EP0069620B1 - Dispositif d'amortissement d'aubes de turbomachines, notamment de soufflantes - Google Patents

Dispositif d'amortissement d'aubes de turbomachines, notamment de soufflantes Download PDF

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Publication number
EP0069620B1
EP0069620B1 EP82401105A EP82401105A EP0069620B1 EP 0069620 B1 EP0069620 B1 EP 0069620B1 EP 82401105 A EP82401105 A EP 82401105A EP 82401105 A EP82401105 A EP 82401105A EP 0069620 B1 EP0069620 B1 EP 0069620B1
Authority
EP
European Patent Office
Prior art keywords
blade
torsion bar
root
engaged
sleeve
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
EP82401105A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0069620A1 (fr
Inventor
Alexandre Forestier
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 EP0069620A1 publication Critical patent/EP0069620A1/fr
Application granted granted Critical
Publication of EP0069620B1 publication Critical patent/EP0069620B1/fr
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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the present invention relates to a rotor, in particular to blowers, comprising blades damping devices.
  • the feet of fan blades are mounted with clearance in cells distributed around the periphery of a support disc.
  • the centrifugal force is insufficient to press the foot of the blade on the upper part of the cell, or even on the ground, when the fan turns in a reel under the effect of the wind, the feet of the blades beat in their cell.
  • the beating of the blade root can cause erosion of the protective coating, matting of the disc teeth or blade blade and local corrosion which are all detrimental defects in the longevity of the parts and which can cause the scrap of these which are very expensive.
  • GB-A-2 021 206 describes an axial blade root retention device using an elastic radial damping blade. This device is not entirely satisfactory, in particular because it is complicated and it requires a large number of elementary parts.
  • the compression means consists of a torsion bar disposed under the foot of the blade and one of the ends of which is secured to a cam bearing against the base of the blade foot and the bottom of the cell, while the other end of the torsion bar is in abutment by a cam-shaped dowel attached to said bar against the base of the blade tip and the bottom of the cell under the prior tension imparted to the bar, the minimum and maximum radial dimensions of the cam and of the pin being respectively less than and greater than the distance separating the axis of the torsion bar from the base of the foot of the blade.
  • the underside of the blade root is thus permanently subjected to compression which keeps it in abutment on the upper walls of the cell.
  • FIG 1 there is shown a fan blade 1 whose base 2 is engaged in a cell 3 ( Figures 3, 4) of a rotor disc 4 of a turbomachine fan.
  • the underside of the foot 2 of the blade is subjected to the action of a compression means which keeps the said foot in abutment against the upper walls 3a, 3b (FIGS. 3 to 5) of the cell 3.
  • a torsion bar 5 (FIG. 1, 2) which is supported longitudinally on one side by a cylindrical part 5a against an annular member 6 fixed to the rear of the disc 4 by bolts 7 and on the other side by its end 5b against a front cone 8 fixed to the support disc 4 by bolts 9.
  • the torsion bar 5 is inserted by overmolding in a sleeve 12 of polymer material.
  • This sleeve corresponds to the shape of the space left free between the bottom of the cell 3 and the lower part of the foot 2 of the blade.
  • a lateral recess is provided at the two ends of the sleeve to allow the travel, during assembly, of a cam 10 and of a bush 16 carried by the torsion bar and which are described below.
  • the torsion bar 5 has a cam 10 (FIGS. 1, 2, 5) comprising an eccentric boss 10a which bears against the underside 11 of the blade root, so that one end of the torsion bar is immobilized in rotation against the foot of the blade.
  • the torsion bar 5 has two grooved parts 13, 14 (FIGS. 1, 2) separated by a smooth part 15 of smaller section.
  • a sleeve 16 having a corresponding grooved hole 16b in order to secure in rotation the sleeve 16 with the torsion bar 5, said sleeve playing the role of a second cam which has, like the cam 10, an eccentric boss 16a resting against the underside of the foot 2 of the blade under the tension imparted to the torsion bar 5 before the fitting of the bush 16.
  • a ring 17 having internal grooves corresponding to those of the torsion bar, said ring 17 being in abutment on one side against the sleeve 16 which it locks axially and on the other side against a split elastic ring 18 engaged in a groove 19 provided at the end of the torsion bar.
  • a housing or slot 20 in which is engaged a lock 21 (FIGS. 2 and 6) in the shape of a U which is mounted on a part 2a of reduced section of the foot 2 of the blade, said lock 21 having a circular cutout 21a in which the ring 17 which radially locks the lock 21 in the housing 20.
  • the assembly of the device is carried out as follows.
  • the torsion bar 5 being mounted in the space of the cell under the foot 2 of the blade with the sleeve 12 of deformable material and the cam 10 being in abutment against the lower part 11 of the blade foot, slides on the front part of the torsion bar 5 the bush 16 to the smooth part 15 of the bar.
  • a tool of the "left-turn" type is then inserted on the fluted part 14 of the torsion bar and a torsion is printed on the latter.
  • the tool is kept in this position and the sleeve 16 is then slid from the smooth part 15 to the grooved part 13, after having chosen the position which ensures that the boss 16a has a sliding contact on the underside of the blade root. .
  • the tension of the bar 5 being produced, the tool can then be removed.
  • the U-bolt, 21, is then introduced through the upper face of the spoiler before the blade, into the housing 20.
  • the ring 17 is itself axially locked by a locking ring 18.
  • front cone 8 is mounted, which is fixed by bolts 9 to the disc 4 and which locks the entire area.

