EP1012445B2 - Aube pour une turbomachine - Google Patents

Aube pour une turbomachine Download PDF

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Publication number
EP1012445B2
EP1012445B2 EP98951240A EP98951240A EP1012445B2 EP 1012445 B2 EP1012445 B2 EP 1012445B2 EP 98951240 A EP98951240 A EP 98951240A EP 98951240 A EP98951240 A EP 98951240A EP 1012445 B2 EP1012445 B2 EP 1012445B2
Authority
EP
European Patent Office
Prior art keywords
blade
cross
vane
end region
another
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
EP98951240A
Other languages
German (de)
English (en)
Other versions
EP1012445B1 (fr
EP1012445A1 (fr
Inventor
Mathias Deckers
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
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Application filed by Siemens AG filed Critical Siemens AG
Publication of EP1012445A1 publication Critical patent/EP1012445A1/fr
Publication of EP1012445B1 publication Critical patent/EP1012445B1/fr
Application granted granted Critical
Publication of EP1012445B2 publication Critical patent/EP1012445B2/fr
Anticipated expiration legal-status Critical
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations

Definitions

  • the invention relates to a blade for a turbomachine, wherein the blade is directed along a blade axis and along this blade axis has adisproportionateend Scheme, a Kopfend Scheme and disposed therebetween a central region and a cross-sectional area perpendicular to the blade axis.
  • the EP-A-0 704 602 deals with the design of a turbine vane in an intermediate stator of a steam turbine directed along a turbine axis.
  • the blade extends along a radially directed blade axis and has a pressure side and a suction side as well as an entry edge and an exit edge.
  • the blade along the radial direction is configured such that the pressure side has a convex curvature behavior from a blade root area to a blade head area opposite the blade root area along the blade axis.
  • the convex curvature of the pressure side of the airfoil is achieved in the radial direction by a rotating displacement of the cross sections around the straight trailing edge.
  • the curvature is achieved in that, in the case of radially successive, spaced-apart cross-sectional profiles, the setting angle (bitangential angle) with respect to the turbine axis is varied in a parabolic manner by a corresponding rotation of the cross-sectional profiles around the fixed common exit edge.
  • the channel width for the steam can thus be reduced in the blade head area and in the blade root area and increased in an intermediate blade center area. This results in a displacement of a portion of the vapor mass flow away from the two lossy edge regions of the turbine vane.
  • Such cylindrical blades have parallel to the blade axis pressure and suction sides and thus have neither a twist nor an inclination.
  • so-called twisted turbine blades are described, which have over their height an increasing rotation and a changing blade profile.
  • an axial turbine such as a steam turbine or a gas turbine having a plurality of circumferentially spaced vanes.
  • the vanes used are wound over their height and have a changing inlet angle.
  • the change in the inlet angle increases from a certain height measured from the blade root (root) continuously in the region of the tip of the vane over-linear.
  • the distortion also increases continuously over the height of the vane.
  • the cross-sectional profile of the vane changes continuously from the blade root to the blade tip, with the vane becoming increasingly slender.
  • the size and shape of the vane are taken into account.
  • inlet guide vanes are arranged along the gas flow path in front of the blades and vanes. These inlet or inlet guide vanes have a curved cross-section, except in the region of the walls.
  • the central blade part with the curved cross section goes in each wall area in a smooth and continuously curved surface in the non-curved cross-sectional profile in the wall areas over. Over the height of the inlet guide vane thus continuously change the cross-sectional profiles of the airfoil.
  • the inlet angle remains constant over the entire height of the inlet guide vane.
  • a vane ring for an axial turbine is described with vanes, wherein the guide vanes are arranged between an inner and an outer ring and the profile thickness of the airfoil changes in proportion to the blade pitch.
  • the change in the blade profile is made over the height of the vane in that there is no change in the shape of the leading edge (pressure side), but the projection on the trailing edge gradually increases in size over the height while increasing the thickness of the vane.
  • the profile change is in this case carried out so that the thickness of the vane increases while their chord length remains the same.
  • Such a vane ring is applicable to steam turbines, gas turbines and compressors.
  • Turbine blades according to the preamble of claim 1 are known from the article " Development of three-dimensional stage viscous time marching method for short height stages "by G. Singh, PJ Walker, BR Haller, in:” VDI Reports No. 1185, 1995, pp. 157-179 , known.
  • the object of the invention is to provide a blade with low flow losses for a turbomachine.
  • the object directed to a blade for a turbomachine is achieved by such a blade which is directed along a blade axis and along this blade axis has a predominantlyend Scheme, a Kopfend Scheme and between a central region and a vertical axis to the blade profile cross-sectional profile, wherein axially in the direction of the blade axis spaced apart cross-sectional profiles from the prescribedend Scheme to the central region and from the Kopfend Scheme to the central region in the same direction are offset from each other and wherein in thepreparingend Scheme and / or Kopfend Scheme axially spaced cross-sectional profiles are rotated by a differential angle to each other, wherein the blade is cylindrical in the central region.
  • the blade is cylindrical in the central region.
  • the sides (pressure side, suction side) of the blade thus run parallel to the blade axis.
  • the axially spaced-apart cross-sectional areas in the pleasingend Scheme and the head end region are rotated rectified towards the central region.
