EP0396726B1 - Befestigung und dichtung einer laufschaufel an einer laufradscheibe einer gasturbine - Google Patents

Befestigung und dichtung einer laufschaufel an einer laufradscheibe einer gasturbine Download PDF

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Publication number
EP0396726B1
EP0396726B1 EP89913063A EP89913063A EP0396726B1 EP 0396726 B1 EP0396726 B1 EP 0396726B1 EP 89913063 A EP89913063 A EP 89913063A EP 89913063 A EP89913063 A EP 89913063A EP 0396726 B1 EP0396726 B1 EP 0396726B1
Authority
EP
European Patent Office
Prior art keywords
segment
disc
blades
downstream
accordance
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
EP89913063A
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English (en)
French (fr)
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EP0396726A1 (de
Inventor
Philippe Patrick Catte
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
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 filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0396726A1 publication Critical patent/EP0396726A1/de
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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Definitions

  • the present invention relates to turbomachine rotors and more particularly to the means for axially locking vanes mounted in axial pinouts of the periphery of the disc.
  • a first problem consists in ensuring the axial locking of each of the blades in the simplest possible but also the safest way possible and so that the easy disassembly of a blade or of the entire stage is also simplified.
  • the second problem is that of the seal between the upstream and downstream of a disc and arises crucially in turbomachine compressors. Indeed, if the spaces located between the bottom of the disc cavities and the blade roots are not properly masked, large volumes of downstream air can pass under the blade roots and recirculate upstream of the compressor , which decreases the compression ratio thereof and causes the overall efficiency of the turbomachine to drop prohibitively.
  • turbomachinery of the type currently being studied for example fast propeller turbojets whose compressor rotors have very small diameters, it is necessary to minimize the height under the platforms and to gain mass on the compressor blades, the solution above mentioned cannot be used because it is too bulky.
  • the object of the present invention is therefore to replace the anterior double segmentation with a single monobloc segment. performing both locking and sealing functions.
  • the subject of the invention is therefore a turbomachine rotor of the type already indicated above and which is characterized in that the locking means consists of a single split segment with Y-shaped section of which a radially external upstream branch is inserted. in the grooves of the spoilers downstream of the blades and of the disc, the radially external downstream branch of the segment being pressed against the downstream part of the spoilers of the blades.
  • the rotor disc 1 comprises substantially axial cells 2 into which are inserted the feet 3 of vanes 4 having an upstream wedging means 5 on the upstream face of the disc 1 and a downstream spoiler 6 comprising a transverse groove 7 radially oriented towards the axis of the disc.
  • the latter comprises opposite the groove 7 of the blades a groove 8 radially oriented towards its periphery, which will be used for mounting / dismounting the segment.
  • a split segment 9 whose section has the shape of a Y with asymmetrical branches 9a and 9b joined by their common base 9c.
  • the upstream branch 9a flat is inserted into the groove 7.
  • the downstream branch 9b longer than the branch 9a, has a curved shape which matches the downstream shape of the spoiler 6 and which rises under the platform 10 of the blade.
  • the two branches 9a and 9b can be produced during manufacture with a slight tightening so that during assembly of the segment in its location the downstream branch is pressed against the downstream face of the spoiler 6.
  • the pressure coming from the ⁇ P between the upstream and downstream of the disc, combined with the centrifugal force, increases the plating of the downstream branch against the blade.
  • the segment is produced by welding radially internal parts of two annular sheets of which the downstream one has a curved shape and the upstream one is flat.
  • the segment is produced by folding and forming a single annular sheet, the fold of which forms the foot 9c of the Y section of the segment.
  • the segment is produced by machining around a one-piece annular blank.
  • the segment is assembled by placing the foot 9c of the segment in the groove 8 and compressing it radially so that the upstream branch 9a passes under the spoiler 6. Once pressed forward, the segment can be released radially so that the upstream branch 9a enters the groove 7. In operation, the centrifugal force will maintain the segment in the groove 7.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (7)

