EP0064679B1 - Leitschaufeln für divergente Kanäle in Dampfturbinen - Google Patents

Leitschaufeln für divergente Kanäle in Dampfturbinen Download PDF

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Publication number
EP0064679B1
EP0064679B1 EP82103671A EP82103671A EP0064679B1 EP 0064679 B1 EP0064679 B1 EP 0064679B1 EP 82103671 A EP82103671 A EP 82103671A EP 82103671 A EP82103671 A EP 82103671A EP 0064679 B1 EP0064679 B1 EP 0064679B1
Authority
EP
European Patent Office
Prior art keywords
blades
ceiling
floor
blade
turbine
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
EP82103671A
Other languages
English (en)
French (fr)
Other versions
EP0064679A1 (de
Inventor
Raymond Bessay
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.)
Alstom SA
Original Assignee
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 AT82103671T priority Critical patent/ATE20119T1/de
Publication of EP0064679A1 publication Critical patent/EP0064679A1/de
Application granted granted Critical
Publication of EP0064679B1 publication Critical patent/EP0064679B1/de
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
    • 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
    • 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 present invention relates to a directional vane for divergent veins of a steam turbine, comprising vanes arranged between a floor and a diverging ceiling and the surfaces of the lower and upper surfaces being substantially orthogonal to the floor near the latter. and whose dawn generators are curved.
  • the term "generator" is used here for a line whose displacement parallel to itself generates the surface of the blade.
  • the surfaces of the upper surface and the lower surface of the blades consist of generators which are substantially rectilinear orthogonal to the floor and making an angle close to the angle 90 ° + O with the ceiling, O being the angle of divergence of the vein.
  • the invention aims to reduce losses due to the divergence of the veins. This object is achieved by blading as defined in the claim.
  • This turbine comprises a succession of fixed blades and mobile blades.
  • the director blade 1 of the top stage comprises vanes 2 arranged between a cylindrical floor 3 and a conical ceiling 4 at an angle 6 with the axis 00 'of the turbine.
  • This angle 6 is particularly important for the last stage of the low pressure part of the turbine. In addition, when it is desired to use terminal movable blades of great height, this divergence is accentuated.
  • the values of 8 at the right of the top stage directing vane are usually between 25 ° and 70 °.
  • FIG 2 there is shown a top view of the director vane 1 with two consecutive blades 2, 2 '.
  • the vein 3 is limited by the lower surface of the blade 2. the upper surface of the blade 2 'and by the ceiling and the floor.
  • the minimum distance ⁇ between the two neighboring blades 2, 2 ' starts from the ends a of the trailing edge of the blade 2 to a point b of the upper surface of the blade 2'.
  • the circle with center a and radius 8 is tangent at b to the upper surface of dawn 2 '.
  • this section has substantially the shape of a ring sector ai bi bs (ai, bi being on the floor and ace, bs on the ceiling) between the floor 3, the ceiling 4, the trailing edge of the blade 2 and the upper surface of the blade 2 '(see FIG. 3).
  • the minimum flow cross-section has the shape of a quadrilateral ai bi bs as (neglecting the curvatures of ai bi on the floor 3, and as bs on the ceiling 4) which essentially differs of the section shown in Figure 3 by the triangle as bs cs, bs cs being drawn parallel to ai bi (see Figure 4).
  • the angle ⁇ as b cs of the triangle as bs cs is all the more close to angle 8 the smaller the exit angle of the jet a 1S with the grid front.
  • Any cylindrical cut XY centered on the axis of the turbine such as X2 Y2 made at a height below the level bs, cs, meets the blades.
  • any cut XY such as X1 Y1 made on the blade portion between ace and cs cuts the blade 2 but no longer cuts the blade 2 '(see this cut in FIG. 5).
  • the flow passage section is determined on one side by the lower surface of the blade 2 and on the other side by the upper surface of the blade 2 'in a first part b' bo, then by the ceiling of bo to b ".
  • FIG 6 there is shown a blade of a conventional blading.
  • the surfaces of the upper and lower surfaces are orthogonal to the floor and make an angle 9 + 90 ° with the ceiling 4.
  • the successive profiles of the blades are joined by lines such as m, n, p, which are never very far from a straight line.
  • FIG. 7 A blade of a vane according to the invention is shown in FIG. 7.
  • the surfaces of the upper surface and the lower surface are orthogonal to the floor in the vicinity thereof.
  • the generators m, n, p are straight up to an intermediate profile 1 and then are curved enough so that the surfaces of the upper surface and the lower surface are also orthogonal to the ceiling.

