of the guide vane through the facing the channel Base plate 13 of the guide blades Le1, Le2, Le3 formed.
  • the inner flow-limiting contour becomes the same 11 of the flowed channel in the area of the rotor blade through the base plate 21 of the rotor blades facing the channel La1, La2, La3 and in the area of the guide blade through the cover plate 20 of the guide blades facing the channel Be1, Be2, Be3 formed.
  • the channel 50 is now on the stator and / or executed on the rotor with a bent contour, wherein the contour is created as follows:
  • This kink angle is dimensioned so that the outflow from the blades is homogenized with respect to total pressure and outflow angle. in the For example, this means that both stator side and also the angles A and AA shown on the rotor side as positive To be defined.
  • the bent wall parts run radially to the outside, i.e. they are of the type not shown Machine axis directed away.
  • the choice of the articulation angle is based on the following considerations: There is a divergent at the outlet of the blades Current in front, possibly with counter-spin on the hub and co-spin on the cylinder. At least the flow points in the radial a much higher energy than in the outer zone radially inner zone, which is in the form of much higher Total pressures manifested in the radially outer zone.
  • the idea behind the articulation angle is now to be as small as possible Total pressure and outflow angle inhomogeneity over the blade height to achieve.
  • the radial equation equation teaches that this is primarily about the curvature of the meridian the streamlines can be reached. So this must be primary are influenced by adjusting the articulation angle.
  • a clean guidance of the flow at the blade outlet is difficult, however.
  • the axial gap 26 for the labyrinth outlet 42 and downstream the base plate 21 is usually the axial gap 23 for the entrance to the labyrinth 41. Remedy here the measure that, on the one hand, the one provided with the articulation angle A.
  • Wall 10 at the outlet of the blade as an extension 17 of the cover plate 16 is formed.
  • the other is with wall with the kink angle AA at the outlet of the rotor blade formed as an extension 22 of the base plate 21.
  • she extends into the axial gap 23 between extended Blade base plate and following guide blade cover plate 20.
  • the area of the blade cover plate extremely important outflow of harmful cross-flow effects protected.
  • the wall with the counter-bend angle B is now outside in the foot area of the downstream guide blade Le2, Be3 then radially inwards at the counter-angle guided. In addition, it is at the vane exit provided with an extension 14.
  • the radially inward Course is chosen so that the resulting flow-restricting Wall, which is between the extended guide vane root and subsequent blade cover plate 16 through the axial gap 18 is interrupted, at least approximately in the blade entry level of this subsequent stage an intersection P with the original straight channel contour 51 has. From the drawing it can be seen that the Extension 14 with the original channel contour 51, which on the side of the cover plate 16 facing the channel of the following Blade prevails, again one outwards opening positive angle. Expediently this kink also relocated to the center of the axial gap 18. The consequence of this is a reduction in pressure at the inlet 40 of the labyrinth 15. This reduction in pressure at the entrance to the labyrinth causes like the pressure increase at the labyrinth outlet a reduction in the pressure drop across the sealing points.
  • the base plate 13 of the guide vane on the stator side is provided with the extension 14, the labyrinth entries 40 between the guide vane feet 13 and the blade cover plates 16 the same level contrary to the general one Direction of flow in the channel be directed obliquely. All that is required is the base plate of the guide vane on the outlet side and the cover band of the rotor blade on the inlet side can be configured accordingly. This inclination of the Inlet impedes the inflow to labyrinth 15.
  • the base plate 21 of the rotor blade on the rotor side is provided with the extension 22, can also the labyrinth entrances 41 between the blade feet 21 and the vane cover plates 20 of the following stage the general direction of flow in the channel become. All that is required is the base plate of the blade outlet side and the cover band of the guide vane can be configured accordingly on the entry side. This Inclination of the inlet makes the inflow more difficult Labyrinth 19th
