EP0385833A1 - Laufschaufel einer Turbomaschine mit Kompensation des Einspannmoments am Fuss - Google Patents

Laufschaufel einer Turbomaschine mit Kompensation des Einspannmoments am Fuss Download PDF

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Publication number
EP0385833A1
EP0385833A1 EP90400501A EP90400501A EP0385833A1 EP 0385833 A1 EP0385833 A1 EP 0385833A1 EP 90400501 A EP90400501 A EP 90400501A EP 90400501 A EP90400501 A EP 90400501A EP 0385833 A1 EP0385833 A1 EP 0385833A1
Authority
EP
European Patent Office
Prior art keywords
blade
foot
gravity
sections
curve
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.)
Granted
Application number
EP90400501A
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English (en)
French (fr)
Other versions
EP0385833B1 (de
Inventor
Christian Odoul
Marc Gilles France Paty
Jean-Pierre Roger Serey
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0385833A1 publication Critical patent/EP0385833A1/de
Application granted granted Critical
Publication of EP0385833B1 publication Critical patent/EP0385833B1/de
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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations

Definitions

  • the present invention relates to a movable blade of a turbomachine whose compensated bending moments at the foot of the blade are compensated.
  • FR-A 2 556 409 defines a blade with reduced centrifugal stresses for which the geometrical location of the centers of gravity of the blade sections is nonlinear and has two parts of inclinations opposite with respect to a radial straight line.
  • Figure 2 of the drawings schematically shows this solution and the curve 1a representing the area centers of gravity with respect to the platform 2a and 3a at the foot of the blade.
  • Another proposed solution shown diagrammatically in FIG. 3 shows a non-linear curve 1b of the geometrical location of the centers of gravity of the cross sections of the blade of the blade between the platform 2b and the foot 3b on the one hand and the radially external end. on the other hand.
  • the curve 1b in this case has a variable inclination which corresponds to the application of a continuous law of compensation for bending moments.
  • the invention defines a movable blade of a turbomachine which does not have the drawbacks of known prior solutions while ensuring cancellation of the bending moments at the foot of the blade by compensation.
  • Said blade is characterized in that the geometrical location of the centers of gravity of the cross sections whose stacking forms the blade of the blade is a curve of which one end has its starting point, in the plane of axial symmetry of the foot of blade, at the meeting point of the radial straight line passing through the axis of rotation of the motor with the zone of connection of the blade with the platform and the foot of the blade and which then progressively connects to at least one first line segment parallel to said radial line and axially spaced apart.
  • the geometrical location of the centers of gravity of the cross sections comprises, in addition to said line segment, a second line segment located between said fin and the radially outer end of blade , axially spaced from the first segment and progressively connecting to said first segment at said fin.
  • a blade 10 according to the invention of the movable blade type of a turbomachine is shown diagrammatically in FIG. 4 by its foot 11, its platform 12 and the curve 13 which represents the geometrical location of the centers of gravity of the cross sections whose stacking forms the aerodynamic blade of the blade 10.
  • the curve 13 has an origin at the level of the platform 12 at the center point 0 where the radial straight line passing through the axis of rotation A of the engine and contained in the plane of symmetry of the foot 11 meets the platform 12 and the foot 11.
  • the curve 13 comprises along the blade of the blade 10 a straight part axially offset with respect to said radial straight line 1 shown in dotted lines in FIG.
  • the blade has an evolving part for connecting the blade to the foot which corresponds to a connecting part 13a of the curve of the geometric location of the centers of gravity of the sections.
  • a blade 20 shown diagrammatically in FIG. 5 comprises intermediate heels or fins carried laterally by the blade of the blade and symbolized at 23 in FIG. 5, the curve of the geometrical location of the centers of gravity of the cross sections of the blade of the blade 20 takes the form indicated in FIG. 5.
  • the curve includes, as before, an origin 0 centered on the foot 21 and the platform 22 of the blade 20, a continuous evolving part of connection 24a to a first part right 24 axially offset from the radial line 1 up to the level of the fin 23 and beyond the fin 23 again a offset by a continuous evolving part connecting 25a to a second straight part 25 to the end of the blade of the blade 20.
  • FIG. 6 shows an example of the actual curves obtained in the application to a movable blade of a turbomachine and representing the geometrical location of the centers of gravity of the cross sections of the blade, one 30 according to axial coordinates and the other 40 according to tangential coordinates, and comprising, remarkably in accordance with the invention, the right-hand parts offset with respect to the central radial straight line.
  • FIG. 7 shows an example in the application to a movable blade of a turbomachine comprising intermediate heels or fins carried laterally by the blade of the blade.
  • the curves 50 and 60 representing the geometrical location of the centers of gravity of the cross sections of the blade, respectively according to axial coordinates and tangential coordinates, comprise from an origin O at the center of the foot of the blade, a portion 51 or 61 of connection corresponding to a continuous evolving zone of connection of the blade to the plane of symmetry of the foot of the blade, then a part of line 52 or 62 offset relative to the radial line 1 centered on the foot, which corresponds to a "block" offset of the sections of the blade of the blade, followed by a new portion of curve 53 or 63 at the level of the fin which is connected to a new portion of straight line 54 or 64 which has an additional offset by with respect to said radial straight line 1 and corresponds to the offset of a second "en bloc" part of sections of the blade of the blade.
  • FIG. 8 schematically shows an example of production of movable blades in accordance with the invention. Only a very precise geometrical analysis makes it possible to determine the geometrical place of the centers of gravity of the transverse sections of blade which is not a curve materialized on part. We find on a blade 70, a foot 71, a platform 72, a blade 73 and the fins 74 carried by said blade as well as a zone 73a for connecting the blade 73 to the foot 71.
  • the offset in parts and in block of the cross sections of the blade of the blades according to the invention makes it possible to obtain the creation of induced return moments in the centrifugal field and in the case of fins, also to balance the induced effects. This gives rise to a cancellation of the bending moments at the foot of the blade which is the mechanically most stressed area.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP90400501A 1989-03-01 1990-02-23 Laufschaufel einer Turbomaschine mit Kompensation des Einspannmoments am Fuss Expired - Lifetime EP0385833B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8902639 1989-03-01
FR8902639A FR2643940B1 (fr) 1989-03-01 1989-03-01 Aube mobile de turbomachine a moment de pied compense

