EP0854268B1 - Beschaufelte Rotorscheibe mit dreifüssigen Schaufeln - Google Patents

Beschaufelte Rotorscheibe mit dreifüssigen Schaufeln Download PDF

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Publication number
EP0854268B1
EP0854268B1 EP98400062A EP98400062A EP0854268B1 EP 0854268 B1 EP0854268 B1 EP 0854268B1 EP 98400062 A EP98400062 A EP 98400062A EP 98400062 A EP98400062 A EP 98400062A EP 0854268 B1 EP0854268 B1 EP 0854268B1
Authority
EP
European Patent Office
Prior art keywords
blades
disc
grooves
feet
blade roots
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
EP98400062A
Other languages
English (en)
French (fr)
Other versions
EP0854268A1 (de
Inventor
Jacky Naudet
Christophe Poy
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
SNECMA Moteurs 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 SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP0854268A1 publication Critical patent/EP0854268A1/de
Application granted granted Critical
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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides

Definitions

  • the invention relates to a bladed disc with tripod vanes.
  • Machines such as gas turbines all include bladed discs to constitute their turbines and compressors. If we put aside the discs made in one piece with the blades they carry, which are few, we find that concrete achievements of assembling the blades at discs are very diverse but fall into two fairly clearly separated families: that of the disks and the circular groove discs.
  • a tool broaching performs axial direction grooves or oblique, straight or in an arc across the width of the outer crown of the disc; the dawn are introduced around the disc by sliding their foot along the pinouts, and the interlocking of feet with bulbous section in pinouts prohibited tear off the blades.
  • An example is illustrated in Figure 6, where blades 20 have their curvilinear feet and plugged into form 22 pinouts complementary, established around the edge of a crown outer 23 of the disc, attached to a central part 24 narrower of the disc.
  • a single groove extends over the circumference of the outer crown of the disc and the feet of the blades are all engaged.
  • the invention constitutes an improvement from mounting blades to a disc within the second family. It retains the advantage inherent in it good uniformity of effort while allowing to transmit significantly higher efforts than with known achievements.
  • the bladed disc according to the invention is dug with three circular grooves in which penetrate respectively, for each of the blades, three blade roots located at different angles to the disc, and in addition, these feet are directed on the axis of disc rotation; moreover, the grooves have different sections and the blade roots also have different sections. It may be advantageous to place the grooves at different distances from the axis of disc rotation, always to allow a transmission of high forces depending on the shape (cylindrical or conical) of the disc.
  • shock absorbers can be between the blade roots and the bottoms of the grooves to reduce vibrations.
  • the document FR-2375440-A describes tripod vanes, but which are mounted in helical grooves: it concerns therefore the first family of achievements.
  • the device of document US 2,639,119 A belongs to the same family of achievements as the invention, and it describes multi-groove blades (at least four in the illustrated embodiments) in which respective feet of the disc are engaged and retained by forging. But the grooves and feet all have the same section, and their number is arbitrary and depends the width of the blades and the disc. Such a provision does not allow to adjust the efforts and stresses on the bonding surface between dawn and the disc, and the number of feet implies that they have all a small section. This double disadvantage forbidden to transmit the same efforts as with the invention between the blades and the disc.
  • the document US 1,638,639 A deserves the same comments.
  • the disc according to the invention carries the reference 1 in the figures, and we can distinguish there a thin and flat central part 2 and at the edge of which is connected to an outer crown 3 in which have been dug a central groove 4 and two lateral grooves 5 and 6 flanking the previous one, all three circular and opening outwards crown 3.
  • the three grooves 4, 5 and 6 are narrow at their opening portion to hold respectively three feet 7, 8 and 9 of bulbous shape of blades 10.
  • the disc 1 rotates by driving the crown blades 10, the latter are subjected, under the effect centrifugal, aerodynamic and vibratory forces, to mainly radial forces which are transmitted to disc 1 by three components F7, F8 and F9 passing respectively by the feet of the same number. It is thus possible to better distribute the efforts in the disc 1 only if we only had groove 4 central and its 7 foot, as in the designs earlier.
  • FIG 2 shows that the camber of the blades 10 requires placing feet 7, 8 and 9 at different angles of the circumference of the disc 1. But as seen in Figure 3, feet 7, 8 and 9 are not parallel but directed on the axis of disc X rotation 1, which favors standardization of constraints.
  • FIG. 4 illustrates a method of mounting the blades 10: notches 11 of radial direction are formed on the outer ring 3 so as to locally widen grooves 4, 5 and 6 for make it wider than feet 7, 8 and 9 and allow to insert them.
  • the blade insertion movement can be purely radial or, as shown here, it can be produced by a rotation of dawn 10 around a hinge point 12 defined by the contact of a edge of dawn 10 and crown 3. In all in this case, the blades 10 are locked in place sliding feet 7, 8 and 9 in their groove 4, 5 and 6 after insertion to make them leave the notch sector 11.
  • Figure 5 shows an element cushioning 13 made of elastic material and of arcuate shape, whose ends 14 rest on the bottom 15 of a any of grooves 4, 5 and 6 and the part of which median 16 is engaged under the foot of a blade 10, and kept under this foot despite the risk of movement of element 13 along the groove thanks to two edges 17 which pinch the blade root. Vibrations of radial direction to which the blade 10 is subjected have the effect of crushing and releasing element 13 and to give him the opportunity to dispel energy.
  • a boss 18 is advantageously provided under the middle part 16 for abutting against the bottom 15 of the groove when element 13 has been crushed a limit that one wishes not to exceed.