  • the opening into the axial gap 26 runs on the outside Maze exit 42 between the blade cover plate 16 a step and the guide vane root 13 on it following stage in the general, prevailing in channel 50 Flow direction.
  • the labyrinth outlet 42 is radially like this kept tight as possible to avoid unnecessary dissipation.
  • the inside of the axial gap 25 runs opening maze outlet 43 between the guide vane cover plate 20 and the blade root 21 of the same Level sloping in the general, prevailing in channel 50 Flow direction.
  • the rotor section on the corresponding Provide elevations 44 which one allow flow-favorable exit.
  • the flow-limiting wall 31 of the stator immediately upstream of the guide vanes Le2 is part of the one with the counter-bend angle B. Wall trained.
  • the rotor side can be in the plane of the Tapping point 30, the flow-limiting wall 32 of the Rotor 9 immediately downstream of the blades La1 as wall provided with the articulation angle AA.
  • FIG. 2 A variant of this is shown in FIG. 2.
  • the rotor side is here in the level of the tapping point 30 Blade La1 with the extension 22 described above equipped while the cover plate 20 'of the downstream guide vane Le2 with an inlet-side extension 33 provided, which also the game with the counter kink angle BB includes.
  • FIG. 3 shows the application of the invention in high-pressure blading with cover plate seal in which the flowed through Channel 50 has only a very weak taper.
  • Two stages are shown, each with a leading row Le and one La series.
  • the functionally identical elements are the same Reference numerals as in Fig. 1 can be seen 3 kinks X, Y, Z both on the outside of the cylinder and inside the hub.
  • kinks X run the Walls 10 and 11 with the bend angles A and AA respectively; in the kinks Y with the opposite kink angles B and BB respectively.
  • the kinks Y and Z are again advantageous in the the respective middle of the gap. It can also be seen that the other measures described above such as the slope of the labyrinth entries and the unspecified flow-compliant formation of the labyrinth outlets such blading can be realized.
  • FIG. 4 shows the application of the invention to blading, in which the blade ends of the blades La1, La2, La3 with the tip against the flow-limiting walls 10 of the flow through channel 50 seal. Outside of bladed area these walls 10 through the channel-side inner wall of the stator is formed.
  • the one with the positive folding angle A provided wall at the blade outlet
  • the step under consideration runs in its longitudinal extent initially radially outwards in an opening sense.
  • the one with the negative counter bend angle B is on the stator side from the foot plates 13 facing the flow channel of the guide blades Le2, Le3, Le4 of the following stage. Subsequent to the wall section with a counter-bend angle the wall runs radially inwards so that it at least approximately in the plane of the blade entry of these following Level a common point P with the original one straight outer channel contour 51.
  • the one with the positive kink angle AA provided wall at the blade outlet of the The stage considered runs in its longitudinal extent initially radially outwards.
  • the wall provided with BB then runs at the counter-bend angle so that they are at least approximately in the plane of the Blade entry of this following stage a common Point PP with the original straight channel contour 52 having.
  • FIG. 5 shows the last 2 stages of the LP turbine shown in FIG. 1 with a variant of the channel contour.
  • the Counter-kink angles are introduced here by introducing curved ones Contours in the area of the guide vanes reduced. With these curved contours can also be a reduction of Plus pressure in P and an increase in minus pressure in PP achieve.
  • the invention is of course not based on those shown and described embodiments limited.
  • the new Idea can e.g. only on the stator or - in the case of cover plate blading - realized only after the series of runs if there are space problems, for example. she is basically applicable to all turbomachinery.
  • Both previous examples assumed that total pressure increases from the hub to the cylinder.
  • the total pressure curve can be different. What is decisive in any case is that by arranging correct dimensioned and directed kink angles in the meridian contour after the impellers the total pressure curve as well the flow angle curve can be influenced positively, where positive stands for homogenization.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (13)

