EP0023025B1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP0023025B1
EP0023025B1 EP19800104153 EP80104153A EP0023025B1 EP 0023025 B1 EP0023025 B1 EP 0023025B1 EP 19800104153 EP19800104153 EP 19800104153 EP 80104153 A EP80104153 A EP 80104153A EP 0023025 B1 EP0023025 B1 EP 0023025B1
Authority
EP
European Patent Office
Prior art keywords
blade
flow direction
flow
direction changing
point
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
Application number
EP19800104153
Other languages
German (de)
English (en)
Other versions
EP0023025A1 (fr
Inventor
Takeshi Sato
Akira Uenishi
Norio Yasugahira
Katsukuni Hisano
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.)
Hitachi Ltd
Original Assignee
Hitachi Ltd
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 Hitachi Ltd filed Critical Hitachi Ltd
Publication of EP0023025A1 publication Critical patent/EP0023025A1/fr
Application granted granted Critical
Publication of EP0023025B1 publication Critical patent/EP0023025B1/fr
Expired 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
    • 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
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/301—Cross-sectional characteristics

Definitions

  • the present invention relates to a turbine blade of axial flow fluid machines according to the first part of the claim.
  • Turbine blade profiles are in general designed to obtain a desired inlet angle, a desired outlet angle and a desired blade width or chord length, but hydrodynamical conditions in the flow passage between the adjacent blades are not enough taken into consideration.
  • the boundary layers are formed over the blade surfaces due to the viscosity of the fluid and flow past the outlet of the flow passage, resulting in the lack of velocity of the fluid at the downstream of the outlet.
  • the degree of the lack of the velocity of the fluid at the downstream of the outlet determines the performance of the blade profile.
  • the most important factor which must be taken into consideration in design of turbine blade profiles is the thickness of the boundary layer at the outlet of the flow passage between the adjacent blades. In general, the thinner the boundary layer at the outlet, the higher the performance becomes.
  • the turbine blade as defined in the claim has the advantage that the fluid flow at the outlet end of the flow channel has a more uniform velocity over the flow section of the channel than in the prior art turbine blades.
  • the advantage results from the fact that the acceleration of the income fluid flow is substantially completed upstream of the flow direction changing point and that the relative long channel portion downstream of the flow direction changing point has a substantially uniform cross section and a wide curvature. Especially this wide curvature of the channel portion downstream of the changing point causes a reducing of the velocity difference between the fluid flow on the back or suction wall surface and the fluid flow on the front or pressure wall surface in a flow channel.
  • Said uniformed velocity distribution has advantageous effects to the form and the development of the boundary layers and to the reducing of turbulences behind the trailing edges of the blade outlets.
  • a line H is first drawn which is in parallel with the axis of blade array (that is, the direction in which the blades 10 are mounted in a circular array) and which passes the point of intersection J between a first line F inclined to the axis of the blade array, at an inlet angle 01 and a third line inclined to a fourth line in parallel with the above-mentioned axis at an outlet angle a 2 .
  • the position of this line H corresponds to the point P at which the fluid flow is deflected in direction within the passage between the back surface 10b of the turbine blade 10 and the front surface 10a of the adjacent blade 10.
  • the inlet width of this passage i.e.
  • the pitch of the blade array is denoted by t and the outlet width by S.
  • the passage width Sp is the diameter of a circle around the point P at which the center line A of the flow passage intersects the line H.
  • the distance 1. between the straight line H which passes the flow direction changing point P and the outlet of the blade is greater than one half of the chord length C of the blade 10.
