EP1134361B1 - Turbomachine comportant un dispositif de suppression des vibrations - Google Patents

Turbomachine comportant un dispositif de suppression des vibrations Download PDF

Info

Publication number
EP1134361B1
EP1134361B1 EP01400573A EP01400573A EP1134361B1 EP 1134361 B1 EP1134361 B1 EP 1134361B1 EP 01400573 A EP01400573 A EP 01400573A EP 01400573 A EP01400573 A EP 01400573A EP 1134361 B1 EP1134361 B1 EP 1134361B1
Authority
EP
European Patent Office
Prior art keywords
cavity
wall
symmetry
turbomachine
turbomachine according
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
EP01400573A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1134361A1 (fr
Inventor
Bernard Lalanne
René Rodellar
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 Helicopter Engines SAS
Original Assignee
Turbomeca 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 Turbomeca SA filed Critical Turbomeca SA
Publication of EP1134361A1 publication Critical patent/EP1134361A1/fr
Application granted granted Critical
Publication of EP1134361B1 publication Critical patent/EP1134361B1/fr
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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/105—Final actuators by passing part of the fluid
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/663—Sound attenuation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the present invention relates to a turbomachine of the type comprising a plurality of blades placed in the path of a stream of air or gas.
  • one or more cavities are provided outside the airstream and communicate with it through a plurality of orifices in a symmetrical wall along the axis of the turbomachine , defining the vein of air.
  • a pipe comprising a discharge valve is generally connected to the cavity in order to allow, in partial operating mode of the turbomachine, a part of the air flow for outside discharge to be taken in order to increase the stability of the operation of the turbomachine or for an auxiliary need.
  • the volume of the cavity must be sufficient to allow a regular sampling operation.
  • the air or the gas of the air stream circulating in front of the cavity can trigger, for certain speed ranges, an acoustic resonance of the cavity due to shearing of the boundary layer.
  • the cavity may indeed be symmetrical with respect to the axis of the turbomachine or may comprise patterns, bosses or the like, regularly distributed over its periphery and thus achieving a cyclic symmetry.
  • the symmetry breaking caused by the tapping of the air bleed pipe for the discharge valve or for the cooling of the turbine blades and discs of the turbomachine, is insufficient to avoid a certain setting acoustic resonance of the cavity.
  • US-A-5,399,064 discloses a turbocharger for an internal combustion engine which comprises means for reducing noise resulting from vibrations in the compressor by establishing a tortuous path for the air flow in an annular chamber which surrounds the compressor.
  • a plurality of deflectors forces the flow of air passing through an annular chamber to follow a tortuous path.
  • the set of deflectors has a cyclic symmetry being arranged symmetrically about the axis of rotation of the compressor.
  • the annular chamber described in this document is open to the air intake which contributes to obtaining the reduction of noise by the tortuous flow of air in the annular chamber
  • the invention relates to a turbomachine comprising means for eliminating or preventing the birth of rotating acoustic waves in the cavity mentioned above and thus to eliminate the disadvantages due to acoustic resonances within said cavity.
  • the turbomachine according to the invention is of the type comprising a plurality of blades placed in the path of an air or gas stream delimited by a symmetrical wall along the axis of the turbomachine.
  • Said wall has orifices communicating with a cavity external to the air stream, of symmetrical general structure, whether it is a symmetry along the axis of the turbomachine or a cyclic symmetry.
  • Means of symmetry breaking are provided inside said cavity.
  • the symmetry breaking means can be made in different ways.
  • the symmetry breaking means comprise a spacer device mounted in a pipe connected to the cavity, so as to partially protrude inside the cavity.
  • the spacer device is preferably mounted with a clamping preload in said pipe so as to limit vibration during operation.
  • the spacer device may, for example, advantageously consist of a portion of tube pushed in from the outside into the pipe
  • the symmetry breaking means comprise a localized area of the cavity, having a convexity directed towards the inside of the cavity.
  • the convexity can be obtained for example by localized stamping of the outer wall of the cavity or on the inner wall of the cavity.
  • the symmetry breaking means comprise an element fixed at a determined location on the internal face of the outer wall of the cavity, for example, a portion of sheet welded to the inner face of the cavity. the outer wall of the cavity or on the inner wall of the cavity.
  • the symmetry breaking means comprise a screw passing through the outer wall of the cavity and projecting inside the cavity.
  • the turbomachine of the invention has an air inlet 1 provided with a first set of rotary blades 2.