  1. Aubage multiétagé d'une turbomachine traversée axialement, présentant un canal traversé (50) avec une paroi (10) côté stator limitant l'écoulement et une paroi (11) côté rotor limitant l'écoulement, qui présentent par rapport à l'axe longitudinal de la machine des inclinaisons variables et qui forment sur la distance entre les aubes fixes (Le1, Le2,...) et les aubes mobiles (La1, La2,...) un angle de pli (A, AA), caractérisé en ce que la paroi (10) côté stator et/ou la paroi (11) côté rotor limitant l'écoulement du canal traversé (50) sont (est) pourvue(s), immédiatement à la sortie des aubes mobiles (La1, La2, La3), d'un angle de pli (A, AA) qui est dimensionné de telle façon que l'écoulement à partir des aubes mobiles (La1, La2, La3) soit homogénéisé en ce qui concerne la pression totale et l'angle d'écoulement et en ce que cette paroi (10) et/ou cette paroi (11) sont (est) pourvue(s) au moins approximativement dans la zone d'entrée des aubes fixes (Le2, Le3) de l'étage suivant d'un angle de pli opposé (B, BB).
  2. Aubage multiétagé selon la revendication 1, dans lequel les extrémités d'aube des aubes mobiles (La1, La2, La3) forment avec leur pointe une étanchéité par rapport aux parois limitant l'écoulement du canal traversé (50), caractérisé en ce que la paroi pourvue d'un angle de pli opposé (B) est formée côté stator par les plaques de base (13) des aubes fixes (Le2, Le3, Le4) de l'étage suivant, tournées vers le canal traversé et s'étend selon l'angle de pli opposé de façon à présenter du moins approximativement dans le plan de l'entrée d'aube mobile de cet étage suivant un point commun (P) avec le contour (51) de canal extérieur rectiligne original.
  3. Aubage multiétage selon la revendication 2, dans lequel les extrémités d'aube des aubes fixes (Le2, Le3, Le4) forment avec la pointe une étanchéité par rapport aux parois limitant l'écoulement du canal traversé, caractérisé en ce que
    la paroi (11) pourvue de l'angle de pli (AA) et de l'angle de pli opposé (BB) est formée côté rotor par la surface du rotor
    la paroi pourvue de l'angle de pli (AA) à la sortie d'aube mobile de l'étage considéré s'étend dans son étendue longitudinale d'abord radialement vers l'extérieur
    et la paroi pourvue de l'angle de pli opposé (BB) s'étend selon l'angle de pli opposé de façon à présenter au moins approximativement dans le plan de l'entrée d'aube mobile de cet étage suivant un point commun (PP) avec le contour (52) de canal rectiligne original.
  4. Aubage multiétagé selon la revendication 1, dans lequel les extrémités d'aube des aubes mobiles (La1, La2, La3) forment une étanchéité par rapport au stator (8) via une plaque de recouvrement (16) pourvue de labyrinthes (15), le contour limitant l'écoulement du canal traversé étant formé dans la zone du corps d'aube mobile par la plaque de recouvrement (16) tournée vers le canal des aubes mobiles (La1, La2, La3) et dans la zone du corps d'aube fixe par la plaque de base (13) tournée vers le canal des aubes fixes (Le1, Le2, Le3) caractérisé en ce que la paroi (10) pourvue de l'angle de pli (A) à la sortie de l'aube mobile est conformée en tant que prolongement (17) de la plaque de recouvrement (16).
  5. Aubage multiétagé selon la revendication 4, caractérisé en ce que la paroi pourvue de l'angle de pli opposé (B) dans la zone de base de l'aube fixe (Le2, Le3) située en aval s'étend suivant l'angle de pli opposé à nouveau radialement vers l'intérieur, et en ce qu'elle est pourvue à la sortie d'aube fixe d'un prolongement (14) de sorte que la paroi résultante limitant l'écoulement qui est interrompue entre la base d'aube fixe prolongée et la plaque de recouvrement consécutive d'aube mobile (16) par une fente axiale présente au moins approximativement dans le plan de l'entrée d'aube mobile de cet étage suivant un point commun (P) avec le contour (51) de canal rectiligne original.
  6. Aubage multiétagé selon la revendication 4, dans lequel des endroits de soutirage (30) orientés au moins approximativement radialement sont disposés dans le stator dans la zone entre les aubes mobiles d'un étage et les aubes fixes de l'étage suivant celui-ci, caractérisé en ce que la paroi (31) du stator limitant l'écoulement immédiatement en amont des aubes fixes est conformée en tant que partie de la paroi pourvue de l'angle de pli opposé (B).
