EP0488874A1 - Gebläserotor mit Schaufeln ohne Plattform und Stromlinien rekonstruierenden Füllstücken - Google Patents

Gebläserotor mit Schaufeln ohne Plattform und Stromlinien rekonstruierenden Füllstücken Download PDF

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Publication number
EP0488874A1
EP0488874A1 EP91403182A EP91403182A EP0488874A1 EP 0488874 A1 EP0488874 A1 EP 0488874A1 EP 91403182 A EP91403182 A EP 91403182A EP 91403182 A EP91403182 A EP 91403182A EP 0488874 A1 EP0488874 A1 EP 0488874A1
Authority
EP
European Patent Office
Prior art keywords
disc
shoe
shoes
wall
blades
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
EP91403182A
Other languages
English (en)
French (fr)
Other versions
EP0488874B1 (de
Inventor
Michel Antoine Brioude
Philippe Chereau
Jacky Naudet
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 EP0488874A1 publication Critical patent/EP0488874A1/de
Application granted granted Critical
Publication of EP0488874B1 publication Critical patent/EP0488874B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • 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 of a blower or compressor stage of a turbomachine, of the type comprising a rotor disc, a series of radial blades mounted in axial housings produced in the periphery of said disc, a series of shoes disposed between said blades in order to maintain the spacing between said blades and to constitute the internal profile of the annular stream of fluid circulating from upstream to downstream of said stage, means for fixing said shoes on said disc and means for axially retaining said vanes in their respective housings, each of said shoes having an external wall defining the internal profile of the vein and remote from the periphery of said disc, the axial ends of said external wall being located substantially in the planes of the front and rear faces of said disc.
  • turbomachine rotor is particularly used in large diameter stages, because it is imperative, on the one hand, to limit the diameter of the disc carrying the blades because of the considerable centrifugal force obtained at high speeds of rotation of the turbomachine, and, on the other hand, to increase the internal diameter of the annular stream of fluid flowing from upstream to downstream of the stage so as to have a substantially uniform fluid flow speed throughout the section of the stream.
  • the British document GB-2 006 883 in particular shows a rotor for a turbomachine stage of the type mentioned above.
  • the shoe described in this document comprises, at the rear, an upwardly directed hook which cooperates with a groove provided in correspondence in a first retaining ring fixed by a bayonet device on the rear face of the disc, and it comprises, at the front, a rib which extends towards the axis of the disc and which cooperates with the front face of the disc to prevent the axial displacement of the shoe towards the back.
  • a second retaining ring, fixed by bolting, is provided on the front face of the disc to connect the front end of the shoe with said disc.
  • the shoe In this method of construction and attachment, the shoe must have an internal wall which is only partially supported on the periphery of the disc so that the rear hook can be engaged in the corresponding groove of the first retaining ring by pivoting. shoe on the periphery of the disc. This results in a complex configuration of the hoof and an increase in weight.
  • the bayonet device used to fix the first retaining ring on the rear face of the disc requires delicate machining of the disc and of this ring.
  • the object of the present invention is to overcome these drawbacks and to propose a turbomachine stage of the type mentioned in which the shoe has a simpler configuration and in which the means for fixing the shoes on the disc are different and easy to produce.
  • each of said shoes has a front wall and a rear wall which extend radially towards the axis of the turbomachine from said axial ends of the outer wall so as to cover at least partially the front and rear faces of said disc and, by the fact that the means for fixing said shoes to said disc comprise, for each of said shoes, at least one front hook extending axially towards the rear from its front wall and at minus a rear hook which extends forward from its rear wall, and grooves formed in said disc in correspondence with said hooks, said grooves extending between the ends of the mounting housings of the two blades adjacent to said shoe , said grooves and said hooks being shaped and dimensioned so that said shoe can be mounted by presentation to the right of a mounting housing and sliding of said shoe in the plane of the disc.
  • the grooves and the hooks cooperate with each other to retain the shoe radially during the rotation of the disc.
  • the front and rear walls of the shoe cooperate with the disc to axially retain the shoe forwards and backwards.
  • the grooves are preferably circular in shape, the center of which is on the axis of the turbomachine. But this is not compulsory. Their shape must allow the mounting of the shoe by sliding it in the plane of the disc.