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)
EP82401105A 1981-06-25 1982-06-18 Dispositif d'amortissement d'aubes de turbomachines, notamment de soufflantes Expired EP0069620B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8112459 1981-06-25
FR8112459A FR2508541B1 (fr) 1981-06-25 1981-06-25 Dispositif d'amortissement d'aubes de turbomachines, notamment de soufflantes

Publications (2)

Publication Number Publication Date
EP0069620A1 EP0069620A1 (fr) 1983-01-12
EP0069620B1 true EP0069620B1 (fr) 1985-02-13

Family

ID=9259854

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82401105A Expired EP0069620B1 (fr) 1981-06-25 1982-06-18 Dispositif d'amortissement d'aubes de turbomachines, notamment de soufflantes

Country Status (5)

Country Link
US (1) US4453891A (enrdf_load_stackoverflow)
EP (1) EP0069620B1 (enrdf_load_stackoverflow)
JP (1) JPS585406A (enrdf_load_stackoverflow)
DE (1) DE3262317D1 (enrdf_load_stackoverflow)
FR (1) FR2508541B1 (enrdf_load_stackoverflow)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4626169A (en) * 1983-12-13 1986-12-02 United Technologies Corporation Seal means for a blade attachment slot of a rotor assembly
US4778342A (en) * 1985-07-24 1988-10-18 Imo Delaval, Inc. Turbine blade retainer
JPS63133031U (enrdf_load_stackoverflow) * 1987-02-23 1988-08-31
US4836749A (en) * 1988-02-19 1989-06-06 Westinghouse Electric Corp. Pre-load device for a turbomachine rotor
JPH02249913A (ja) * 1989-03-24 1990-10-05 Canon Inc 光学式エンコーダー
US5205714A (en) * 1990-07-30 1993-04-27 General Electric Company Aircraft fan blade damping apparatus
GB2287993A (en) * 1994-03-24 1995-10-04 Rolls Royce Plc Gas turbine engine fan blade retention
WO2000070509A1 (en) 1999-05-13 2000-11-23 Rolls- Royce Corporation Method for designing a cyclic symmetric structure
US8894370B2 (en) * 2008-04-04 2014-11-25 General Electric Company Turbine blade retention system and method
ATE523659T1 (de) * 2008-07-30 2011-09-15 Siemens Ag Befestigungsanordnung zur befestigung von einer laufschaufel an einem rotor einer turbomaschine
US8485784B2 (en) * 2009-07-14 2013-07-16 General Electric Company Turbine bucket lockwire rotation prevention
US8708656B2 (en) 2010-05-25 2014-04-29 Pratt & Whitney Canada Corp. Blade fixing design for protecting against low speed rotation induced wear
FR3025553B1 (fr) 2014-09-08 2019-11-29 Safran Aircraft Engines Aube a becquet amont
US20170191366A1 (en) * 2016-01-05 2017-07-06 General Electric Company Slotted damper pin for a turbine blade
FR3107724B1 (fr) * 2020-02-27 2022-06-24 Safran Aircraft Engines Rotor de soufflante à aubes à calage variable et turbomachine équipée d’un tel rotor
FR3108664A1 (fr) * 2020-03-31 2021-10-01 Safran Aircraft Engines Rotor de soufflante comprenant des aubes à centre de gravité en amont
FR3108665A1 (fr) * 2020-03-31 2021-10-01 Safran Aircraft Engines Rotor de soufflante comprenant des aubes à centre de gravité en amont
US12286903B2 (en) 2023-02-24 2025-04-29 General Electric Company Turbine engine including a composite airfoil assembly having a dovetail portion
US12241383B2 (en) 2023-02-24 2025-03-04 General Electric Company Turbine engine with a composite-airfoil assembly having a dovetail portion

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3266770A (en) * 1961-12-22 1966-08-16 Gen Electric Turbomachine rotor assembly
US3598503A (en) * 1969-09-19 1971-08-10 United Aircraft Corp Blade lock
US3723023A (en) * 1971-05-05 1973-03-27 Us Air Force Independent self adjusting vibration damper
US4088421A (en) * 1976-09-30 1978-05-09 General Electric Company Coverplate damping arrangement
US4208170A (en) * 1978-05-18 1980-06-17 General Electric Company Blade retainer

Also Published As

Publication number Publication date
JPS585406A (ja) 1983-01-12
DE3262317D1 (en) 1985-03-28
FR2508541A1 (fr) 1982-12-31
FR2508541B1 (fr) 1985-11-22
EP0069620A1 (fr) 1983-01-12
JPS6215726B2 (enrdf_load_stackoverflow) 1987-04-09
US4453891A (en) 1984-06-12

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