  • the width of the flow passage is drastically reduced at the upstream portion from the inlet to the flow direction changing point P (from A to P in Fig. 1) while the decrease in width is gradual in the downstream portion (from P to B in Fig. 1).
  • the radius of curvature R N of the upstream portion of the back surface 10b (from the inlet to the straight line H in Fig. 1) is made smaller than 0.15 of the chord length C'.
  • the radius of curvature R NO of the downstream portion of the back surface 10b (from the straight line H to the outlet in Fig. 1) is expressed by R NO /C>5.0.
  • the radius of curvature R NP of the downstream portion of the front surface 10a is expressed by R NP /C>1.3.
  • the diameter Sp of a circle around said flow direction changing point P contacting the front surface (10a) of one blade (10) and the back surface (10b) of the next blade (10) is less than about 0.4 times as small as the blade pitch (1).
  • Said diameter S P of said circle is 0.9 ⁇ S/Sp ⁇ 1.0, whereby S is the smallest width at the outlet end of the flow channel.
  • the curvature of the back surface upstream of the straight line H is made greater while the curvatures of the downstream portions of the front and back surfaces are made smaller or made substantially zero, so that an optimum acceleration of flow can be ensured and the acceleration of the fluid flow can be substantially completed before the fluid reaches the flow direction changing point P.
  • the increase in thickness of the upstream portion of the blade 10 results from the fact that the radius of curvature R N of the upstream portion of the back surface 10b is reduced.
  • the acceleration of the fluid can be substantially completed before the fluid reaches the flow direction changing point P without changing the inlet angle ⁇ 1 .
  • the acceleration stabilizes the boundary layers and decreases their thickness.
  • the fluid flow is deflected along the concave front surface 10a and the convex back surface 10b so that satisfactory boundary layers are formed even after passing the flow direction changing point P. As a consequence, a uniform velocity distribution can be attained in the flow at the downstream of the outlet.
  • the thickness d m of the blade is given by the following dimensionless expression or parameter: where d m is the distance from the point M, at which the straight line Q is tangent to the back surface 10b, to the point at which a stragiht line constructed at the point M at right angle to the straight line Q intersects the front surface 10a of the blade.
  • Fig. 2 shows the flow in the passage between the blades is expressed in terms of the pressure acting on the blade surfaces.
  • the pressure acting on the back surface of the blade has a high pressure drop ⁇ Ps in the upstream portion of the flow passage from the inlet to the point P at which the flow is deflected. Since the pressure drop ⁇ Ps approaches AP which is a pressure drop in the overall portion of the flow passage, the stabilized boundary layers can be formed.
  • AP is a pressure drop in the overall portion of the flow passage
  • AP is a pressure drop in the overall portion of the flow passage
  • the stabilized boundary layers can be formed.
  • S in Fig. 1 a very gentle increase in pressure is observed.
  • a sudden pressure rise or the decrease in velocity
  • Fig. 3 Shown in Fig. 3 are the velocity distribution V, displacement thickness ⁇ and momentum thickness ⁇ on the back surface 10b of the blade.
  • the thicknesses 6 and ⁇ are the measures in determining the thickness of the boundary layer and are calculated (according to "TN D-5681", published by NASA, May 1970) based upon the pressure distribution shown in Fig. 2.
  • Fig. 4 is shown the relationship between the blade profile loss coefficient e and the inlet and outlet angles a 1 and a 2 .
  • the present invention provides a blade profile with a mininum loss and a higher degree of performance.
  • the acceleration is almost completed before the flow direction changing point so that the boundary layers can be highly stabilized and consequently the velocity enhancing and high performance blade profile can be provided.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (1)