  • each shoe has at least one cleat which extends from its rear wall to at least partially cover a mounting housing adjacent to said shoe and has a locking tab extending radially towards the axis of the turbomachine to from its front wall, said locking tab being spaced from the front face of said disc and cooperating with an additional groove of the disc, the axial retention means of said series of blades being formed, upstream of said stage, by said tabs and , downstream of said stage, by an annular segment interposed between the front face of said disc and said locking tabs.
  • each shoe also has a central partition which extends from its external wall towards the periphery of the disc and is substantially parallel to the plane of the adjacent blades, said partition having a slot in the vicinity of said external wall, and it is equipped with a vibration damper formed by a spring leaf passing through said slot and damping plates provided at the ends of said spring leaf.
  • each shoe also has additional walls extending from the underside of the external wall and serving as a stop for shock absorber pads.
  • the drawing shows a rotor 1 of a stage of a turbomachine, in which the blades 2 are fixed in axial housings 3 provided on the periphery 4 of a disc 5.
  • the blades 2 are of the type without platform.
  • the internal profile of the stream of fluid flowing upstream downstream of the blade stage is obtained by the external wall 6 of shoes 7 arranged between the blades 2 and fixed to the disc 5. Each shoe 7 also maintains the spacing between two adjacent blades 2.
  • each shoe 7 has a front wall 8 which extends radially towards the axis of the turbomachine from the front end 9 of the external wall 6 and which at least partially covers the front face 10 of the disc 5. It also has a rear wall 11 which extends radially towards the axis of the turbomachine from the rear end 12 of the external wall 6 and which at least partially covers the rear face 13 of the disc 5 .
  • the portions of the front 8 and rear 11 walls which cover the front 10 and rear 13 faces of the disc 5 have each at least one hook which extends axially towards the disc 5 and cooperates with a groove formed in correspondence in the wall of the disc 5.
  • the front wall 8 thus comprises at least one front hook 14 which extends towards the rear and cooperates with the groove 15, and the rear wall 11 has at least one hook 16 which extends forward and cooperates with the groove 17.
  • the front grooves 15 and rear 17 of the disc 5 extend between the axial housings 3 used for mounting the two blades 2 adjacent to the corresponding shoe 7.
  • the circumferential width of the hooks 14 and 16 must be less than the width of an axial housing 3 in line with the grooves 15 and 17 to allow the mounting of the stage vanes 1 as explained below.
  • the rear wall 11 of the shoe 7 is extended in the direction of the circumference of the disc 5 by at least one cleat 18 which at least partially closes the rear end of a mounting housing 3 adjacent to said shoe 7.
  • a stopper 18 is provided on each side of the shoe 7.
  • the shoe 7 also has on its front face a locking tab 19 which extends towards the axis of the turbomachine and which is spaced from the front face 10 of the disc 5. This locking tab 19 cooperates with an additional groove 20.
  • An annular segment 21 is interposed between the front face 10 of the disc 5 and all of the locking tabs 19 of the shoes 7.
  • the annular segment 21 at least partially covers the front ends housings 3 for mounting the blades 2.
  • the annular segment 21 and the tabs 18 of the shoes 7 thus constitute the means of axial retention of the blades 2.
  • Each shoe 7 also has on the underside of its outer wall 6 a central partition 22 which extends parallel to the adjacent vanes 2 towards the periphery 4 of the disc 5.
  • This central partition 22 has in the vicinity of the outer wall 6 a slot 23 through which passes a spring leaf 24 provided at each of its ends with damper plates 25.
  • the assembly 26 constituted by the spring leaf 24 and damper plates 25 constitutes a vibration damper.
  • the leaf spring 24 is of curvilinear shape, so that, when the rotor 1 stops, the plates 25 are in the vicinity of the periphery 4 of the disc 5. The action of the centrifugal force will force the plates 25 to move away from the periphery 4 of the disc 5 against the bending force of the spring leaf 24. The plates 25 then come to bear on the adjacent vanes 2 thus promoting vibration damping.
  • Each shoe 7 also has additional walls 27 which extend from the underside of the external wall 6 perpendicular to the central partition 22 and which serve as a stop for the plates 25.
  • the shoe 7 is made of a composite material.
  • the vibration damper 25 can be produced by mounting the damper plates 25 on the spring leaf 24, but it can also be produced in one piece, in which case it will be put in place when the composite shoe is manufactured. .
  • the blade 2 is mounted in a housing 3 by sliding it in a direction parallel to the axis of this housing 3; the shoe 7 is mounted by positioning its base in the housing 3 adjacent to the already mounted blade 2, by sliding it in the plane of the disc 5, the two hooks 14 and 16 being introduced into the corresponding grooves 15 and 17, and by pressing it against the already mounted blade 2.
  • the annular segment 21 is rotated between the front face 10 of the disc 5 and the locking tabs 19 after each assembly of a blade-shoe pair. We continue this assembly operation until the last dawn 2.

