EP0913585A1 - Compresseur - Google Patents

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Publication number
EP0913585A1
EP0913585A1 EP98307915A EP98307915A EP0913585A1 EP 0913585 A1 EP0913585 A1 EP 0913585A1 EP 98307915 A EP98307915 A EP 98307915A EP 98307915 A EP98307915 A EP 98307915A EP 0913585 A1 EP0913585 A1 EP 0913585A1
Authority
EP
European Patent Office
Prior art keywords
wall
tubular portion
annular passage
housing
inlet
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
EP98307915A
Other languages
German (de)
English (en)
Other versions
EP0913585B1 (fr
Inventor
William Kenneth Bruffell
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.)
Cummins Turbo Technologies Ltd
Original Assignee
Holset Engineering Co Ltd
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 Holset Engineering Co Ltd filed Critical Holset Engineering Co Ltd
Publication of EP0913585A1 publication Critical patent/EP0913585A1/fr
Application granted granted Critical
Publication of EP0913585B1 publication Critical patent/EP0913585B1/fr
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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids

Definitions

  • the present invention relates to a compressor and in particular to a compressor having an inlet structure the characteristics of which are such that noise levels external to the structure are reduced as compared with conventional inlet structures.
  • Turbochargers have been designed which incorporate a compressor inlet structure that has become known as a "map width enhanced” (MWE) structure.
  • MWE map width enhanced
  • the compressor inlet comprises two coaxial tubular inlet sections, the inner inlet section being shorter than the outer section and having an inner surface which is an extension of a surface of an inner wall of the compressor housing which faces vanes defined by an impeller wheel mounted within the housing.
  • An annular flow path is defined between the two tubular inlet sections, the annular flow path being open at the upstream end and opening at the downstream end through apertures communicating with the inner surface of the housing which faces the impeller wheel.
  • compressors incorporating MWE inlet structures tend to exhibit high levels of noise as compared with conventional structures in which an inlet is defined by a single tubular member.
  • This problem is addressed in British patent number 2256460 which discloses an MWE inlet which incorporates a noise-reduction baffle located upstream of the inner tubular section of the structure and retained within the upstream end of the outer tubular section of the structure.
  • the baffle thus closes off the otherwise open axial end of the annular flow path defined between the inner and outer tubular sections of the inlet structure, the flow path communicating with the inlet through slots defined between the baffle and the upstream end of the inner tubular section of the inlet structure.
  • the baffle may incorporate a conical section expanding outwards from the slots adjacent the upstream end of the inner tubular section of the structure.
  • a compressor comprising a housing defining an inlet and an outlet, and an impeller wheel rotatably mounted in the housing such that on rotation of the wheel gas within the inlet is moved to the outlet, the housing having an inner wall defining a surface located in close proximity to radially outer edges of vanes supported by the wheel, wherein the inlet is defined by a first tubular portion an inner surface of which is an extension of the said surface of the inner wall of the housing, a second tubular portion located radially outside the first portion to define an annular passage between the first and second portions, and an wall extending across the annular passage between the first and second tubular portions, the wall being located between upstream and downstream ends of the first tubular portion, sections of the passage on opposite sides of the wall communicating through at least one aperture, and at least one aperture being defined adjacent the wheel in the said surface of the inner wall of the housing to communicate with the annular passage
  • the wall which extends across the annular passage suppresses the propagation of noise along the annular passage.
  • the wall is located at or adjacent the position of an anti-node of a noise wave which may be expected to propagate along the annular passage during normal use of the compressor.
  • the wall may be in the form of a simple radially extending flange, or alternatively may extend in a direction inclined to the radial direction, and may be shaped to define a helix or other configuration with an axial component.
  • the inlet may comprise a wall defining an annular surface facing the annular passage and extending outwards from adjacent the upstream end of the first tubular portion to the upstream end of the second tubular portion, an aperture being defined between the upstream end of the first tubular portion and the radially inner edge of the annular surface.
  • the annular surface may be frusto-conical, and may extend in the radially outwards and upstream direction from adjacent the upstream end of the first tubular portion.
  • the inlet comprises a wall defining a tubular surface extending in the upstream direction from adjacent the upstream end of the first tubular portion.
  • a structure ensures that noise propagating in the upstream direction along the inlet is subjected to a rapid expansion at the upstream end of the tubular surface. This further reduces the noise output.
  • the wall extending across the annular passage may be in the form of flange extending radially outwards from the first tubular portion, at least one aperture being defined in radially outer portions of the flange adjacent the second tubular portion.
  • At least the first tubular portion and the wall extending across the annular passage may be defined by a sub-assembly which is received within the second tubular portion.
