EP2294285A2 - Grille d'aubes pour une turbomachine et turbomachine comportant une telle grille - Google Patents

Grille d'aubes pour une turbomachine et turbomachine comportant une telle grille

Info

Publication number
EP2294285A2
EP2294285A2 EP09771999A EP09771999A EP2294285A2 EP 2294285 A2 EP2294285 A2 EP 2294285A2 EP 09771999 A EP09771999 A EP 09771999A EP 09771999 A EP09771999 A EP 09771999A EP 2294285 A2 EP2294285 A2 EP 2294285A2
Authority
EP
European Patent Office
Prior art keywords
blade
chord length
range
leading edge
distance
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Withdrawn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
EP09771999A
Other languages
German (de)
English (en)
Inventor
Günter Neumann
Jörg GATZKE
Ulrich Harbecke
Marc Andre Schwarz
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.)
MAN Energy Solutions SE
Original Assignee
MAN Diesel and Turbo SE
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=41256100&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP2294285(A2) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by MAN Diesel and Turbo SE filed Critical MAN Diesel and Turbo SE
Publication of EP2294285A2 publication Critical patent/EP2294285A2/fr
Withdrawn legal-status Critical Current

Links

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

Definitions

  • the invention relates to a blade grid for a turbomachine, in particular a steam turbine, with a plurality of profiled blades, in particular profiled blades, with a suction side, a pressure side, a skeleton line, a blade leading edge and a blade trailing edge, and a flow machine with such a blade grid.
  • turbomachines for example steam turbines, in particular compressible, fluid such as steam is deflected by one or more blade lattice and exerts forces on the blade grid. If this is movable, the fluid will drive this blade lattice while doing work.
  • fluid such as steam
  • optimum flow angles of an inflow of the blade leading edge to the circumferential direction are between 37 ° and 47 °, while outflow angles of the blade trailing edge are in one Range between 21 ° and 29 °, ie significantly different from the angle of attack.
  • Object of the present invention is to improve a blade grid for a flow machine.
  • a vane grille for a turbomachine for example, a steam or gas turbine, a compressor or the like, has a plurality of profiled vanes with a suction side, a pressure side, a skeleton line and a chord length, which are arranged side by side in the circumferential direction.
  • a skeleton line or (profile) center line or curvature line is in the usual way, preferably in the axial and curved or curved line, which has the same distance from the suction and pressure sides, ie lies exactly in the cross section between the pressure and suction sides Skeleton line
  • the connecting line of the circle centers inscribed in a profile Suction or pressure side are defined by the two circumferentially spaced outer surfaces of a blade cross-section, which is normal to the radial direction.
  • the blade grid can form, for example as a blade grid, a stage of a steam turbine.
  • the suction and pressure sides are preferably curved convexly in the direction of rotation of the turbine rotor, the suction side being in the direction of rotation in front of the pressure side, so that the fluid flowing through the turbine rotates the blade grid and thus the turbine rotor carrying it in the direction of rotation to do, for example, to drive a generator coupled to the turbine rotor.
  • the tendon of a blade in particular a tangent to its front and rear edge circle, may be inclined with respect to the axial direction.
  • Height and distance indications therefore refer to a bit tangent system whose one axis is parallel to the chord of the blade and whose other axis is tangential to the blade leading edge, unless otherwise stated, so that, for example, a height in cross section is defined as the distance from the chord.
  • the chord length accordingly denotes the distance between a downstream upstream blade edge in the flow direction of the fluid flowing through the fluid machine and a downstream blade trailing edge along the chord.
  • the invention is based on the finding that a blade lattice can be improved if the ratio of very specific blade heights, blade circles and / or blade curvatures to this chord length lies in specific, predetermined ranges.
  • already advantageous blade grids result if one or more blade heights, one or more blade circles or one or more blade curvatures, based on the chord length, lie in the ranges indicated below.
  • Particularly advantageous blade grids can be realized if one or more blade heights and blade circles, one or more blade heights and blade curvatures, one or more blade circles and blade curvatures, and in particular one or more blade heights, blade circles and blade curvatures lie in these regions.