Landscapes

  • 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. Leitbeschaufelung für divergierende Kanäle einer Dampfturbine mit Schaufeln (2, 2'), die zwischen einem Boden (3) und einer divergierenden Decke (4) angeordnet sind, und deren Innenflächen und Außenflächen im wesentlichen senkrecht zum Boden (3) in seiner Nähe liegen und deren Schaufelmantellinien (m, n, p) gekrümmt sind, dadurch gekennzeichnet, daß die Innenflächen und die Außenflächen in der Nähe der Decke (4) im wesentlichen senkrecht zur Decke (4) verlaufen. 9
EP82103671A 1981-05-05 1982-04-29 Leitschaufeln für divergente Kanäle in Dampfturbinen Expired EP0064679B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT82103671T ATE20119T1 (de) 1981-05-05 1982-04-29 Leitschaufeln fuer divergente kanaele in dampfturbinen.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8108884 1981-05-05
FR8108884A FR2505399A1 (fr) 1981-05-05 1981-05-05 Aubage directeur pour veines divergentes de turbine a vapeur

Publications (2)

Publication Number Publication Date
EP0064679A1 EP0064679A1 (de) 1982-11-17
EP0064679B1 true EP0064679B1 (de) 1986-05-28

Family

ID=9258069

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82103671A Expired EP0064679B1 (de) 1981-05-05 1982-04-29 Leitschaufeln für divergente Kanäle in Dampfturbinen

Country Status (7)

Country Link
US (1) US4470755A (de)
EP (1) EP0064679B1 (de)
JP (1) JPS57193703A (de)
AT (1) ATE20119T1 (de)
DE (1) DE3271339D1 (de)
FR (1) FR2505399A1 (de)
ZA (1) ZA823055B (de)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2523642A1 (fr) * 1982-03-19 1983-09-23 Alsthom Atlantique Aubage directeur pour veines divergentes de turbine a vapeur
GB2128687B (en) * 1982-10-13 1986-10-29 Rolls Royce Rotor or stator blade for an axial flow compressor
US4682935A (en) * 1983-12-12 1987-07-28 General Electric Company Bowed turbine blade
GB2164098B (en) * 1984-09-07 1988-12-07 Rolls Royce Improvements in or relating to aerofoil section members for turbine engines
JPS6244719A (ja) * 1985-08-23 1987-02-26 Alps Electric Co Ltd エレクトロクロミツク表示素子
US4826400A (en) * 1986-12-29 1989-05-02 General Electric Company Curvilinear turbine airfoil
FR2643940B1 (fr) * 1989-03-01 1991-05-17 Snecma Aube mobile de turbomachine a moment de pied compense
JP2753382B2 (ja) * 1990-09-17 1998-05-20 株式会社日立製作所 軸流タービン静翼装置及び軸流タービン
US5167489A (en) * 1991-04-15 1992-12-01 General Electric Company Forward swept rotor blade
GB9210421D0 (en) * 1992-05-15 1992-07-01 Gec Alsthom Ltd Turbine blade assembly
DE4228879A1 (de) * 1992-08-29 1994-03-03 Asea Brown Boveri Axialdurchströmte Turbine
DE59709447D1 (de) * 1997-11-17 2003-04-10 Alstom Switzerland Ltd Endstufe für axialdurchströmte Turbine
US6299412B1 (en) * 1999-12-06 2001-10-09 General Electric Company Bowed compressor airfoil
US6682301B2 (en) 2001-10-05 2004-01-27 General Electric Company Reduced shock transonic airfoil
KR100587571B1 (ko) * 2001-10-10 2006-06-08 가부시끼가이샤 히다치 세이사꾸쇼 터빈날개
US6554564B1 (en) * 2001-11-14 2003-04-29 United Technologies Corporation Reduced noise fan exit guide vane configuration for turbofan engines
US7740347B2 (en) 2002-12-02 2010-06-22 Silverbrook Research Pty Ltd Ink usage tracking in a cartridge for a mobile device
JP4045993B2 (ja) * 2003-03-28 2008-02-13 株式会社Ｉｈｉ ファン静翼、航空エンジン用ファン、及び航空エンジン
US7547187B2 (en) * 2005-03-31 2009-06-16 Hitachi, Ltd. Axial turbine
DE112007000717A5 (de) * 2006-03-31 2009-02-19 Alstom Technology Ltd. Leitschaufel für eine Strömungsmaschine, insbesondere für eine Dampfturbine
US7806653B2 (en) * 2006-12-22 2010-10-05 General Electric Company Gas turbine engines including multi-curve stator vanes and methods of assembling the same
GB2471152B (en) * 2009-06-17 2016-08-10 Dresser-Rand Company Use of bowed nozzle vanes to reduce acoustic signature
US9011084B2 (en) * 2010-09-28 2015-04-21 Mitsubishi Hitachi Power Systems, Ltd. Steam turbine stator vane and steam turbine using the same
US11629599B2 (en) * 2019-11-26 2023-04-18 General Electric Company Turbomachine nozzle with an airfoil having a curvilinear trailing edge
US11566530B2 (en) * 2019-11-26 2023-01-31 General Electric Company Turbomachine nozzle with an airfoil having a circular trailing edge