  • the sub-assembly may be retained in position within the second tubular portion by engagement between radially outer sections of the wall defining an annular surface and indentations defined within the second tubular portion.
  • the invention also provides a compressor comprising a housing defining an inlet and outlet, and an impeller wheel rotatably mounted in the housing such that on rotation of the wheel gas within the inlet is moved to the outlet, the housing having an inner wall defining a surface located in close proximity to radially outer edges of vanes supported by the wheel, wherein the inlet is defined by a first tubular portion an inner surface of which is an extension of the said surface of the inner wall of the housing, a second tubular portion located radially outside the first portion to define an annular passage between the first and second portions, a wall defining a surface facing the annular passage and extending from adjacent the upstream end of the first tubular portion to the upstream end of the second tubular portion, and a wall defining a tubular surface extending axially in the upstream direction from the upstream end of the first tubular portion, at least one first aperture being defined between the downstream end of the wall defining the tubular surface and the upstream end of the first tubular portion to communicate with the annular passage, at
  • the illustrated conventional inlet section of a compressor is not provided with a map width enhanced structure.
  • the illustrated structure comprises a housing 1 a tubular inlet portion 2 of which defines an inlet passage 3 which tapers in the downstream direction.
  • the inlet communicates with a cavity defined within the housing 1 within which an impeller wheel 4 is mounted to rotate about an axis indicated by broken line 5.
  • the wheel 4 supports vanes 6 the radially outer edges of which sweep across an inner surface 7 defined by the housing 1.
  • the inlet structure illustrated in Figure 2 comprises a tubular first portion 8 an inner surface of which is an extension of the inner housing surface 7 and a tubular second portion 9 which is located radially outside the first portion 8 to defined an annular passage 10 between the first and second portions.
  • Apertures 11 are formed through the housing at the downstream end of the tubular first portion 8, the apertures opening into the surface 7 defined by the housing. The radially outer edges of the vanes 6 sweep across the surface 7 in which the apertures 11 are formed.
  • the illustrated inlet structure is as described in Figure 14 of published British patent specification number 2256460.
  • the structure of Figure 3 is generally similar to that of Figure 2 except for the addition of a baffle located upstream of the tubular first portion 8 within the tubular second portion 9.
  • the baffle is a frusto-conical annular structure defining a conical surface 13 and a tubular portion 14 which is a tight fit within the tubular second portion 9 of the inlet structure.
  • a slot 15 is defined between the downstream end of the tubular surface 13 and the upstream end of the tubular first portion 8 of the inlet structure.
  • the illustrated embodiment comprises a tubular first portion 16 within which a moulded plastics assembly is received, that assembly incorporating elements which make up second, third, fourth and fifth portions of the of the overall assembly.
  • the second portion is in the form of a tubular portion 17 extending in the upstream direction from adjacent a slot 18, the functional purpose of the slot 18 being the same as that of the slot 11 as described above with reference to Figures 2 and 3.
  • An annular passage 19 is defined between the tubular first portion 16 and the tubular second portion 17.
  • the third portion is in the form of a wall 20 which extends radially outwards from the tubular second portion 17 across the passage 19.
  • the fourth portion is in the form of a frusto-conical wall 21 which extends in the radially outwards and upstream directions from the upstream end of the tubular second portion to an inner surface of the tubular first portion 16.
  • the angle of inclination of the wall 21 relative to the radial direction could be reversed such that the surface extends in the radially outwards and downstream directions.
  • the frusto-conical surface suppresses noise across a range of frequencies. If the wall was radial, noise suppression would occur only at one frequency.
  • the fifth portion is in the form of a tubular extension 22 of the tubular second portion 17. Slots 23 are formed between the tubular second and fifth portions, the slots 23 performing the function of the slot 15 as described with reference to Figure 3 above.
  • the wall 20 extends only part way across the annular passageway 17 but supports four lugs 24 which bear the inner surface of the tubular first portion 16.
  • the tubular passageway 19 is divided into two separate sections located on opposite sides of the wall 20, the wall being in effect apertured as a result of the four slots defined between each adjacent pair of lugs 24.
  • the direction of flow of air through the annular passageway 19 is a function of the flow rate through the inlet structure as a whole as is the case with any conventional MWE inlet structure.
  • the radially outer end of the conical fourth portion 21 supports four lugs 25 which define radially projecting ribs that are received in an annular groove formed within the tubular first portion 16.
  • FIG 8 this illustrates the performance in terms of output noise for three different inlet structures.
  • the upper full line trace represents the weighted sound pressure level resulting from the operation of a turbocharger compressor having an inlet structure as illustrated in Figure 3.
  • the lower broken-line trace shows the result of replacing the inlet structure of Figure 3 with the inlet structure as shown in Figures 4 to 7.
  • the intermediate full line trace represents the noise level recorded using an inlet structure of the type illustrated in Figures 4 to 7 but modified by removal of the fifth portion, that is the tubular extension 22.
