EP1134361A1 - Turbomachine comportant un dispositif de suppression des vibrations - Google Patents
Turbomachine comportant un dispositif de suppression des vibrations Download PDFInfo
- Publication number
- EP1134361A1 EP1134361A1 EP01400573A EP01400573A EP1134361A1 EP 1134361 A1 EP1134361 A1 EP 1134361A1 EP 01400573 A EP01400573 A EP 01400573A EP 01400573 A EP01400573 A EP 01400573A EP 1134361 A1 EP1134361 A1 EP 1134361A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cavity
- wall
- turbomachine
- turbomachine according
- symmetry
- 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
Links
Images
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 subject of the present invention is a turbomachine of the type comprising a plurality of blades placed in the path of an air stream or gas.
- one or more cavities are provided outside of the air stream and communicate with it by through a plurality of holes in a wall symmetrical along the axis of the turbomachine, delimiting the air stream.
- a pipeline with a relief valve is generally connected to the cavity to allow, in operating mode partial of the turbomachine, a sampling of part of the air flow for discharge to the outside in order to increase the stability of the operation of the turbomachine or for an auxiliary need.
- the volume of the cavity must therefore be sufficient to allow a regular withdrawal in operation.
- the air or gas from the air stream in circulation in front of the cavity can trigger, for certain ranges of velocity, an acoustic resonance of the cavity due to a shear of the boundary layer.
- This resonance is favored by the structure, generally symmetrical to the cavity.
- the cavity can indeed be symmetrical with respect to the axis of the turbomachine or even include patterns, bosses or others, regularly distributed around its periphery and thus achieving cyclical symmetry.
- the break in symmetry caused by the connection of the air sampling pipe for the valve discharge or for cooling the discs and turbine blades of the turbomachine, is insufficient to avoid certain setting up acoustic resonance of the cavity.
- the subject of the invention is therefore a turbomachine comprising means for suppressing or preventing the birth of waves rotating acoustics in the previously mentioned cavity and so to eliminate the drawbacks due to the acoustic resonances at inside 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 general symmetrical structure, whether it is a symmetry along the axis of the turbomachine or of cyclic symmetry. Means of rupture of symmetry are provided inside said cavity.
- the means of breaking symmetry can be made of different ways.
- the symmetry breaking means includes a spacer device mounted in a pipe connected to the cavity, so as to partially protrusion inside the cavity.
- the spacer device is preferably mounted with a tightening preload in said pipe so as to limit the vibrations in operation.
- the spacer device can for example advantageously consist of a portion of tube pressed from the outside into the pipeline.
- the means of rupture of symmetry include a localized area of the cavity, presenting a convexity directed towards the interior of the cavity.
- Convexity can be obtained for example by stamping located on the outer wall of the cavity. or on the inside wall of the cavity.
- the means of rupture of symmetry include an element fixed at a determined location on the inner face of the outer wall of the cavity, for example, a portion of sheet metal welded to the internal face of the external wall of the cavity or on the inner wall of the cavity.
- the means of rupture of symmetry include a screw passing through the outer wall of the cavity and protruding into the interior of the cavity.
- the turbomachine of the invention has an air inlet 1 provided with a first set rotary blades 2.
- the outer wall 3 of the turbomachine has a pipe connection 4 for a part of the air discharge pipe of the flow.
- the wall 10 delimits the air stream 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 blades rotary 6, between the wall 10 and an outer wall 12.
- the wall 10 has on its periphery a plurality of orifices 13 putting in communicating the air stream with the cavity 11. These orifices 13 can be in the form of slots, lunules or grooves circular.
- the cavity 11 could present a cyclical symmetry, that is to say include a plurality of patterns or other elements regularly arranged inside of the cavity and can thus give rise to a resonance acoustics of the cavity.
- the valve 14 is mounted downstream of the tubing 4, itself integral with the wall 12 at a determined location in the cavity 11.
- the discharge valve 14 allows, when open, to take a part of the air flow in order to reject it outside so as to improve the operation of the turbomachine for certain regimes.
- the circulation of the air stream can trigger, passing in front of orifices 13 and for certain speed ranges, the resonance of the cavity 11 by shear of the boundary layer.
- the birth of acoustic waves is prevented rotating in the cavity 11 by carrying out a voluntary rupture and significant of the symmetry with respect to the axis of the cavity 11, in addition to the break in symmetry which already exists due to the existence of the tubing 4.
- the means of rupture of symmetry include a portion of tube 15 forced into with a preload for tightening in the tubing 4.
- the mounting is done from the outside, the tube portion 15 being pushed in until a radial shoulder 16 formed on the outer edge of the portion of tube 15, comes into abutment on a conical portion 17 of the tubing 4, so as to properly define the final position of the portion of tube 15.
- the tube portion 15 partly protrudes inside the cavity 11 beyond the right of the wall 12 without however going as far as contact with the internal wall 10, so as to avoid unduly disturbing the air flow in the cavity 11 when the discharge valve 14 is open.
