EP0520288B1 - Aube de turbine à flux subsonique - Google Patents

Aube de turbine à flux subsonique Download PDF

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Publication number
EP0520288B1
EP0520288B1 EP92110107A EP92110107A EP0520288B1 EP 0520288 B1 EP0520288 B1 EP 0520288B1 EP 92110107 A EP92110107 A EP 92110107A EP 92110107 A EP92110107 A EP 92110107A EP 0520288 B1 EP0520288 B1 EP 0520288B1
Authority
EP
European Patent Office
Prior art keywords
suction
trailing edge
profile contour
concave
contour
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
EP92110107A
Other languages
German (de)
English (en)
Other versions
EP0520288A1 (fr
Inventor
Martin Schönenberger
Said Havakechian
Nils Lannefors
Ulrich Steiger
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0520288A1 publication Critical patent/EP0520288A1/fr
Application granted granted Critical
Publication of EP0520288B1 publication Critical patent/EP0520288B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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 turbomachine blade for subsonic conditions with a profile contour which is convexly curved in the region of the front edge and over the major part of the suction side and with a profile contour which is concavely curved in the region of the pressure side, the entire profile contour having a continuous curve,
  • the profile contour of the known blades is usually either straight or slightly convex in the area of the suction-side trailing edge.
  • Other known ways of reducing the profile loss are to delay the laminar-turbulent reversal of the suction-side boundary layer as much as possible by means of suitable acceleration of the flow. This is based on the fact that a turbulent boundary layer is more lossy than a laminar boundary layer.
  • the invention now has the task of taking measures on the rear edge of a turbomachine blade of the type mentioned in order to keep the lack of impulse thickness as small as possible .
  • profile contour is concave in the suction-side trailing edge region. This measure can favorably influence the development of the boundary layer on the suction side.
  • the concave section extends from the rear edge over a length which essentially corresponds to the distance between two adjacent blades in the narrowest cross section.
  • the cylinder development can be viewed as a straight vane grille. It can be seen that it is a turbine blading for subsonic conditions with a continuous course of the entire profile contour.
  • Se denotes the chord of the blades, S their suction side and D their pressure side.
  • the ratio of the blade pitch T to the chord length Se is approximately 0.8.
  • the blades are staggered at an angle ⁇ of approx. 55 °.
  • the area of the front edge and the majority of the suction side are provided with a convexly curved profile contour.
  • the area of the pressure side has a concavely curved profile contour.
  • the narrowest cross-section Q to be flowed through by the working medium is measured at these conditions from the pressure-side rear edge of one blade to the convex blade back of the adjacent blade, regardless of the suction-side design of the rear edge thereof.
  • the invention is now used on this element.
  • the profile contour of the blades is concave on the suction side.
  • This concavity which is explained in more detail in FIG. 2, preferably extends from the actual rear edge over an extension E which corresponds approximately to the above-mentioned dimension Q.
  • the new measure is shown in detail in FIG. It goes without saying that here the disclosure of all the absolute values on which the calculations are based is dispensed with, since these are in any case of insufficient informative value because of their dependence on too many parameters.
  • the previously known profile contours are shown in dash-dotted lines, the same trailing edge thickness being assumed in each case.
  • the dash-dotted contour indicates a straight trailing edge on the suction side, the transition to the convex part not being shown here; the dashed contour corresponds to the convex profile formation, which is a continuation of the convex blade back.
  • the new concave contour K lies between the two.
  • the contour can be explained as follows: A tangent is created from the trailing edge corner to the suction side. From this tangent, the wall now deviates towards the pressure side.
  • the new contour is therefore made up of two parts. First of all, a first section adjoining the suction side with a more indented convexity, which extends to the turning point U and from there to the actual concave section K, which extends to the trailing edge corner.
  • This profile contour must be designed in such a way that the suction-side flow velocity is first decelerated after the maximum reached with a stronger gradient and then with a weaker gradient. There may even be a slight acceleration towards the rear edge.
  • FIGS. 3 and 4 show how this looks qualitatively and quantitatively.
  • the chord length Se of the blades is plotted dimensionlessly on the abscissa of the two diagrams.
  • the abscissa in FIG. 3 bears the Mach number M, that in FIG. 4 the dimensionless ratio J of the lack of impulse thickness to the chord length.
  • the curves indicated with D denote the prevailing conditions on the blade pressure side, while the curves indicated with S indicate represent the prevailing conditions on the blade suction side.
  • the solid curves N are the profile provided with the new measure, while the dashed curves B show the results for a profile with a convex profile of the trailing edge on the suction side.
  • the full curves N D are therefore congruent in both diagrams with the dashed curves B D not shown .
  • Fig. 4 shows how the new measure affects the pulse deficiency thickness.
  • the corresponding boundary layer calculations now show that, analogously to the Mach number distribution in FIG. 3, the larger gradient of the speed decrease according to curve N S initially leads to a greater increase in the pulse deficiency thickness.
  • the subsequent smaller gradient of the decrease in speed towards the rear edge leads to a clear flattening of the lack of impulse thickness.
  • the lack of momentum at the rear edge which is decisive for the loss of profile, is smaller than the comparable value that can be achieved with a convex rear edge, as is clearly shown by curve B S.