  • structures as illustrated in both the modified and unmodified forms result in a substantial reduction in output noise, particularly at the higher frequencies.
  • the best performance is obtained using the unmodified inlet structure as illustrated in Figures 4 to 7, but significant improvements are also obtainable using the modified form of that inlet structure, that is without the tubular extension 22.
  • the presence of the apertured wall 20 significantly reduces the output noise as pressure waves travelling along the annular passage 19 from the slot 18 encounter a reduction in cross-sectional area in the passageway at the wall and then a sudden expansion in that cross-sectional area.
  • the wall 20 should be at the position of an antinode of noise wave passing along the annular passageway 19, but the position of antinodes is a function of the frequency of the noise in most applications.
  • An antinode will be located at a distance of one quarter of the wavelength of the noise wave as measured from the slot 18. This frequency varies over a wide range during normal operation of most devices.
  • the wall should be positioned approximately midway between the slot 18 and 23.
  • the wall 20 is ideally placed at an antinode of the noise wave to be expected given that operating speed.
  • the provision of the wall 20 in the otherwise conventional structure results in a substantial reduction in noise output.
  • a further improvement is achieved by providing the tubular extension 22. It is believed that the inclusion of such an extension is effective because a noise wave passing in the upstream direction encounters a sudden expansion in the cross-sectional area of the passageway along which it is transmitted when it reaches the upstream end of the extension 22.
  • providing the tubular extension 22 even in the absence of the wall 20 provides some reduction in the noise output.
  • the inlet structure illustrated in Figures 5, 6 and 7 may be a single piece moulding or may be an assembly of separately moulded pieces. Generally the assembly will be moulded from plastics material although a metal structure could be used.
  • the lugs 24 provided on the wall 20 served the purpose of locating the integrally moulded components within the compressor housing.
  • the lugs do not have an aerodynamic or noise reduction function however and can be omitted if alternative arrangements are made to ensure the correct relative location of the various components. Tests have been conducted after removal of the lugs 24 with no measurable increase in output noise.
  • the inner diameter of the tubular extension 22 is shown to be slightly larger than the inner tubular section 17. Differences between these diameters may affect noise output and aerodynamic performance and selection of the appropriate diameters for these components may be determined experimentally for specific applications. Similarly, the outside diameter of the wall 20, that is the wall of the wall 20 without the lugs 24, may be optimised best by experimentation for specific applications.
  • the structure illustrated in Figures 5 to 7 could be formed as an assembly of individual moulded components or cast components.
  • the wall 20 could be a separate component fitted onto the tubular portion 17.
  • the tubular portions 16 and 17 could form part of an integral casting defining an annular passageway into which an annular member defining the wall 20 could be inserted.
  • the conical wall 21 and tubular extension 22 could be formed as a single integral casting or moulding.
  • the illustrated sub-assembly was mounted within a tubular inlet to a compressor such that a radially outer surface 26 was engaged against the radially inner surface of a tubular portion of the inlet, an end surface 27 formed one side of a slot which was functionally equivalent to the slot 18 in the arrangement of Figures 4 to 7, a conical wall 28 was functionally equivalent to the conical portion 21 of the structure shown in Figures 4 to 7, and a radial wall 29 was functionally equivalent to the wall 20 of the arrangement of Figures 4 to 7.
  • the assembly also incorporated slots 30 which were functionally equivalent to the slots 23 of the arrangement of Figures 4 to 7.
  • the fifth portion of the assembly which is upstream of the slots 30 is not tubular but rather flares outwards towards the surface 26.
  • Figure 10 illustrates in full line the noise output from a conventional MWE compressor of the type generally illustrated in Figure 2. It will be noted that the noise output peaks significantly in the 4000 to 8000 hertz range. Figure 10 also shows in broken line the performance of an MWE input structure incorporating the assembly illustrated in Figure 9. It will be noted that across the frequency range the two traces overlap but there is a significant reduction in noise output in the 4000 to 8000 frequency range.
  • the assembly of Figure 9 was formed from three components, that is a flanged tube defining the surfaces 26 and 27 and the slots 30, an annular ring of triangular cross-section defining the conical surface 28, and an annular ring of rectangular cross-section defining the wall 29. Tests were also conducted with a structure identical to that of Figure 9 except for removal of the annular ring defining the conical surface 28. Such a structure is shown in Figure 11 and the noise output from that structure is shown in Figure 12.
  • a frusto-conical surface is very effective at suppressing oise at a predetermined frequency, and could be used to particular advantage in an application in which the impeller speed is expected to be constant such that noise is propagated at that predetermined frequency.
  • a part-spherical or part elliptical or other curved surface might be used however to better effect in applications where variable impeller speed operation is expected.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP98307915A 1997-10-31 1998-09-29 Compresseur Expired - Lifetime EP0913585B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB9722916.5A GB9722916D0 (en) 1997-10-31 1997-10-31 Compressor
GB9722916 1997-10-31