1. Turbomachinenrotor, insbesondere für Flugzeug-Turbotriebwerke, mit wenigstens einer Scheibe, die einen Satz von Schaufeln trägt, deren Füße in Zellen montiert sind, die am Umfang der Scheibe in Richtung einer Achse herausgearbeitet sind, die zu einer zur Längsachse des Triebwerks parallelen Linie parallel verläuft oder dieser gegenüber geringfügig geneigt ist, wobei die Schaufelfüße (3) Mittel (5) zum Festlegen der Schaufeln an der stromaufwärtigen Seite des Scheibe (1) aufweisen und auf der stromabwärtigen Seite eine Nase (6) mit einer radial zur Achse der Scheibe ausgerichteten transversalen Kehle (7) besitzen, in die ein Mittel zur axialen Verriegelung der Schaufeln an der stromabwärtigen Seite der Scheibe eingesetzt ist, das gleichzeitig die Dichtigkeit zwischen den Schaufelfüßen und dem Boden der genannten Zellen (2) der Scheibe gewährleistet, wobei die Scheibe eine kreisförmige Kehle (8) besitzt, die radial in Richtung auf ihren Umfang ausgerichtet ist, dadurch gekennzeichnet, daß das Verriegelungsmittel aus einem einzigen geschlitzten Segment (9) mit Y-förmigem querschnitt besteht, dessen radial äußerer stromaufwärtiger Schenkel (9a) in die Kehle (7) der stromabwärtigen Nasen (6) der Schaufeln und der Scheibe (1) eingesetzt ist, und daß der radial äußere stromabwärtige Schenkel (9b) des Segments (9) auf dem stromabwärtigen Teil der Nasen (6) der Schaufeln aufliegt.
2. Turbomachinenrotor nach Anspruch 1, dadurch gekennzeichnet, daß der stromabwärtige Schenkel (9b) des Segments eine gekfümmte Form hat, die der Form des stromabwärtigen Teils der Nasen (6) der Schaufeln entspricht.
3. Turbomachinenrotor nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, daß der stromabwärtige Schenkel (9b) des Segments länger ist als sein stromaufwärtiger Schenkel (9a) und in radialer Richtung unter die Plattform (10) der Schaufeln ansteigt.
4. Turbomachinenrotor nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß das Segment mit einer leichten Spannung seiner radial äußeren Schenkel (9a, 9b) hergestellt ist, um eine Klemmverriegelung der Schaufeln an der Scheibe und eine bessere Dichtigkeit herbeizuführen.
5. Turbomachinenrotor nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß das Segment (9) durch Falten und Verformen eines ringförmigen Bleches hergestellt ist.
6. Turbomachinenrotor nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß das Segment (9) durch Verschweißen der radial inneren Teile zweier ringförmiger Bleche hergestellt ist.
7. Turbomachinenrotor nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß das Segment (9) durch maschinelles Bearbeiten eines einstückigen ringförmigen Rohlings hergestellt ist.
EP89913063A 1988-11-17 1989-11-16 Befestigung und dichtung einer laufschaufel an einer laufradscheibe einer gasturbine Expired - Lifetime EP0396726B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8814913 1988-11-17
FR8814913A FR2639063A1 (fr) 1988-11-17 1988-11-17 Segment d'arret et d'etancheite d'un ensemble d'aubes monte sur un disque de rotor de turbomachine

Publications (2)

Publication Number Publication Date
EP0396726A1 EP0396726A1 (de) 1990-11-14
EP0396726B1 true EP0396726B1 (de) 1992-05-13

Family

ID=9371914

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89913063A Expired - Lifetime EP0396726B1 (de) 1988-11-17 1989-11-16 Befestigung und dichtung einer laufschaufel an einer laufradscheibe einer gasturbine

Country Status (4)