  • the outer wall 3 of the turbomachine has a connecting pipe 4 for a pipe of free discharge of a portion of the flow.
  • FIG. 2 In the cross-sectional view of FIG. 2, there is illustrated the rotary shaft 5 on which are mounted the rotary vanes 6 of a first compression section of the turbomachine.
  • the fixed hub 7 comprises fixed guide vanes 8.
  • the circulation of the air stream is shown schematically by the arrows 9.
  • the wall 10 delimits the air flow towards the outside and has a symmetrical configuration with respect to the axis of the turbomachine.
  • a cavity 11 of general structure also symmetrical with respect to the axis of the turbomachine is defined, substantially at the location of the rotating blades 6, between the wall 10 and an outer wall 12.
  • the wall 10 has on its periphery a plurality of orifices 13 placing in communication the air stream with the cavity 11. These orifices 13 may be formed in the form of slots, lunules or circular grooves.
  • the cavity 11 could have a cyclic symmetry, that is to say comprise a plurality of patterns or other elements regularly arranged inside the cavity and can thus give rise to an acoustic resonance of the cavity.
  • the valve 14 is mounted downstream of the tubing 4, itself secured to the wall 12 at a specific location of the cavity 11.
  • the discharge valve 14 allows, when it is open, to take a portion of the air flow to reject it outside so as to improve the operation of the turbomachine for certain speeds.
  • the circulation of the air stream can trigger, passing in front of the orifices 13 and for certain speed ranges, the resonance of the cavity 11 by shearing of the boundary layer.
  • the invention prevents the birth of rotating acoustic waves in the cavity 11 by achieving a voluntary and significant rupture of the symmetry with respect to the axis of the cavity 11, in addition to the symmetry rupture that already exists in the cavity 11. made of the existence of the tubing 4.
  • the symmetry breaking means comprise a portion of tube 15 force-fitted with a clamping preload in the tubing 4.
  • the assembly is done from the outside, the portion of tube 15 being pressed until a radial shoulder 16 formed on the outer edge of the tube portion 15, abuts a conical portion 17 of the tubing 4, so as to properly define the final position of the portion of tube 15.
  • the portion of the tube 15 projects in part inside the cavity 11 by going beyond the right of the wall 12 without however going to the contact with the inner wall 10, so as to avoid excessively disturbing the flow of air into the cavity 11 when the discharge valve 14 is open.
  • FIG. 3 differs from the embodiment of FIG. 2 only in that the outer wall 12 has a convex localized zone 18 whose convexity is directed towards the interior of the cavity 11. is preferably obtained by simple local stamping of the sheet constituting the outer wall 12. This stamped area 18 thus causes an additional break of symmetry, in addition to that which already exists when a pipe 4, as shown in Figure 2 is located at another location in the cavity 11.
  • the embodiment illustrated in FIG. 4 differs from the embodiment of FIG. 3 in that a radially disposed portion of sheet 19 is welded to the inner face of the outer wall 12 of the cavity 11. welded sheet 19 thus protrudes inside the cavity 11 and prevents the birth of rotating acoustic waves in the cavity 11.
  • the tubing 4 may also be provided at another location on the cavity 11.
  • the dimensions of the welded sheet metal portion 19, of square shape in the embodiment illustrated by way of example in FIG. 4 are such that said portion of welded sheet 19 extends from the outer wall 12 in the direction of the inner wall 10 without however going to come into contact with the latter.
  • the welded sheet metal portion 19 could also be fixed on the inner wall 10 while extending in the opposite direction towards the outer wall 12.
  • FIG. 5 differs from the embodiment of FIG. 4 in that a screw 20 passes through the outer wall 12 of the cavity 11 projecting inside said cavity 11 over a certain length.
  • the outer wall 12 has a zone 13 provided with a tapping which can cooperate with the thread of the screw 20 whose head 21 remains outside the outer wall 12.
  • the dimensions of the screw 20 projecting inside the cavity 11 are such that said screw extends towards the inner wall 10 in a radial plane without however coming into contact with the inner wall 10.
  • a symmetry breaking means has been introduced inside the symmetrical cavity that can prevent the birth of rotating acoustic waves and therefore to avoid the resonance of the cavity, regardless of the flow velocity in the turbomachine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Exhaust Silencers (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Vibration Prevention Devices (AREA)
  • Springs (AREA)
  • Suspension Of Electric Lines Or Cables (AREA)
EP01400573A 2000-03-17 2001-03-06 Turbomachine comportant un dispositif de suppression des vibrations Expired - Lifetime EP1134361B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0003490A FR2806442B1 (fr) 2000-03-17 2000-03-17 Turbomachine comportant un dispositif de suppression des vibrations dues aux resonances acoustiques
FR0003490 2000-03-17