- the embodiment illustrated in FIG. 3 does not differ from the mode of FIG. 2 only by the fact that the external wall 12 has a localized convex area 18 whose convexity is directed inward of the cavity 11.
- This zone is preferably obtained by simple localized stamping of the sheet forming the outer wall 12.
- This stamped area 18 therefore causes an additional break in symmetry, in addition to that which already exists when a tube 4, as illustrated on FIG. 2 is located at another location in the cavity 11.
- the embodiment illustrated in FIG. 4 differs from the mode of embodiment of FIG. 3 by the fact that a portion of sheet metal 19 disposed radially is fixed by welding on the internal face of the external wall 12 of the cavity 11.
- the portion of welded sheet metal 19 thus projects inside the cavity 11 and prevents the birth of acoustic waves rotating in the cavity 11.
- the tubing 4 can also be provided at another location on the cavity 11.
- the dimensions of the portion of welded sheet metal 19, of square shape in the mode illustrated as an example in FIG. 4 are such that said portion of welded sheet 19 extends from the outer wall 12 in direction of the inner wall 10 without however going so far as to enter contact with the latter.
- the portion of welded sheet 19 could also be fixed on the inner wall 10 extending to the opposite towards the outer wall 12.
- FIG. 5 differs from the mode of embodiment of FIG. 4 by the fact that a screw 20 passes through the wall outside 12 of the cavity 11 by projecting inside said cavity 11 over a certain length.
- the outer wall 12 has a zone 13 provided with a thread which can cooperate with the screw thread 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 wall interior 10 in a radial plane without however coming into contact with the inner wall 10.
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)
- Suspension Of Electric Lines Or Cables (AREA)
- Springs (AREA)
Abstract
Description
- la figure 1 est une vue extérieure de côté d'une turbomachine;
- la figure 2 est une vue partielle en coupe de la turbomachine illustrée sur la figure 1, montrant un premier mode de réalisation de l'invention;
- la figure 3 est une vue en coupe analogue à la figure 2, montrant un deuxième mode de réalisation de l'invention;
- la figure 4 est une vue en coupe analogue à la figure 2, montrant un troisième mode de réalisation de l'invention; et
- la figure 5 est une vue en coupe partielle analogue à la figure 2, montrant un quatrième mode de réalisation de l'invention.
Claims (10)
- Turbomachine du type comportant une pluralité d'aubages placés sur le trajet d'une veine d'air ou de gaz délimitée par une paroi symétrique selon l'axe de la turbomachine, ladite paroi présentant des orifices (13) communiquant avec une cavité (11) extérieure à la veine d'air, de structure générale symétrique, axiale ou cyclique,
caractérisée par le fait que des moyens de rupture de symétrie sont prévus à l'intérieur de ladite cavité. - Turbomachine selon la revendication 1, caractérisée par le fait que les moyens de rupture de symétrie comprennent un dispositif d'entretoise monté dans une canalisation reliée à la cavité, de façon à faire en partie saillie à l'intérieur de la cavité.
- Turbomachine selon la revendication 2, caractérisée par le fait que le dispositif d'entretoise est monté avec une précontrainte de serrage dans ladite canalisation.
- Turbomachine selon les revendications 2 ou 3, caractérisée par le fait que le dispositif d'entretoise est constitué d'une portion de tube (15).
- Turbomachine selon la revendication 1, caractérisée par le fait que les moyens de rupture de symétrie comprennent une zone localisée (18) de la cavité, présentant une convexité dirigée vers l'intérieur de la cavité.
- Turbomachine selon la revendication 5, caractérisée par le fait que la convexité a été obtenue par emboutissage localisé de la paroi extérieure de la cavité.
- Turbomachine selon la revendication 1, caractérisée par le fait que les moyens de rupture de symétrie comprennent un élément (19) fixé à un endroit déterminé sur la face interne de la paroi extérieure de la cavité.
- Turbomachine selon la revendication 1, caractérisée par le fait que les moyens de rupture de symétrie comprennent un élément fixé à un endroit déterminé sur la paroi intérieure de la cavité.
- Turbomachine selon les revendications 7 ou 8, caractérisée par le fait que ledit élément est une portion de tôle soudée sur la paroi précitée de la cavité.