  • information on blade heights, blade circles or blade curvatures subsequently always refers to at least one cross section normal to the radial direction. If the pressure and suction sides of the blades extend parallel to the radial direction, that is to say that each blade cross section is obtained by purely translational displacement of a cross section at the radially inner blade root in the radial direction, the data apply correspondingly to all cross sections. Equally, however, the pressure and / or suction side can also be curved in the radial direction, in which case one or more blade heights, blade circles and / or blade cambers in at least one cross section, for example at the blade root, at the blade head and / or in the radial blade center. relative to the chord length, should be in the ranges indicated below.
  • the suction side in cross section has a maximum height whose quotient with the chord length is in a range between 0.52 and 0.56, in particular between 0.53 and 0.55.
  • the pressure side in cross section has a maximum height whose quotient with the chord length is in a range between 0.18 and 0.22, in particular between 0.19 and 0.21.
  • the skeleton line in cross section has a maximum height whose quotient with the chord length is in a range between 0.35 and 0.39, in particular between 0.36 and 0.38.
  • the maximum heights of at least two of the suction side, the pressure side and the skeleton line are each in the specified ranges, more preferably from the suction side, pressure side and skeleton line.
  • the suction side preferably reaches its maximum height in a range between 0.39 and 0.43, in particular between 0.40 and 0.42, measured from the blade leading edge in the bit tangent system of the blade and with respect to the chord length.
  • a maximum extent in the cross section of a blade according to the invention is preferably about 0.40 to 0.42 times the chord length measured from the axially foremost point of the blade contour along the chord.
  • the pressure side preferably reaches its maximum height in a range between 0.50 and 0.54, in particular between 0.51 and 0.53, measured from the blade leading edge in the bit tangent system of the blade and with respect to the chord length.
  • the skeleton line preferably assumes its maximum height in a range between 0.41 and 0.45, in particular between 0.42 and 0.44, measured from the leading edge of the blade in the bit tangent system of the blade and relative to the chord length.
  • a maximum circle between the suction and pressure sides has a diameter in a range between 0.33 and 0.36 , in particular between 0.34 and 0.36, and / or a center distance, measured from the blade leading edge in the bit tangent system of the blade, in a range between 0.36 and 0.40, in particular between 0.37 and 0.39 and / or a height in cross section, measured from the chord, in a range between 0.34 and 0.38, in particular between 0.35 and 0.37, that a leading edge circle, in relation to the chord length, has a diameter in a range between 0.024 and 0.046, in particular between 0.025 and 0.045, and / or that a trailing edge circle, based on the chord length, has a diameter in a range between 0.099 and 0.021, in particular between 0, 01 and 0.02.
  • Circles can be inscribed between the pressure and suction sides, the centers of which lie on the skeleton line and which touch the pressure or suction side from inside. The largest of these circles forms the inscribed maximum circle.
  • the leading or trailing edge circle preferably define the leading or trailing edge of the blade such that the blade contour has a radius of curvature in the transition from the pressure and suction side, which corresponds to the radius of the leading or trailing edge circle.
  • the suction side be at a distance 0.1 times the chord length, measured from the blade leading edge in the bit tangent system of the blade Radius of curvature whose quotient with the chord length is in a range between 0.38 and 0.42, in particular between 0.39 and 0.41, and / or at an axial distance of 0.75 times the chord length has a radius of curvature, its quotient with the chord length in a rich between 0.82 and 0.86, in particular between 0.83 and 0.85, and / or that the pressure side at an axial distance of 0.15 times the chord length, measured from the blade leading edge in the bit tangent system of the blade, a Radius of curvature whose quotient with the chord length is in a range between 0.73 and 0.77, in particular between 0.74 and 0.76, and / or at an axial distance of 0.80 times the chord length has a radius of curvature,
  • the medium is advantageously deflected substantially only without being accelerated significantly, so that the pressure before and after the blade grid is only reduced to a lesser extent.
  • a low-separation boundary layer flow along the pressure and suction side and / or a greater flow deflection can be achieved, i. the impulse transferred from the fluid to the blade grid is increased.
  • the efficiency of the flow grid can be increased.
  • the deflection can be advantageous without significant pressure reduction.
  • Another advantage may be that a blade grid according to the invention is easier to produce, in particular can be milled without obstructive transfer operations.
  • the chord or a tangent to the blade leading and trailing edges encloses a so-called stagger angle with the circumferential direction, which is in a range between 73 ° and 83 °, in particular between 74 ° and 82 °, which also differs from conventional stagger angles advantageous effect on the efficiency.