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 (4)

  1. Schaufel-Rotorscheibe (1) mit einem Außenkanz von Schaufeln (10),
       dadurch gekennzeichnet, daß in ihr drei kreisförmige Nuten (4, 5, 6) ausgeführt sind, in die drei Schaufelfüße (7, 8 bzw. 9) jeder Schaufel (10) eintauchen, die sich in verschiedenen Winkeln zur Rotorscheibe befinden und zu einer Drehachse (X) der Rotorscheibe hin gerichtet sind, und daß die Nuten (4, 5, 6) unterschiedliche Querschnitte haben und die Schaufelfüße (7, 8, 9) ebenfalls unterschiedliche Querschnitte haben.
  2. Schaufel-Rotorscheibe nach Anspruch 1, dadurch gekennzeichnet, daß die Nuten sich in unterschiedlichen Abständen von der Drehachse der Rotorscheibe befinden.
  3. Schaufel-Rotorscheibe nach Anspruch 1, dadurch gekennzeichnet, daß die Stoßdämpfer (13) sich zwischen den Schaufelfüßen (10) und den Nutböden (15) befinden.
  4. Schaufel-Rotorscheibe nach Anspruch 3, dadurch gekennzeichnet, daß die Stoßdämpfer aus gebogenen und federnden Plättchen, deren Enden auf den Nutböden ruhen und deren Mittelabschnitt (16) unter den Schaufelfüßen (10) liegt, und aus einem Federungsanschlag-Vorsprung (18), der unter dem Mittelabschnitt (16) angebracht ist und zu den Nutböden hin gerichtet ist, bestehen.
EP98400062A 1997-01-16 1998-01-15 Beschaufelte Rotorscheibe mit dreifüssigen Schaufeln Expired - Lifetime EP0854268B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9700383 1997-01-16
FR9700383A FR2758364B1 (fr) 1997-01-16 1997-01-16 Disque aubage a aubes tripodes

Publications (2)

Publication Number Publication Date
EP0854268A1 EP0854268A1 (de) 1998-07-22
EP0854268B1 true EP0854268B1 (de) 2000-09-13

Family

ID=9502643

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98400062A Expired - Lifetime EP0854268B1 (de) 1997-01-16 1998-01-15 Beschaufelte Rotorscheibe mit dreifüssigen Schaufeln