  1. Aube de turbine pour une machine fluidique à écoulement axial comportant une partie d'entrée possédant une épaisseur accrue de telle sorte que le fluide est accéléré à une vitesse élevée dans la partie d'entrée du canal d'écoulement et conserve cette vitesse élevée après le changement de sa direction d'écoulement, caractérisée par la combinaison des caractéristiques suivantes:
    a) un point P de changement de direction d'écoulement, défini par l'intersection de la ligne neutre APB du canal d'écoulement et d'une droite H parallèle à la droite de liaison des extrémités de sortie des aubes (10) et passant par le point d'intersection J des prolongements des droites définissant l'angle d'entrée α1 et l'angle de sortie α2 de l'aube (10), ledit point P de changement de direction d'écoulement étant situé à une distance lax de ladite droite de liaison, qui est supérieure à 0,5 fois la longueur C de la corde axiale de l'aube (10),
    b) le rayon de courbure RN de la partie de la surface arriére (10b) de l'aube en amont du point P de changement de direction de l'écoulement est inférieur à 0,15 fois la longueur C de la corde de l'aube (10),
    c) le rayon de courbure RNO de la partie de la surface arrière (10b) de l'aube en aval du point P de changement de direction de l'écoulement est supérieur à 5 fois la longueur C de la corde de l'aube (10),
    d) le rayon de courbure RNP de la partie de la surface avant (10a) de l'aube en aval de point P de changement de direction de l'écoulement est supérieur à 1,3 fois la longueur C de la corde de l'aube (10),
    e) le diamètre Sp d'un cercle entourant le point P de changement de direction de l'écoulement et en contact avec la surface avant (10a) d'une aube (10) et la surface arrière (10b) de l'aube (10) suivante est inférieur à environ 0,4 fois le pas (t) des aubes,
    f) ledit diamètre Sp dudit cercle est tel que l'on a 0,9<S/Sp<1,0, S étant la largeur la plus faible au niveau de l'extrémité de sortie du canal d'écoulement.
EP19800104153 1979-07-18 1980-07-16 Aube de turbine Expired EP0023025B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP90426/79 1979-07-18
JP9042679A JPS5614802A (en) 1979-07-18 1979-07-18 Profile of accelerating blade

Publications (2)

Publication Number Publication Date
EP0023025A1 EP0023025A1 (fr) 1981-01-28
EP0023025B1 true EP0023025B1 (fr) 1989-03-15

Family

ID=13998272

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19800104153 Expired EP0023025B1 (fr) 1979-07-18 1980-07-16 Aube de turbine

Country Status (3)

Country Link
EP (1) EP0023025B1 (fr)
JP (1) JPS5614802A (fr)
DE (1) DE3072147D1 (fr)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5829603U (ja) * 1981-08-21 1983-02-25 芝浦メカトロニクス株式会社 保線機械の車体横振装置
DE3201436C1 (de) * 1982-01-19 1983-04-21 Kraftwerk Union AG, 4330 Mülheim Turbomaschinenschaufel
JPS60250102A (ja) * 1984-05-25 1985-12-10 芝浦メカトロニクス株式会社 コンパクタ付きバラストスイ−パ
JPS61122302A (ja) * 1984-11-20 1986-06-10 芝浦メカトロニクス株式会社 位置調整機能を備えたコンパクタ装置
JP2516962B2 (ja) * 1987-03-18 1996-07-24 三菱電機株式会社 マスタ−スライスｌｓｉ
US5172210A (en) * 1987-03-18 1992-12-15 Mitsubishi Denki Kabushiki Kaisha Master slice integrated circuit having a memory region
US4900230A (en) * 1989-04-27 1990-02-13 Westinghouse Electric Corp. Low pressure end blade for a low pressure steam turbine
EP1915514B2 (fr) 2005-07-15 2018-10-31 Vestas Wind Systems A/S Aube d'eolienne
DE102008031781B4 (de) * 2008-07-04 2020-06-10 Man Energy Solutions Se Schaufelgitter für eine Strömungsmaschine und Strömungsmaschine mit einem solchen Schaufelgitter
JP6396093B2 (ja) 2014-06-26 2018-09-26 三菱重工業株式会社 タービン動翼列、タービン段落及び軸流タービン
US11015993B2 (en) 2019-10-02 2021-05-25 Cnh Industrial America Llc System and method for wirelessly monitoring the operational status of tools of an agricultural implement

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE334235A (fr) * 1925-05-27 1926-05-21
GB550393A (en) * 1941-05-21 1943-01-06 Oscar Anton Wiberg Blade rim for steam or gas turbines
DE1272305B (de) * 1959-01-27 1968-07-11 Siemens Ag Beschaufelung fuer Dampfturbinen
US3475108A (en) * 1968-02-14 1969-10-28 Siemens Ag Blade structure for turbines
JPS5237526B2 (fr) * 1973-04-20 1977-09-22

Also Published As

Publication number Publication date
EP0023025A1 (fr) 1981-01-28
DE3072147D1 (en) 1989-04-20
JPS5614802A (en) 1981-02-13
JPS6259203B2 (fr) 1987-12-10

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