  • a pitch ratio of a distance to the axial direction of parallel tangents on suction sides in the circumferential direction of adjacent blades to the chord length may be in a range of 0.70 to 0.79, more preferably 0.71 to 0.78 height. If the circumferential extent of the profile is smaller than the pitch, no rhomboid foot shapes or platforms are required, resulting in especially advantageous in terms of vorzuhaltendem tool and material inventory.
  • the number of blades at the same chord length can be increased by about 20%.
  • a turbomachine according to the present invention advantageously steeper inflow and outflow angles of an inflow of the blade leading edge to the axial direction can be realized, which in particular can lie in a range between 26 ° and 38 °, preferably between 27 ° and 37 °.
  • advantageously flows with a larger swirl can be processed before the blading.
  • the pressure peaks in the leading edge region can be reduced.
  • Fig. 1 a blade of a blade grid according to an embodiment of the present invention in a perspective view
  • Fig. 2 the blade of Figure 1 in a cross section H-Il normal to the radial direction with characteristic blade heights and - circles in Bitangentensystem.
  • Fig. 3 the blade of Figure 1 in Figure 2 corresponding representation with characteristic blade curvatures.
  • Fig. 4 two circumferentially adjacent blades of the blade blade of FIG. 1 in a corresponding cross-sectional view.
  • Fig. 1 shows a profiled blade 1 of a blade grid according to an embodiment of the present invention with a three-lobated plug foot.
  • For orientation tion are the radial direction r, the circumferential direction U and the axial direction a drawn.
  • FIG. 2 shows this blade in a cross section U-II normal to the radial direction r (see Fig. 1) with characteristic blade heights and circles in Bitangen- tensystem whose axes with the axial or circumferential direction in each case explained in more detail below staggering angle ß s include.
  • a first axis (from left to right in FIG. 2) of the bitangent system, to which the following dimensions refer, is parallel to a chord 5 of the blade 1, ie tangential to a leading and trailing edge circle 3, 4, a second axis / from bottom to top in Fig. 2) tangential to the leading edge.
  • the other, not shown blades are identical in their dimensions.
  • the blade 1 has a front suction side SS (upper in Fig. 1) in the rotational direction, a pressure side DS in the rotational direction DS, and a skeleton line Sk having the same distance at each point from the suction and pressure sides, i.e., the same distance. lies in cross section exactly between the pressure and suction side.
  • chord length s of the chord 5 between a blade leading edge and a blade trailing edge is 60 mm. Since the excellent blade circles, heights and curves explained below have according to the invention predetermined conditions with this chord length, the chord length s in FIGS. 2 and 3 is normalized to "1".
  • the suction side SS has in cross section a maximum height fss from the chord 5, measured in the bit tangent system, whose quotient fss / s with the chord length s is 0.54.
  • the pressure side DS has in cross-section a maximum heightyogs whose quotient f D s / s with the chord s length is 0.20.
  • the skeleton line Sk has in cross-section a maximum height fsk whose ratio fs k / s with the chord length s is 0.37:
  • the suction side of SS has its maximum height f S s at a position X f ss, which, based on the chord length of s, is 0.41, measured along the chord tangent system 5 in the Bi- (from left to right in Fig. 2) from the blade leading edge. In other words, the ratio x fS s / s is 0.41.
  • the pressure side DS reaches its maximum height f ⁇ s in an axial position Xros, which, based on the chord length s, is 0.52.
  • the skeleton line Sk has its maximum height fs k in an axial position x f s k , which is 0.43 with respect to the chord length s.
  • a maximum circle 2 inscribed between the suction side and the pressure side has, in relation to the chord length s, a diameter D ma ⁇ / s of 0.35, its center from the blade leading edge along the chord 5 in the bitmap system a distance Xomax / s of 0.38, of the tendon 5 a height fxomax ts of 0.36.
  • the leading edge circle 3 has, with respect to the chord length s, the diameter D 0 / s 0.035, a trailing edge circle 4 a diameter D 9 / s of 0.015:
  • a quotient RKSSOJS / s with the chord length s of a radius of curvature Rkssojs is 0.84.
  • the quotient RRDSO.IS / s the one radius of curvature Rk D so.tä in a distance X R koso.i ⁇ of 0.15 times the chord length s, measured from the blade leading edge along the chord 5, with the chord length s, 0.75, is a quotient RkDso. ⁇ o / s of a radius of curvature RKDSO.BO at an axial distance XRKDSO.8O of 0.80 times the chord length s 0.56.
  • chord 5 and a tangent to Schaufelvorder- and trailing edge closes with the circumferential direction U a staggering angle ßs, which is registered in Fig. 4 and 78 °.
  • a division ratio t / s of a distance t (see Fig. 4) of axially parallel tangents on suction sides SS in the circumferential direction of adjacent blades to the chord length s is 0.74.
  • An angle of incidence ßi in Fig. 4 indicated by an arrow flow of the blade leading edge to the circumferential direction is 32 °, a corresponding outflow angle ß ⁇ 25 °.