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA503596A (en) * 1954-06-08 A. V. Roe Canada Limited Blading for compressors, turbines and the like
US850200A (en) * 1905-11-28 1907-04-16 Gen Electric Turbine bucket and nozzle.
US1062258A (en) * 1911-07-07 1913-05-20 Georg Arthur Schlotter Propeller.
US1966787A (en) * 1931-03-27 1934-07-17 Sulzer Ag Cooling fan for vehicles driven by internal combustion engines
FR759166A (fr) * 1932-10-25 1934-01-30 Perfectionnements aux aubes directrices des ventilateurs et semblables
US2029813A (en) * 1932-10-25 1936-02-04 Mey Rene De Guiding vane for fans or the like
US2154313A (en) * 1938-04-01 1939-04-11 Gen Electric Directing vane
US2795373A (en) * 1950-03-03 1957-06-11 Rolls Royce Guide vane assemblies in annular fluid ducts
FR1037610A (fr) * 1950-03-03 1953-09-22 Rolls Royce Perfectionnements aux ensembles d'aubes de guidage pour conduits annulaires de fluide
US3316714A (en) * 1963-06-20 1967-05-02 Rolls Royce Gas turbine engine combustion equipment
GB1116580A (en) * 1965-11-17 1968-06-06 Bristol Siddeley Engines Ltd Stator blade assemblies for axial-flow turbine engines
GB1284341A (en) * 1970-01-28 1972-08-09 Rolls Royce Fluid flow machine
US3989406A (en) * 1974-11-26 1976-11-02 Bolt Beranek And Newman, Inc. Method of and apparatus for preventing leading edge shocks and shock-related noise in transonic and supersonic rotor blades and the like
US4075500A (en) * 1975-08-13 1978-02-21 Grumman Aerospace Corporation Variable stator, diffuser augmented wind turbine electrical generation system
US4131387A (en) * 1976-02-27 1978-12-26 General Electric Company Curved blade turbomachinery noise reduction
SE410331B (sv) * 1976-09-24 1979-10-08 Kronogard Sven Olof Statorkonstruktion avsedd att placeras nedstroms en separat arbetsturbinrotor
JPS5445405A (en) * 1977-09-16 1979-04-10 Hitachi Ltd Turbine cascade

Also Published As

Publication number Publication date
EP0064679A1 (de) 1982-11-17
FR2505399B1 (de) 1985-05-03
JPS57193703A (en) 1982-11-29
DE3271339D1 (en) 1986-07-03
ATE20119T1 (de) 1986-06-15
FR2505399A1 (fr) 1982-11-12
ZA823055B (en) 1983-03-30
US4470755A (en) 1984-09-11

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