Country Status (6)

Country Link
US (1) US5919032A (de)
EP (1) EP0854268B1 (de)
JP (1) JPH10205304A (de)
CA (1) CA2227521A1 (de)
DE (1) DE69800296T2 (de)
FR (1) FR2758364B1 (de)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9814567D0 (en) * 1998-07-07 1998-09-02 Rolls Royce Plc A rotor assembly
US6736602B2 (en) * 2002-07-31 2004-05-18 United Technologies Corporation Hollow fan hub under blade bumper
FR2856105B1 (fr) * 2003-06-16 2007-05-25 Snecma Moteurs Amelioration de la capacite de retention d'une aube a attache marteau dissymetrique a l'aide des raidisseurs de plates-formes
DE10337868A1 (de) * 2003-08-18 2005-03-17 Mtu Aero Engines Gmbh Rotor für eine Gasturbine sowie Gasturbine
DE10357134A1 (de) * 2003-12-06 2005-06-30 Alstom Technology Ltd Rotor für einen Verdichter
US20110158814A1 (en) * 2009-12-31 2011-06-30 General Electric Company Turbine engine rotor blades and rotor wheels
US10465537B2 (en) * 2016-05-27 2019-11-05 General Electric Company Margin bucket dovetail radial support feature for axial entry buckets
GB201800732D0 (en) * 2018-01-17 2018-02-28 Rolls Royce Plc Blade for a gas turbine engine
GB201811205D0 (en) * 2018-07-09 2018-08-29 Rolls Royce Plc Blade for a gas turbine engine

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US846739A (en) * 1906-07-21 1907-03-12 Gen Electric Bucket for elastic-fluid turbines.
US1500787A (en) * 1922-09-20 1924-07-08 Gen Electric Turbine rotor
US1638639A (en) * 1923-09-18 1927-08-09 Westinghouse Electric & Mfg Co Turbine blading
US2327839A (en) * 1940-03-26 1943-08-24 Bbc Brown Boveri & Cie Turbine construction
US2639119A (en) * 1947-11-14 1953-05-19 Lockheed Aircraft Corp Rotor blade attachment means and method
US2751189A (en) * 1950-09-08 1956-06-19 United Aircraft Corp Blade fastening means
US2847187A (en) * 1955-01-21 1958-08-12 United Aircraft Corp Blade locking means
US2928651A (en) * 1955-01-21 1960-03-15 United Aircraft Corp Blade locking means
US3014695A (en) * 1960-02-03 1961-12-26 Gen Electric Turbine bucket retaining means
US3282561A (en) * 1964-12-14 1966-11-01 Associated Electric Ind Ltd Turbine rotors
US3383094A (en) * 1967-01-19 1968-05-14 Gen Electric Rotor blade locking means
US3597112A (en) * 1970-02-02 1971-08-03 Gen Electric Compressor-blade-retaining means
CH572155A5 (de) * 1974-05-27 1976-01-30 Bbc Sulzer Turbomaschinen
DE2441249C3 (de) * 1974-08-28 1979-01-04 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Axiallaufrad für hochtourige Turbomaschinen
FR2375440A1 (fr) * 1976-12-23 1978-07-21 Europ Turb Vapeur Rotor de turbine axiale
US4101245A (en) * 1976-12-27 1978-07-18 United Technologies Corporation Interblade damper and seal for turbomachinery rotor
US4767274A (en) * 1986-12-29 1988-08-30 United Technologies Corporation Multiple lug blade to disk attachment

Also Published As

Publication number Publication date
FR2758364B1 (fr) 1999-02-12
EP0854268A1 (de) 1998-07-22
US5919032A (en) 1999-07-06
FR2758364A1 (fr) 1998-07-17
DE69800296T2 (de) 2001-03-29
JPH10205304A (ja) 1998-08-04
CA2227521A1 (fr) 1998-07-16
DE69800296D1 (de) 2000-10-19

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