  7. Aubage multiétagé selon la revendication 1, dans lequel les extrémités d'aube des aubes fixes (Le2, Le3) forment une étanchéité par rapport au rotor (9) via une plaque de recouvrement (20) pourvue de labyrinthes (19), le contour du canal traversé limitant l'écoulement étant formé dans la zone du corps d'aube mobile par la plaque de base (21) des aubes mobiles (La1, La2, La3) tournée vers le canal et dans la zone du corps d'aube fixe par la plaque de recouvrement (20) des aubes fixes (Le2, Le3) tournée vers le canal, caractérisé en ce que la paroi pourvue de l'angle de pli (AA) à la sortie de l'aube mobile est conformée en tant que prolongement (22) de la plaque de base (21) et s'étend jusque dans la fente axiale (23) entre la plaque de base prolongée de l'aube mobile et la plaque de recouvrement (20) de l'aube fixe située en aval.
  8. Aubage multiétage selon la revendication 7, caractérisé en ce que la paroi pourvue de l'angle de pli opposé (BB) dans sa zone d'entrée dans la plaque de recouvrement (20) de l'aube fixe située en aval s'étend à nouveau radialement vers l'intérieur suivant l'angle de pli opposé, et en ce qu'elle est pourvue d'un prolongement (24) à la sortie d'aube fixe, de sorte que la paroi résultante limitant l'écoulement, qui est interrompue entre la plaque allongée de recouvrement d'aube fixe et la plaque de base d'aube mobile (21) suivant celle-ci par une fente axiale (25) présente au moins approximativement dans le plan de l'entrée d'aube mobile de cet étage suivant un point commun (PP) avec le contour (52) de canal rectiligne original.
  9. Aubage multiétagé selon la revendication 6, caractérisé en ce que la paroi limitant l'écoulement (32) du rotor (9) immédiatement en aval des aubes mobiles est conformée côté rotor dans le plan de l'endroit de soutirage (30) en tant que paroi pourvue de l'angle de pli (AA).
  10. Aubage multiétagé selon les revendications 6 et 7, caractérisé en ce que la plaque de recouvrement (20') de l'aube fixe située en aval est pourvue côté rotor dans le plan de l'endroit de soutirage (30) d'un prolongement (33) côté entrée.
  11. Aubage multiétagé selon les revendications 5 et 7, caractérisé en ce que les entrées de labyrinthe (40, 41) entre les bases d'aube fixe (13) et les plaques de recouvrement d'aube mobile (16) d'un même étage ainsi qu'entre les bases d'aube mobile (21) d'un étage et les plaques de recouvrement d'aube fixe (20) de l'étage suivant s'étendent de façon inclinée et opposée au sens d'écoulement général dans le canal.
  12. Aubage multiétagé selon les revendications 5 et 8, caractérisé en ce que les sorties de labyrinthe (42, 43) débouchant dans la fente axiale (26, 25) entre les plaques de recouvrement d'aube mobile (16) d'un étage et les bases d'aube fixe (13) de l'étage suivant celui-ci ainsi qu'entre les plaques de recouvrement d'aube fixe (20) et les bases d'aube mobile (21) d'un même étage s'étendent dans le sens d'écoulement général régnant dans le canal (50).
  13. Aubage multiétagé selon la revendication 12, caractérisé en ce que les sorties de labyrinthe (42, 43) sont étranglées.
EP96810199A 1996-04-01 1996-04-01 Contour de paroi pour une turbomachine axiale Expired - Lifetime EP0799973B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP96810199A EP0799973B1 (fr) 1996-04-01 1996-04-01 Contour de paroi pour une turbomachine axiale
DE59609405T DE59609405D1 (de) 1996-04-01 1996-04-01 Wandkontur für eine axiale Strömungsmaschine
US08/818,978 US5791873A (en) 1996-04-01 1997-03-14 Multi-stage blade system
JP08249797A JP4180131B2 (ja) 1996-04-01 1997-04-01 多段式の翼構造

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP96810199A EP0799973B1 (fr) 1996-04-01 1996-04-01 Contour de paroi pour une turbomachine axiale

Publications (2)

Publication Number Publication Date
EP0799973A1 EP0799973A1 (fr) 1997-10-08
EP0799973B1 true EP0799973B1 (fr) 2002-07-03

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EP96810199A Expired - Lifetime EP0799973B1 (fr) 1996-04-01 1996-04-01 Contour de paroi pour une turbomachine axiale

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US (1) US5791873A (fr)
EP (1) EP0799973B1 (fr)
JP (1) JP4180131B2 (fr)
DE (1) DE59609405D1 (fr)

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EP0799973A1 (fr) 1997-10-08
DE59609405D1 (de) 2002-08-08
US5791873A (en) 1998-08-11
JP4180131B2 (ja) 2008-11-12
JPH108910A (ja) 1998-01-13

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