  • the rotation is withdrawn.
  • the blade is preferably designed for placement in a blade ring, which has a circumferential direction, wherein the cross-sectional direction coincides locally with the circumferential direction.
  • a bend takes place in the circumferential direction with a simultaneous rotation (angle adaptation) in the end regions of the blade, whereby a reduction of flow losses and thus an increase in the efficiency of a turbomachine can be achieved.
  • an increase in the mechanical discharge energy at the same thermal energy use and on the other hand a reduction of the thermal energy input and thus the environmental impact of pollutant emissions at constant discharge energy compared to purely cylindrical or purely inclined or purely curved blades achieved.
  • the cross-sectional profiles are preferably included a rotation with respect to their centroid or with respect to the blade axis (if different, for example, by inhomogeneous mass distribution) rotated.
  • the rotational angle occurring in the following is referred to as a stagger angle and a rotation is performed as a stagger angle change.
  • the cross-sectional profile along the blade axis is preferably the same everywhere.
  • the cross-sectional profile does not change over the height of the blade.
  • the cross-sectional area of the cross-sectional profiles is constant.
  • the blade preferably has a combination of a circumferential deflection of the center of gravity of the cross-sectional profiles (bending in the circumferential direction) and a staggering of the cross-sectional profiles (without changing the profiling) in the head end and satisfiedend Scheme (hub and housing area).
  • the blade is preferably designed as a vane or blade of a steam turbine, in particular a high pressure or medium pressure steam turbine.
  • the blade preferably has a small length to width ratio, as is the case in particular for blades for a high-pressure steam turbine.
  • FIG. 1 shows a flow machine, a high-pressure steam turbine 11, in a longitudinal section, which is directed along a turbine axis 17.
  • the steam turbine 11 has a turbine shaft 20 directed along the turbine axis 17, which is surrounded by a turbine housing 18.
  • the steam turbine 11 has an inflow region 12 for action fluid, superheated steam, and an outflow region 13 for the superheated steam.
  • a blading region 14 is provided in the blading area 14.
  • guide vanes which are combined in the axial direction alternately one after the other in each case in a corresponding blade ring 21 follow 9 and Blades 8.
  • Each blade 8 and each vane 9 has along a blade axis 2 (see FIG.
  • the rotor blades 8 and / or guide vanes 9 closest to the inflow region 12 are each designed as a blade 1, which is inclined and twisted in the foot end region 3 and in the head end region 4.
  • Blades 8 closest to the outflow region 13 and guide vanes 9 are each designed as twisted blades 19 with an increasing rotation and changing cross-sectional profile over the blade axis 2.
  • In the blading region 14 axially between the inclined and twisted blades 1 and the twisted blades 19 are arranged purely cylindrical blades 16 whose suction and pressure sides are each parallel to the blade axis 2.
  • FIG. 2 shows a detail of a blade ring 21 in which blades 1 are arranged next to one another in the circumferential direction 6a.
  • the blade ring 21 is unwound along the circumferential direction 6a and shown with only two blades 1.
  • the circumferential direction 6 a corresponds to the circumference of the turbine shaft 20 in a section perpendicular to the turbine axis 17.
  • the main flow direction 22 of the steam flowing in the steam turbine 11 is perpendicular to the circumferential direction 6 a of the blade ring 21.
  • FIG. 3 shows, in a three-dimensional view, the blade leaf area 23 of a blade 1 directed along a blade axis 2.
  • the airfoil region 23 has a foot end region 3, a head end region 4 and a middle region 10 therebetween.
  • a shroud possibly following the head end region 4 is likewise not shown.
  • the turbine blade 1 is inclined in a cross-sectional direction 6, which preferably corresponds to the circumferential direction 6a of the blade ring 21, and rotated in the axial direction by a differential angle ⁇ (see FIGS. 4 and 5).
  • the in theticianend Scheme 3 to the central region 10 towards increasing rotation and increasing circumferential deflection corresponds to the same rotation and circumferential bend as in Kopfend Scheme 4.
  • the amount of backward rotation and backward displacement over the head end region 4 is preferably the same as the displacement and twist in the foot end region 3.
  • the circumferential bend herein means a displacement of the cross-sectional profile 5, 5a in the direction of a cross-sectional direction 6, which preferably corresponds to the circumferential direction 6a of a blade ring 21.
  • a rotation of the blade 1 is effected by a stagger angle change, i. a change of the angle ⁇ according to Figure 4 and Figure 5 by a rotation of the cross-sectional profile 5 about the blade axis 2, which preferably coincides with the gravity axis of the blade 1.
  • this likewise corresponds to a rotation about the centroid 7 (center of gravity 7) of the cross-section profile 5, 5a.
  • the cross-sectional profile 5, 5a, 5b is the same over the entire height of the airfoil region 23 for each cross-section, i. in particular that the cross-sectional shape and area are constant.
  • the cross-sectional profile 5b shown in FIG. 5 is rotated relative to the cross-sectional profile 5a shown in FIG. 4 by the difference angle ⁇ and shifted by the displacement value ⁇ U. This corresponds to a change of the stagger angle ⁇ to the value of the stagger angle ⁇ '(FIG. 5).
  • the edge losses i. the fluid mechanical losses in the vicinity of the turbine shaft and the turbine housing, can be up to about 30% of the total losses, a reduction of these edge losses due to the rotation and circumferential deflection of the blade in a steam turbine to an increase in efficiency.
  • the degree of rotation and circumferential deflection can be adapted in each case to the fluidic conditions in a steam turbine.
  • the central region is cylindrical.