Publications (2)

Publication Number Publication Date
EP0913585A1 true EP0913585A1 (fr) 1999-05-06
EP0913585B1 EP0913585B1 (fr) 2004-06-30

Family

ID=10821311

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98307915A Expired - Lifetime EP0913585B1 (fr) 1997-10-31 1998-09-29 Compresseur

Country Status (4)

Country Link
EP (1) EP0913585B1 (fr)
CN (1) CN1119532C (fr)
DE (1) DE69824808T2 (fr)
GB (1) GB9722916D0 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2002048550A2 (fr) * 2000-12-13 2002-06-20 Honeywell International Inc. Silencieux pour turbocompresseur
US7059820B2 (en) 2002-07-19 2006-06-13 Honeywell International, Inc. Noise control
EP2194279A1 (fr) * 2007-09-28 2010-06-09 Mitsubishi Heavy Industries, Ltd. Compresseur
DE102009052162A1 (de) * 2009-11-06 2011-05-12 Mtu Friedrichshafen Gmbh Verdichteranordnung und Verfahren zur Herstellung einer solchen
DE102011019006B3 (de) * 2011-04-29 2012-08-30 Voith Patent Gmbh Strömungsverdichter, insbesondere zur Aufladung eines Verbrennungsmotors
DE102011109704A1 (de) 2011-08-06 2013-02-07 Daimler Ag Verdichter für eine Strömungsmaschine, insbesondere einen Abgasturbolader
US8926264B2 (en) 2009-12-16 2015-01-06 Piller Industrieventilatoren Gmbh Turbo compressor having a flow diversion channel