Country Link
US (1) US5052893A (de)
EP (1) EP0396726B1 (de)
FR (1) FR2639063A1 (de)
WO (1) WO1990005837A1 (de)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5211407A (en) * 1992-04-30 1993-05-18 General Electric Company Compressor rotor cross shank leak seal for axial dovetails
FR2694046B1 (fr) * 1992-07-22 1994-09-23 Snecma Dispositif d'étanchéité et de rétention pour un rotor entaillé de brochages recevant des pieds d'aubes.
US5257909A (en) * 1992-08-17 1993-11-02 General Electric Company Dovetail sealing device for axial dovetail rotor blades
FR2715975B1 (fr) * 1994-02-10 1996-03-29 Snecma Rotor de turbomachine à rainures d'aube débouchantes axiales ou inclinées.
JP2726895B2 (ja) * 1994-09-14 1998-03-11 川崎重工業株式会社 セラミックブレードの取付構造
GB2311826B (en) * 1996-04-02 2000-05-10 Europ Gas Turbines Ltd Turbomachines
CZ20002685A3 (cs) * 1999-12-20 2001-08-15 General Electric Company Zařízení pro uchycení lopatek otáčivého stroje a způsob jejich uchycení
US7252481B2 (en) * 2004-05-14 2007-08-07 Pratt & Whitney Canada Corp. Natural frequency tuning of gas turbine engine blades
US7238008B2 (en) * 2004-05-28 2007-07-03 General Electric Company Turbine blade retainer seal
JP4873200B2 (ja) * 2007-03-27 2012-02-08 株式会社Ｉｈｉ ファン動翼支持構造とこれを有するターボファンエンジン
US8038405B2 (en) * 2008-07-08 2011-10-18 General Electric Company Spring seal for turbine dovetail
US8210820B2 (en) * 2008-07-08 2012-07-03 General Electric Company Gas assisted turbine seal
US8011894B2 (en) * 2008-07-08 2011-09-06 General Electric Company Sealing mechanism with pivot plate and rope seal
US8215914B2 (en) * 2008-07-08 2012-07-10 General Electric Company Compliant seal for rotor slot
US8210823B2 (en) * 2008-07-08 2012-07-03 General Electric Company Method and apparatus for creating seal slots for turbine components
US8210821B2 (en) * 2008-07-08 2012-07-03 General Electric Company Labyrinth seal for turbine dovetail
FR2939832B1 (fr) * 2008-12-11 2011-01-07 Turbomeca Roue de turbine equipee d'un dispositif de retenue axiale verrouillant des pales par rapport a un disque.
US8657580B2 (en) * 2010-06-17 2014-02-25 Pratt & Whitney Blade retainment system
FR2974863B1 (fr) * 2011-05-06 2015-10-23 Snecma Disque de soufflante de turbomachine
FR3127255A1 (fr) * 2021-09-23 2023-03-24 Safran Aircraft Engines Ensemble rotatif pour turbomachine
EP4230843A1 (de) * 2022-02-17 2023-08-23 Siemens Energy Global GmbH & Co. KG Rotoranordnung für einen rotor einer gasturbine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB802476A (en) * 1955-09-29 1958-10-08 Rolls Royce Improvements in or relating to rotors of axial-flow fluid machines for example compressors and turbines
DE1116094B (de) * 1959-07-22 1961-10-26 Buessing Nutzkraftwagen G M B Schwimmvorrichtung fuer Landfahrzeuge
GB905582A (en) * 1960-05-26 1962-09-12 Rolls Royce Improvements relating to the sealing of blades in a bladed rotor
US3853425A (en) * 1973-09-07 1974-12-10 Westinghouse Electric Corp Turbine rotor blade cooling and sealing system
FR2324873A1 (fr) * 1975-09-17 1977-04-15 Snecma Perfectionnements aux flasques de rotors de turbomachines
FR2419389A1 (fr) * 1978-03-08 1979-10-05 Snecma Perfectionnements aux flasques de rotors de turbomachines
JPS6339741A (ja) * 1986-07-30 1988-02-20 Mazda Motor Corp 部品組付装置
FR2603333B1 (fr) * 1986-09-03 1990-07-20 Snecma Rotor de turbomachine comportant un moyen de verrouillage axial et d'etancheite d'aubes montees dans des brochages axiaux du disque et procede de montage

Also Published As

Publication number Publication date
EP0396726A1 (de) 1990-11-14
FR2639063A1 (fr) 1990-05-18
WO1990005837A1 (fr) 1990-05-31
US5052893A (en) 1991-10-01

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