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)
EP91403182A 1990-11-28 1991-11-26 Gebläserotor mit Schaufeln ohne Plattform und Stromlinien rekonstruierenden Füllstücken Expired - Lifetime EP0488874B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR909014850A FR2669686B1 (fr) 1990-11-28 1990-11-28 Rotor de soufflante avec aubes sans plates-formes et sabots reconstituant le profil de veine.
FR9014850 1990-11-28

Publications (2)

Publication Number Publication Date
EP0488874A1 true EP0488874A1 (de) 1992-06-03
EP0488874B1 EP0488874B1 (de) 1994-11-09

Family

ID=9402665

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91403182A Expired - Lifetime EP0488874B1 (de) 1990-11-28 1991-11-26 Gebläserotor mit Schaufeln ohne Plattform und Stromlinien rekonstruierenden Füllstücken

Country Status (4)

Country Link
US (1) US5161949A (de)
EP (1) EP0488874B1 (de)
DE (1) DE69105099T2 (de)
FR (1) FR2669686B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993021425A1 (en) * 1992-04-16 1993-10-28 Rolls-Royce Plc Rotors for gas turbine engines
FR2716502A1 (fr) * 1994-02-23 1995-08-25 Snecma Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires.
WO2014140449A1 (fr) * 2013-03-15 2014-09-18 Snecma Soufflante de turbomoteur a flux multiple, et turbomoteur equipe d'une telle soufflante

Families Citing this family (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
FR2739136B1 (fr) * 1995-09-21 1997-10-31 Snecma Agencement amortissant pour des aubes de rotor
FR2739135B1 (fr) * 1995-09-21 1997-10-31 Snecma Agencement amortisseur monte entre des aubes de rotor
US6447250B1 (en) * 2000-11-27 2002-09-10 General Electric Company Non-integral fan platform
JP4807113B2 (ja) * 2006-03-14 2011-11-02 株式会社Ｉｈｉ ファンのダブテール構造
GB0614640D0 (en) * 2006-07-22 2006-08-30 Rolls Royce Plc An annulus filler seal
US7762781B1 (en) 2007-03-06 2010-07-27 Florida Turbine Technologies, Inc. Composite blade and platform assembly
US7766609B1 (en) * 2007-05-24 2010-08-03 Florida Turbine Technologies, Inc. Turbine vane endwall with float wall heat shield
CN101255873B (zh) * 2008-02-28 2010-06-09 大连海事大学 压气机动叶叶尖小翼
GB0814718D0 (en) * 2008-08-13 2008-09-17 Rolls Royce Plc Annulus filler
US8137072B2 (en) * 2008-10-31 2012-03-20 Solar Turbines Inc. Turbine blade including a seal pocket
US8393869B2 (en) * 2008-12-19 2013-03-12 Solar Turbines Inc. Turbine blade assembly including a damper
US8616849B2 (en) * 2009-02-18 2013-12-31 Pratt & Whitney Canada Corp. Fan blade platform
US8568102B2 (en) 2009-02-18 2013-10-29 Pratt & Whitney Canada Corp. Fan blade anti-fretting insert
US8066479B2 (en) * 2010-04-05 2011-11-29 Pratt & Whitney Rocketdyne, Inc. Non-integral platform and damper for an airfoil
FR2965843B1 (fr) * 2010-10-06 2012-11-09 Snecma Rotor pour turbomachine
US8827651B2 (en) 2010-11-01 2014-09-09 Rolls-Royce Plc Annulus filler
US10036261B2 (en) * 2012-04-30 2018-07-31 United Technologies Corporation Blade dovetail bottom
US9279332B2 (en) 2012-05-31 2016-03-08 Solar Turbines Incorporated Turbine damper
US9650901B2 (en) 2012-05-31 2017-05-16 Solar Turbines Incorporated Turbine damper
US9528376B2 (en) * 2012-09-13 2016-12-27 General Electric Company Compressor fairing segment
US9303519B2 (en) * 2012-10-31 2016-04-05 Solar Turbines Incorporated Damper for a turbine rotor assembly
US9347325B2 (en) * 2012-10-31 2016-05-24 Solar Turbines Incorporated Damper for a turbine rotor assembly
US10145268B2 (en) * 2013-03-15 2018-12-04 United Technologies Corporation Injection molded composite fan platform
FR3021691B1 (fr) * 2014-06-03 2016-06-24 Snecma Rotor pour turbomachine comportant des aubes a plates-formes raportees
US10197009B2 (en) * 2014-07-30 2019-02-05 Pratt & Whitney Canada Corp. Gas turbine engine ejector
US9995162B2 (en) * 2014-10-20 2018-06-12 United Technologies Corporation Seal and clip-on damper system and device
US10156151B2 (en) 2014-10-23 2018-12-18 Rolls-Royce North American Technologies Inc. Composite annulus filler
FR3035677B1 (fr) * 2015-04-29 2017-05-12 Snecma Aube munie de plateformes possedant des portions d'accrochage
FR3038653B1 (fr) * 2015-07-08 2017-08-04 Snecma Assemblage d'une plateforme rapportee d'aube de soufflante sur un disque de soufflante
US10662784B2 (en) 2016-11-28 2020-05-26 Raytheon Technologies Corporation Damper with varying thickness for a blade
US10731479B2 (en) * 2017-01-03 2020-08-04 Raytheon Technologies Corporation Blade platform with damper restraint
US10677073B2 (en) 2017-01-03 2020-06-09 Raytheon Technologies Corporation Blade platform with damper restraint
ES2891030T3 (es) * 2017-10-27 2022-01-25 MTU Aero Engines AG Combinación para sellar un espacio entre las paletas de una turbomaquinaria y reducir las vibraciones de las paletas de la turbomaquinaria
FR3091563B1 (fr) * 2019-01-04 2023-01-20 Safran Aircraft Engines Joint d’étanchéité amélioré de plateforme inter-aubes
CN114439551B (zh) * 2020-10-30 2024-05-10 中国航发商用航空发动机有限责任公司 航空发动机
CN113217461B (zh) * 2021-05-12 2022-08-16 中南大学 一种叶片、其造型方法和制造方法及压气机
FR3126446B1 (fr) * 2021-09-01 2024-07-12 Safran Aircraft Engines Amortisseur déformable pour roue mobile de turbomachine
US20230194096A1 (en) * 2021-12-17 2023-06-22 Pratt & Whitney Canada Corp. Exhaust system for a gas turbine engine and method for using same