Publications (2)

Publication Number Publication Date
EP0385833A1 true EP0385833A1 (de) 1990-09-05
EP0385833B1 EP0385833B1 (de) 1992-04-01

Family

ID=9379241

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90400501A Expired - Lifetime EP0385833B1 (de) 1989-03-01 1990-02-23 Laufschaufel einer Turbomaschine mit Kompensation des Einspannmoments am Fuss

Country Status (4)

Country Link
US (1) US5044885A (de)
EP (1) EP0385833B1 (de)
DE (1) DE69000050D1 (de)
FR (1) FR2643940B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1994012390A2 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Coolable rotor blade structure
DE19823555A1 (de) * 1998-05-27 1999-12-02 Claas Saulgau Gmbh Heuwerbungsmaschine
WO2017013053A1 (en) * 2015-07-20 2017-01-26 Nuovo Pignone Tecnologie Srl Unshrouded turbomachine impeller with improved rigidity

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2665005B2 (ja) * 1989-10-24 1997-10-22 三菱重工業株式会社 軸流機械の動翼
US5203676A (en) * 1992-03-05 1993-04-20 Westinghouse Electric Corp. Ruggedized tapered twisted integral shroud blade
US6331100B1 (en) * 1999-12-06 2001-12-18 General Electric Company Doubled bowed compressor airfoil
US6299412B1 (en) * 1999-12-06 2001-10-09 General Electric Company Bowed compressor airfoil
EP1564374A1 (de) * 2004-02-12 2005-08-17 Siemens Aktiengesellschaft Schaufelblatt für eine Strömungsmaschine
US7204676B2 (en) * 2004-05-14 2007-04-17 Pratt & Whitney Canada Corp. Fan blade curvature distribution for high core pressure ratio fan
US8356975B2 (en) * 2010-03-23 2013-01-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured vane platform
US9976433B2 (en) 2010-04-02 2018-05-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured rotor blade platform
GB2483061A (en) * 2010-08-23 2012-02-29 Rolls Royce Plc A method of damping aerofoil structure vibrations
FR2967202B1 (fr) * 2010-11-10 2013-01-11 Snecma Procede d'optimisation du profil d'une aube en materiau composite pour roue mobile de turbomachine
US9920625B2 (en) 2011-01-13 2018-03-20 Siemens Energy, Inc. Turbine blade with laterally biased airfoil and platform centers of mass
US11767761B2 (en) 2018-08-02 2023-09-26 Horton, Inc. Low solidity vehicle cooling fan