Landscapes

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

Abstract

Grille d'aubes pour une turbomachine, en particulier pour une turbine à vapeur, qui comporte une pluralité d'aubes profilées, en particulier d'aubes mobiles profilées (1) comprenant un extrados (SS), un intrados (DS), un squelette de profil (Sk) et une longueur de corde (s) entre un bord d'attaque et un bord de fuite. Dans ladite grille, le diviseur étant la longueur de corde (s), le quotient se situe entre 0,53 et 0,55 pour une hauteur maximale (fSS) de l'extrados (SS), entre 0,19 et 0,21 pour une hauteur maximale (fDS) de l'intrados (DS), entre 0,36 et 0,38 pour une hauteur maximale (fsk) du squelette de profil (Sk), entre 0,34 et 0,36 pour un diamètre (Dmax / s) d'un cercle maximal inscrit entre le bord d'attaque et le bord de fuite, entre 0,37 et 0,39 pour l'écartement de son centre (xDmax/ s), entre 0,35 et 0,37 pour la hauteur de son centre, entre 0,025 et 0,045 pour un diamètre (De / s) d'un cercle de bord d'attaque (3), entre 0,01 et 0,02 pour un diamètre (Da / s) d'un cercle de bord de fuite, entre 0,39 et 0,41 pour un rayon de courbure de l'extrados (SS) à un écart (XRkSS0.1) équivalent à 0,1 fois la longueur de corde (s), entre 0,83 et 0,85 pour un rayon de courbure de l'extrados (SS) à un écart (XRkSS0.75) équivalent à 0,75 fois la longueur de corde (s), entre 0,74 et 0,76 pour un rayon de courbure de l'intrados (DS) à un écart (XRKD0.15) équivalent 0,15 fois la longueur de corde (s) et entre 0,55 et 0,57 pour un rayon de courbure de l'intrados (DS) à un écart (XRkDS0.80) équivalent à 0,80 fois la longueur de corde (s).
EP09771999A 2008-07-04 2009-06-24 Grille d'aubes pour une turbomachine et turbomachine comportant une telle grille Withdrawn EP2294285A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008031781.0A DE102008031781B4 (de) 2008-07-04 2008-07-04 Schaufelgitter für eine Strömungsmaschine und Strömungsmaschine mit einem solchen Schaufelgitter
PCT/DE2009/000876 WO2010000229A2 (fr) 2008-07-04 2009-06-24 Grille d'aubes pour une turbomachine et turbomachine comportant une telle grille

Publications (1)

Publication Number Publication Date
EP2294285A2 true EP2294285A2 (fr) 2011-03-16

Family

ID=41256100

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09771999A Withdrawn EP2294285A2 (fr) 2008-07-04 2009-06-24 Grille d'aubes pour une turbomachine et turbomachine comportant une telle grille

Country Status (5)

Country Link
EP (1) EP2294285A2 (fr)
JP (1) JP5478617B2 (fr)
CN (1) CN102084089B (fr)
DE (1) DE102008031781B4 (fr)
WO (1) WO2010000229A2 (fr)

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ES2796526T3 (es) 2010-11-30 2020-11-27 Mtu Aero Engines Gmbh Sistema de paletas para un motor de avión
CN110727995B (zh) * 2018-06-29 2023-09-22 中国航发商用航空发动机有限责任公司 叶片形状的构造方法、叶片以及计算机设备
CN113342314B (zh) * 2021-05-28 2023-08-18 西安交通大学 超临界二氧化碳工质轴流式透平设计系统及方法

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Also Published As

Publication number Publication date
DE102008031781A1 (de) 2010-01-07
WO2010000229A3 (fr) 2010-08-19
WO2010000229A2 (fr) 2010-01-07
JP5478617B2 (ja) 2014-04-23
CN102084089A (zh) 2011-06-01
DE102008031781B4 (de) 2020-06-10
JP2011524490A (ja) 2011-09-01
CN102084089B (zh) 2015-01-14

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