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0403869D0 (en) * 2004-02-21 2004-03-24 Holset Engineering Co Compressor
CN101476556B (zh) * 2009-01-22 2012-08-29 四川石油管理局成都天然气压缩机厂 宽气道自然冷却压缩机气缸
DE102010021929A1 (de) 2010-05-28 2011-12-01 Daimler Ag Ansaugtrakt für eine Verbrennungskraftmaschine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0229519A1 (fr) * 1985-12-24 1987-07-22 Holset Engineering Company Limited Compresseurs
US4930979A (en) 1985-12-24 1990-06-05 Cummins Engine Company, Inc. Compressors
WO1992003660A1 (fr) * 1990-08-28 1992-03-05 AKTIENGESELLSCHAFT KüHNLE, KOPP & KAUSCH Stabilisation des caracteristiques de fonctionnement dans des compresseurs centrifuges radiaux
DE4212653A1 (de) * 1991-04-16 1992-10-22 Holset Engineering Co Verdichter
EP0526965A2 (fr) * 1991-05-01 1993-02-10 Ishikawajima-Harima Jukogyo Kabushiki Kaisha Carters de compresseur pour turbosoufflantes
DE4213047A1 (de) * 1992-04-21 1993-10-28 Kuehnle Kopp Kausch Ag Verdichter mit einer Einrichtung zum Beeinflussen der Hauptströmung im Verdichter
US5295785A (en) * 1992-12-23 1994-03-22 Caterpillar Inc. Turbocharger having reduced noise emissions

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0229519A1 (fr) * 1985-12-24 1987-07-22 Holset Engineering Company Limited Compresseurs
US4930979A (en) 1985-12-24 1990-06-05 Cummins Engine Company, Inc. Compressors
WO1992003660A1 (fr) * 1990-08-28 1992-03-05 AKTIENGESELLSCHAFT KüHNLE, KOPP & KAUSCH Stabilisation des caracteristiques de fonctionnement dans des compresseurs centrifuges radiaux
DE4212653A1 (de) * 1991-04-16 1992-10-22 Holset Engineering Co Verdichter
GB2256460A (en) 1991-04-16 1992-12-09 Holset Engineering Co Reducing noise in a turbocharger compressor.
EP0526965A2 (fr) * 1991-05-01 1993-02-10 Ishikawajima-Harima Jukogyo Kabushiki Kaisha Carters de compresseur pour turbosoufflantes
DE4213047A1 (de) * 1992-04-21 1993-10-28 Kuehnle Kopp Kausch Ag Verdichter mit einer Einrichtung zum Beeinflussen der Hauptströmung im Verdichter
US5295785A (en) * 1992-12-23 1994-03-22 Caterpillar Inc. Turbocharger having reduced noise emissions

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2002048550A2 (fr) * 2000-12-13 2002-06-20 Honeywell International Inc. Silencieux pour turbocompresseur
WO2002048550A3 (fr) * 2000-12-13 2002-12-05 Honeywell Int Inc Silencieux pour turbocompresseur
US6623239B2 (en) 2000-12-13 2003-09-23 Honeywell International Inc. Turbocharger noise deflector
US7059820B2 (en) 2002-07-19 2006-06-13 Honeywell International, Inc. Noise control
EP2194279A1 (fr) * 2007-09-28 2010-06-09 Mitsubishi Heavy Industries, Ltd. Compresseur
EP2194279A4 (fr) * 2007-09-28 2013-08-21 Mitsubishi Heavy Ind Ltd Compresseur
DE102009052162A1 (de) * 2009-11-06 2011-05-12 Mtu Friedrichshafen Gmbh Verdichteranordnung und Verfahren zur Herstellung einer solchen
DE102009052162B4 (de) * 2009-11-06 2016-04-14 Mtu Friedrichshafen Gmbh Verdichteranordnung und Verfahren zur Herstellung einer solchen
US8926264B2 (en) 2009-12-16 2015-01-06 Piller Industrieventilatoren Gmbh Turbo compressor having a flow diversion channel
DE102011019006B3 (de) * 2011-04-29 2012-08-30 Voith Patent Gmbh Strömungsverdichter, insbesondere zur Aufladung eines Verbrennungsmotors
WO2012146344A1 (fr) 2011-04-29 2012-11-01 Voith Patent Gmbh Turbocompresseur, destiné notamment à la suralimentation d'un moteur à combustion interne
DE102011109704A1 (de) 2011-08-06 2013-02-07 Daimler Ag Verdichter für eine Strömungsmaschine, insbesondere einen Abgasturbolader

Also Published As

Publication number Publication date
CN1217436A (zh) 1999-05-26
DE69824808D1 (de) 2004-08-05
CN1119532C (zh) 2003-08-27
EP0913585B1 (fr) 2004-06-30
DE69824808T2 (de) 2005-07-14
GB9722916D0 (en) 1998-01-07

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