Claims (6)

  1. Aube (1) pour une turbomachine (11) qui est dirigée le long d'un axe (2) d'aube et qui comprend une partie (3) d'extrémité d'empiétement et une partie (4) d'extrémité de tête, opposée à la partie (3) d'extrémité d'empiétement le long de l'axe (2) de l'aube, ainsi qu'une partie (10) médiane interposée entre elles et ayant un profil (5 ; 5a, 5b ; 15a, 15b) de section transversale, perpendiculaire à l'axe (2) de l'aube, des profils (5a, 5b) de section transversale, à distance les uns des autres axialement dans la direction de l'axe (2) de l'aube, étant mutuellement décalés par une translation dans une direction (6) de section transversale de la partie (4) de tête à la partie (3) médiane et des profils (15a, 15b) de section transversale à distance les uns des autres axialement, étant, décalés mutuellement, par une translation dans la même direction (6) de section transversale, de la partie (3) d'extrémité d'empiétement à la partie (10) médiane et des profils (15a, 15b ; 5a, 5b) de section transversale, à distance axialement les uns des autres, dans la partie (3) d'extrémité d'empiétement et/ou dans la partie (4) d'extrémité de tête, ont les uns par rapport aux autres une torsion d'un angle (Δβ) respectif de différence, caractérisée en ce que l'aube est cylindrique dans la partie médiane.
  2. Aube (1) suivant la revendication 1, dans laquelle des profils (5a, 5b ; 15a, 15b) de section transversale à distance axialement les uns des autres, ont une torsion respectivement dans la même direction, de la partie (3) d'extrémité d'empiétement et de la partie (4) d'extrémité de tête à la partie (10) médiane.
  3. Aube (1) suivant l'une des revendications précédentes, destinée à être disposée dans une couronne d'aubes ayant une direction (6a) périphérique, la direction (6) de section transversale coïncidant localement avec la direction (6a) périphérique.
  4. Aube (1) suivant l'une des revendications précédentes, dans laquelle les profils (5a, 5b ; 15a, 15b) de section transversale ont une torsion respectivement par rapport à leur centre (7) de gravité en surface.
  5. Aube (1) suivant l'une des revendications précédentes, dans laquelle le profil (5a, 5b ; 15a, 15b) de section transversale est le même partout le long de l'axe (2) de l'aube.
  6. Aube (1) suivant l'une des revendications précédentes, qui est réalisée en aube (9) directrice ou en aube (8) mobile d'une turbine (11) à vapeur.
EP98951240A 1997-09-08 1998-08-31 Aube pour une turbomachine Expired - Lifetime EP1012445B2 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19739318 1997-09-08
DE19739318 1997-09-08
PCT/DE1998/002556 WO1999013199A1 (fr) 1997-09-08 1998-08-31 Aube pour une turbomachine, et turbine a vapeur