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1134548A (fr) * 1954-08-12 1957-04-12 Rolls Royce Compresseurs et turbines
FR1579923A (de) * 1968-08-09 1969-08-29
GB1259750A (en) * 1970-07-23 1972-01-12 Rolls Royce Rotor for a fluid flow machine
FR2164196A5 (de) * 1971-12-02 1973-07-27 Gen Electric
GB2006883A (en) * 1977-10-27 1979-05-10 Rolls Royce Fan or Compressor Rotor Stage

Family Cites Families (5)

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Publication number Priority date Publication date Assignee Title
US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly
GB981476A (en) * 1963-11-04 1965-01-27 Rolls Royce Gas turbine engine vane assembly
GB2171151B (en) * 1985-02-20 1988-05-18 Rolls Royce Rotors for gas turbine engines
FR2639402B1 (fr) * 1988-11-23 1990-12-28 Snecma Disque ailete de rotor de turbomachine
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1134548A (fr) * 1954-08-12 1957-04-12 Rolls Royce Compresseurs et turbines
FR1579923A (de) * 1968-08-09 1969-08-29
GB1259750A (en) * 1970-07-23 1972-01-12 Rolls Royce Rotor for a fluid flow machine
FR2164196A5 (de) * 1971-12-02 1973-07-27 Gen Electric
GB2006883A (en) * 1977-10-27 1979-05-10 Rolls Royce Fan or Compressor Rotor Stage

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993021425A1 (en) * 1992-04-16 1993-10-28 Rolls-Royce Plc Rotors for gas turbine engines
US5466125A (en) * 1992-04-16 1995-11-14 Rolls-Royce Plc Rotors for gas turbine engines
FR2716502A1 (fr) * 1994-02-23 1995-08-25 Snecma Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires.
EP0669451A1 (de) * 1994-02-23 1995-08-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Abdichtung zwischen den Schaufeln und den zwischenliegenden Plattformen
US5520514A (en) * 1994-02-23 1996-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Sealing lining between vanes and intermediate platforms
WO2014140449A1 (fr) * 2013-03-15 2014-09-18 Snecma Soufflante de turbomoteur a flux multiple, et turbomoteur equipe d'une telle soufflante
FR3003294A1 (fr) * 2013-03-15 2014-09-19 Snecma Soufflante de turbomoteur a flux multiple, et turbomoteur equipe d'une telle soufflante
GB2526475A (en) * 2013-03-15 2015-11-25 Snecma Multiflow turbojet engine fan and turbojet engine fitted with such a fan
GB2526475B (en) * 2013-03-15 2018-05-16 Snecma Fan for a multi-flow turboshaft engine, and turboshaft engine equipped with such a fan

Also Published As

Publication number Publication date
DE69105099D1 (de) 1994-12-15
FR2669686B1 (fr) 1994-09-02
FR2669686A1 (fr) 1992-05-29
US5161949A (en) 1992-11-10
DE69105099T2 (de) 1995-04-20
EP0488874B1 (de) 1994-11-09

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