Publications (2)

Publication Number Publication Date
EP1134361A1 EP1134361A1 (fr) 2001-09-19
EP1134361B1 true EP1134361B1 (fr) 2006-05-31

Family

ID=8848249

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01400573A Expired - Lifetime EP1134361B1 (fr) 2000-03-17 2001-03-06 Turbomachine comportant un dispositif de suppression des vibrations

Country Status (11)

Country Link
US (1) US6450761B2 (https=)
EP (1) EP1134361B1 (https=)
JP (1) JP4719368B2 (https=)
AT (1) ATE328192T1 (https=)
CA (1) CA2341839C (https=)
CY (1) CY1105534T1 (https=)
DE (1) DE60120017T2 (https=)
DK (1) DK1134361T3 (https=)
ES (1) ES2261357T3 (https=)
FR (1) FR2806442B1 (https=)
PT (1) PT1134361E (https=)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006090152A1 (en) * 2005-02-23 2006-08-31 Cummins Turbo Technologies Limited Compressor

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1132485A (en) * 1966-06-10 1968-11-06 Alexandr Georgievich Ivchenko A centrifugal compressor having a surge-elimination device
US4436481A (en) * 1981-06-15 1984-03-13 The Garrett Corporation Intake vortex whistle silencing apparatus and methods
JPS5968199U (ja) * 1982-10-29 1984-05-09 石川島播磨重工業株式会社 遠心式圧縮機の消音装置
US4844695A (en) * 1988-07-05 1989-07-04 Pratt & Whitney Canada Inc. Variable flow radial compressor inlet flow fences
US4981018A (en) * 1989-05-18 1991-01-01 Sundstrand Corporation Compressor shroud air bleed passages
US5246335A (en) * 1991-05-01 1993-09-21 Ishikawajima-Harimas Jukogyo Kabushiki Kaisha Compressor casing for turbocharger and assembly thereof
US5186601A (en) * 1991-09-16 1993-02-16 Sundstrand Corp. Compressor shroud air bleed arrangement
US5236301A (en) * 1991-12-23 1993-08-17 Allied-Signal Inc. Centrifugal compressor
US5314300A (en) * 1992-01-13 1994-05-24 Fasco Industries, Inc. Noise control device for centrifugal blower
DE4219249C2 (de) * 1992-06-12 1994-03-31 Kuehnle Kopp Kausch Ag Radialverdichter, insbesondere eines Turboladers
DE59206751D1 (de) * 1992-10-17 1996-08-14 Asea Brown Boveri Stabilisierungseinrichtung zur Kennfelderweiterung eines Verdichters
US5295785A (en) * 1992-12-23 1994-03-22 Caterpillar Inc. Turbocharger having reduced noise emissions
DE19727139C2 (de) * 1997-06-26 2000-04-20 Daimler Chrysler Ag Verdichter eines Abgasturboladers
US6183195B1 (en) * 1999-02-04 2001-02-06 Pratt & Whitney Canada Corp. Single slot impeller bleed

Also Published As

Publication number Publication date
DE60120017D1 (de) 2006-07-06
JP2001317497A (ja) 2001-11-16
US20010036402A1 (en) 2001-11-01
US6450761B2 (en) 2002-09-17
CA2341839C (fr) 2008-09-23
DK1134361T3 (da) 2006-10-02
ATE328192T1 (de) 2006-06-15
JP4719368B2 (ja) 2011-07-06
EP1134361A1 (fr) 2001-09-19
PT1134361E (pt) 2006-09-29
DE60120017T2 (de) 2006-10-05
FR2806442A1 (fr) 2001-09-21
FR2806442B1 (fr) 2003-01-10
ES2261357T3 (es) 2006-11-16
CY1105534T1 (el) 2010-07-28
CA2341839A1 (fr) 2001-09-17

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