Publications (3)

Publication Number Publication Date
EP1012445A1 EP1012445A1 (fr) 2000-06-28
EP1012445B1 EP1012445B1 (fr) 2002-10-02
EP1012445B2 true EP1012445B2 (fr) 2008-01-16

Family

ID=7841609

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98951240A Expired - Lifetime EP1012445B2 (fr) 1997-09-08 1998-08-31 Aube pour une turbomachine

Country Status (8)

Country Link
US (1) US6354798B1 (fr)
EP (1) EP1012445B2 (fr)
JP (1) JP4217000B2 (fr)
KR (1) KR20010023783A (fr)
CN (1) CN1100195C (fr)
AT (1) ATE225460T1 (fr)
DE (1) DE59805843D1 (fr)
WO (1) WO1999013199A1 (fr)

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EP1314859B1 (fr) * 2001-11-22 2006-08-02 Siemens Aktiengesellschaft Procédé de fabrication de turbines à vapeur
MXPA04009982A (es) 2002-04-11 2006-02-22 Richard A Haase Metodos, procesos, sistemas y aparatos con tecnologia de combustiion de agua, para la combustion de hidrogeno y oxigeno.
CA2426892C (fr) 2002-08-16 2011-10-25 The Fuel Genie Corporation Dispositif et methode changeant la vitesse angulaire d'un ecoulement d'air
US7262550B2 (en) * 2003-04-15 2007-08-28 Luminus Devices, Inc. Light emitting diode utilizing a physical pattern
EP1710397B1 (fr) * 2005-03-31 2014-06-11 Kabushiki Kaisha Toshiba Aube de guidage courbée
FR2903138B1 (fr) * 2006-06-28 2017-10-06 Snecma Aube mobile et disque de rotor de turbomachine, et dispositif d'attache d'une telle aube sur un tel disque
US8545170B2 (en) * 2009-10-27 2013-10-01 General Electric Company Turbo machine efficiency equalizer system
US8342009B2 (en) 2011-05-10 2013-01-01 General Electric Company Method for determining steampath efficiency of a steam turbine section with internal leakage
ITTO20111009A1 (it) * 2011-11-03 2013-05-04 Avio Spa Profilo aerodinamico di una turbina
US9032733B2 (en) 2013-04-04 2015-05-19 General Electric Company Turbomachine system with direct header steam injection, related control system and program product
CN107489461A (zh) * 2017-09-15 2017-12-19 哈尔滨汽轮机厂有限责任公司 一种用于汽轮机叶片的高效宽负荷叶型
RU191926U1 (ru) * 2019-02-28 2019-08-28 Публичное Акционерное Общество "Одк-Сатурн" Сопловой аппарат турбины
JP7264685B2 (ja) * 2019-03-26 2023-04-25 三菱重工航空エンジン株式会社 タービン静翼、及びタービン
CN113339325B (zh) * 2021-08-09 2022-01-07 中国航发上海商用航空发动机制造有限责任公司 用于压气机的进口级叶片组件及包含其的轴流压气机

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Also Published As

Publication number Publication date
DE59805843D1 (de) 2002-11-07
JP2001515983A (ja) 2001-09-25
EP1012445B1 (fr) 2002-10-02
CN1100195C (zh) 2003-01-29
WO1999013199A1 (fr) 1999-03-18
JP4217000B2 (ja) 2009-01-28
EP1012445A1 (fr) 2000-06-28
US6354798B1 (en) 2002-03-12
KR20010023783A (ko) 2001-03-26
ATE225460T1 (de) 2002-10-15
CN1269865A (zh) 2000-10-11

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