- Turbomachine selon la revendication 1, caractérisée par le fait que les moyens de rupture de symétrie comprennent une vis (20) traversant la paroi extérieure de la cavité et faisant saillie à l'intérieur de la cavité.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0003490 | 2000-03-17 | ||
FR0003490A FR2806442B1 (fr) | 2000-03-17 | 2000-03-17 | Turbomachine comportant un dispositif de suppression des vibrations dues aux resonances acoustiques |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1134361A1 true EP1134361A1 (fr) | 2001-09-19 |
EP1134361B1 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 (fr) |
EP (1) | EP1134361B1 (fr) |
JP (1) | JP4719368B2 (fr) |
AT (1) | ATE328192T1 (fr) |
CA (1) | CA2341839C (fr) |
CY (1) | CY1105534T1 (fr) |
DE (1) | DE60120017T2 (fr) |
DK (1) | DK1134361T3 (fr) |
ES (1) | ES2261357T3 (fr) |
FR (1) | FR2806442B1 (fr) |
PT (1) | PT1134361E (fr) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR101293678B1 (ko) | 2005-02-23 | 2013-08-06 | 커민스 터보 테크놀러지스 리미티드 | 압축기 |
Citations (9)
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 |
EP0350427A2 (fr) * | 1988-07-05 | 1990-01-10 | Pratt & Whitney Canada, Inc. | Pales d'entrée d'un compresseur radial à débit variable |
US4981018A (en) * | 1989-05-18 | 1991-01-01 | Sundstrand Corporation | Compressor shroud air bleed passages |
US5236301A (en) * | 1991-12-23 | 1993-08-17 | Allied-Signal Inc. | Centrifugal compressor |
EP0573895A1 (fr) * | 1992-06-12 | 1993-12-15 | A.G. Kühnle, Kopp & Kausch | Turbocompresseur avec un compresseur radial |
US5314300A (en) * | 1992-01-13 | 1994-05-24 | Fasco Industries, Inc. | Noise control device for centrifugal blower |
US5399064A (en) * | 1992-12-23 | 1995-03-21 | Caterpillar Inc. | Turbocharger having reduced noise emissions |
DE19727139A1 (de) * | 1997-06-26 | 1999-01-07 | Daimler Benz Ag | Verdichter eines Abgasturboladers |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
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 |
DE59206751D1 (de) * | 1992-10-17 | 1996-08-14 | Asea Brown Boveri | Stabilisierungseinrichtung zur Kennfelderweiterung eines Verdichters |
US6183195B1 (en) * | 1999-02-04 | 2001-02-06 | Pratt & Whitney Canada Corp. | Single slot impeller bleed |
-
2000
- 2000-03-17 FR FR0003490A patent/FR2806442B1/fr not_active Expired - Fee Related
-
2001
- 2001-03-06 DE DE60120017T patent/DE60120017T2/de not_active Expired - Lifetime
- 2001-03-06 DK DK01400573T patent/DK1134361T3/da active
- 2001-03-06 EP EP01400573A patent/EP1134361B1/fr not_active Expired - Lifetime
- 2001-03-06 ES ES01400573T patent/ES2261357T3/es not_active Expired - Lifetime
- 2001-03-06 PT PT01400573T patent/PT1134361E/pt unknown
- 2001-03-06 AT AT01400573T patent/ATE328192T1/de not_active IP Right Cessation
- 2001-03-15 US US09/808,189 patent/US6450761B2/en not_active Expired - Lifetime
- 2001-03-16 CA CA002341839A patent/CA2341839C/fr not_active Expired - Fee Related
- 2001-03-16 JP JP2001075980A patent/JP4719368B2/ja not_active Expired - Lifetime
-
2006
- 2006-08-30 CY CY20061101225T patent/CY1105534T1/el unknown
Patent Citations (9)
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 |
EP0350427A2 (fr) * | 1988-07-05 | 1990-01-10 | Pratt & Whitney Canada, Inc. | Pales d'entrée d'un compresseur radial à débit variable |
US4981018A (en) * | 1989-05-18 | 1991-01-01 | Sundstrand Corporation | Compressor shroud air bleed passages |
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 |
EP0573895A1 (fr) * | 1992-06-12 | 1993-12-15 | A.G. Kühnle, Kopp & Kausch | Turbocompresseur avec un compresseur radial |
US5399064A (en) * | 1992-12-23 | 1995-03-21 | Caterpillar Inc. | Turbocharger having reduced noise emissions |
DE19727139A1 (de) * | 1997-06-26 | 1999-01-07 | Daimler Benz Ag | Verdichter eines Abgasturboladers |
Also Published As
Publication number | Publication date |
---|---|
EP1134361B1 (fr) | 2006-05-31 |
JP2001317497A (ja) | 2001-11-16 |
JP4719368B2 (ja) | 2011-07-06 |
FR2806442B1 (fr) | 2003-01-10 |
PT1134361E (pt) | 2006-09-29 |
US20010036402A1 (en) | 2001-11-01 |
CY1105534T1 (el) | 2010-07-28 |
DK1134361T3 (da) | 2006-10-02 |
ATE328192T1 (de) | 2006-06-15 |
FR2806442A1 (fr) | 2001-09-21 |
CA2341839A1 (fr) | 2001-09-17 |
CA2341839C (fr) | 2008-09-23 |
DE60120017T2 (de) | 2006-10-05 |
DE60120017D1 (de) | 2006-07-06 |
ES2261357T3 (es) | 2006-11-16 |
US6450761B2 (en) | 2002-09-17 |
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