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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 (2)

  1. Aube de turbomachine pour des conditions subsoniques, avec un profil du contour à courbure convexe dans la région de l'arête avant et sur la plus grande partie de l'extrados (S) et avec un profil du contour à courbure concave dans la région de l'intrados (D), l'ensemble du contour du profil présentant une courbe continue, caractérisée en ce que le profil du contour a une configuration concave (K) dans la région de l'arête arrière du côté de l'aspiration.
  2. Aube de turbomachine suivant la revendication 1, caractérisée en ce que le tronçon concave (K) dans la région de l'arête arrière s'étend à partir de l'arête arrière sur une longueur (E) qui vaut sensiblement du simple jusqu'au double de la distance (Q) entre deux aubes voisines, dans la section transversale la plus étroite.
EP92110107A 1991-06-28 1992-06-16 Aube de turbine à flux subsonique Expired - Lifetime EP0520288B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH1924/91 1991-06-28
CH192491 1991-06-28

Publications (2)

Publication Number Publication Date
EP0520288A1 EP0520288A1 (fr) 1992-12-30
EP0520288B1 true EP0520288B1 (fr) 1994-09-07

Family

ID=4221779

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92110107A Expired - Lifetime EP0520288B1 (fr) 1991-06-28 1992-06-16 Aube de turbine à flux subsonique

Country Status (4)

Country Link
US (1) US5228833A (fr)
EP (1) EP0520288B1 (fr)
JP (1) JPH05187202A (fr)
DE (1) DE59200459D1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0934455B1 (fr) * 1996-10-28 2005-04-06 Siemens Westinghouse Power Corporation Profil aerodynamique destine a une turbomachine
DE19650656C1 (de) * 1996-12-06 1998-06-10 Mtu Muenchen Gmbh Turbomaschine mit transsonischer Verdichterstufe
JP4484396B2 (ja) 2001-05-18 2010-06-16 株式会社日立製作所 タービン動翼
US6682301B2 (en) 2001-10-05 2004-01-27 General Electric Company Reduced shock transonic airfoil
KR100713252B1 (ko) * 2005-07-08 2007-05-02 부산대학교 산학협력단 축류 터빈용 로터 블레이드
US9790797B2 (en) 2011-07-05 2017-10-17 United Technologies Corporation Subsonic swept fan blade
US9957801B2 (en) 2012-08-03 2018-05-01 United Technologies Corporation Airfoil design having localized suction side curvatures
US10641113B2 (en) * 2015-04-08 2020-05-05 United Technologies Corporation Airfoils
JP6730245B2 (ja) * 2017-11-17 2020-07-29 三菱日立パワーシステムズ株式会社 タービンノズル及びこのタービンノズルを備える軸流タービン
CN109356666B (zh) * 2018-12-14 2021-05-25 中国航发沈阳发动机研究所 一种轴流式涡轮大小叶片组合叶栅的叶型设计方法

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE249844C (fr) *
US1748892A (en) * 1917-10-20 1930-02-25 Allis Chalmers Mfg Co Hydraulic process and apparatus
GB490501A (en) * 1937-03-04 1938-08-16 Escher Wyss Maschf Ag Improvements in or relating to the blading of steam or gas turbines
US2935246A (en) * 1949-06-02 1960-05-03 Onera (Off Nat Aerospatiale) Shock wave compressors, especially for use in connection with continuous flow engines for aircraft
US2830753A (en) * 1951-11-10 1958-04-15 Edward A Stalker Axial flow compressors with circular arc blades
US2949224A (en) * 1955-08-19 1960-08-16 American Mach & Foundry Supersonic centripetal compressor
US3156407A (en) * 1958-07-07 1964-11-10 Commissariat Energie Atomique Supersonic compressors
US3333817A (en) * 1965-04-01 1967-08-01 Bbc Brown Boveri & Cie Blading structure for axial flow turbo-machines
DE3202855C1 (de) * 1982-01-29 1983-03-31 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur Verminderung von Sekundaerstroemungsverlusten in einem beschaufelten Stroemungskanal

Also Published As

Publication number Publication date
EP0520288A1 (fr) 1992-12-30
JPH05187202A (ja) 1993-07-27
DE59200459D1 (de) 1994-10-13
US5228833A (en) 1993-07-20

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