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1541657A (en) * 1924-05-24 1925-06-09 Parsons Turbine blading
US2398140A (en) * 1943-12-08 1946-04-09 Armstrong Siddeley Motors Ltd Bladed rotor
GB609322A (en) * 1945-11-07 1948-09-29 Power Jets Res & Dev Ltd Improvements relating to axial-flow compressors and like machines, and blading thereof
GB610786A (en) * 1943-02-13 1948-10-20 Centre Nat Rech Scient Steam turbines
FR2556409A1 (fr) * 1983-12-12 1985-06-14 Gen Electric Aube perfectionnee pour moteur a turbine a gaz et procede de fabrication
EP0260175A1 (de) * 1986-09-12 1988-03-16 Ecia - Equipements Et Composants Pour L'industrie Automobile Profilierter Propellerflügel und seine Anwendung in Motorventilatoren

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US3128939A (en) * 1964-04-14 Szydlowski
US1127143A (en) * 1908-08-01 1915-02-02 Wiedling Mfg Company Propeller.
US1027201A (en) * 1911-07-08 1912-05-21 Willibald Grun Turbine-blade.
US2282077A (en) * 1940-02-03 1942-05-05 Hamilton K Moore Changeable pitch propeller unit
US2663493A (en) * 1949-04-26 1953-12-22 A V Roe Canada Ltd Blading for compressors, turbines, and the like
US2915238A (en) * 1953-10-23 1959-12-01 Szydlowski Joseph Axial flow compressors
DE2144600A1 (de) * 1971-09-07 1973-03-15 Maschf Augsburg Nuernberg Ag Verwundene und verjuengte laufschaufel fuer axiale turbomaschinen
CH541065A (de) * 1972-01-20 1973-08-31 Bbc Brown Boveri & Cie Verdrillte Laufschaufel einer axial durchströmten Turbomaschine
GB1419381A (en) * 1972-03-09 1975-12-31 Rolls Royce Fan for gas turbine engines
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
US4012172A (en) * 1975-09-10 1977-03-15 Avco Corporation Low noise blades for axial flow compressors
FR2505399A1 (fr) * 1981-05-05 1982-11-12 Alsthom Atlantique Aubage directeur pour veines divergentes de turbine a vapeur
US4460315A (en) * 1981-06-29 1984-07-17 General Electric Company Turbomachine rotor assembly
US4451205A (en) * 1982-02-22 1984-05-29 United Technologies Corporation Rotor blade assembly
US4682935A (en) * 1983-12-12 1987-07-28 General Electric Company Bowed turbine blade
US4585395A (en) * 1983-12-12 1986-04-29 General Electric Company Gas turbine engine blade
US4638602A (en) * 1986-01-03 1987-01-27 Cavalieri Dominic A Turbine blade holding device

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1541657A (en) * 1924-05-24 1925-06-09 Parsons Turbine blading
GB610786A (en) * 1943-02-13 1948-10-20 Centre Nat Rech Scient Steam turbines
US2398140A (en) * 1943-12-08 1946-04-09 Armstrong Siddeley Motors Ltd Bladed rotor
GB609322A (en) * 1945-11-07 1948-09-29 Power Jets Res & Dev Ltd Improvements relating to axial-flow compressors and like machines, and blading thereof
FR2556409A1 (fr) * 1983-12-12 1985-06-14 Gen Electric Aube perfectionnee pour moteur a turbine a gaz et procede de fabrication
EP0260175A1 (de) * 1986-09-12 1988-03-16 Ecia - Equipements Et Composants Pour L'industrie Automobile Profilierter Propellerflügel und seine Anwendung in Motorventilatoren

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Brown Boveri Mitteilungen vol. 59, no. 1, 01 janvier 1972, Baden (CH) pages 42 - 53; A,Hohn et al: "Die Endschaufeln grosser Dampfturbinen" *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1994012390A2 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Coolable rotor blade structure
WO1994012390A3 (en) * 1992-12-08 1994-08-18 United Technologies Corp Coolable rotor blade structure
DE19823555A1 (de) * 1998-05-27 1999-12-02 Claas Saulgau Gmbh Heuwerbungsmaschine
WO2017013053A1 (en) * 2015-07-20 2017-01-26 Nuovo Pignone Tecnologie Srl Unshrouded turbomachine impeller with improved rigidity
US10669864B2 (en) 2015-07-20 2020-06-02 Nuovo Pignone Srl Unshrouded turbomachine impeller with improved rigidity

Also Published As

Publication number Publication date
DE69000050D1 (de) 1992-05-07
FR2643940B1 (fr) 1991-05-17
FR2643940A1 (fr) 1990-09-07
US5044885A (en) 1991-09-03
EP0385833B1 (de) 1992-04-01

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