WO2018178385A1 - Compresseur d'un turbocompresseur de gaz d'échappement - Google Patents

Compresseur d'un turbocompresseur de gaz d'échappement Download PDF

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Publication number
WO2018178385A1
WO2018178385A1 PCT/EP2018/058395 EP2018058395W WO2018178385A1 WO 2018178385 A1 WO2018178385 A1 WO 2018178385A1 EP 2018058395 W EP2018058395 W EP 2018058395W WO 2018178385 A1 WO2018178385 A1 WO 2018178385A1
Authority
WO
WIPO (PCT)
Prior art keywords
compressor
struts
channel
compressor wheel
wheel
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.)
Ceased
Application number
PCT/EP2018/058395
Other languages
German (de)
English (en)
Inventor
Marius Banica
Heinz-Jürgen FELD
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.)
Accelleron Industries AG
Original Assignee
ABB Turbo Systems AG
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 ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Publication of WO2018178385A1 publication Critical patent/WO2018178385A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • 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

Definitions

  • the invention relates to the field of exhaust gas turbochargers for supercharged internal combustion engines.
  • the invention relates to a compressor of such an exhaust gas turbocharger with a circulating chamber delimited from the main flow.
  • exhaust gas turbochargers are used by default for the performance of an internal combustion engine, with a turbine in the exhaust system of the internal combustion engine and with one of the internal combustion engine upstream compressor.
  • the exhaust gases of the internal combustion engine are thereby relaxed in the turbine.
  • the work thus obtained is transmitted by means of a shaft to the compressor, which compresses the internal combustion engine supplied air.
  • an exhaust gas turbocharger on a compressor which is rotatably mounted in a housing.
  • the housing usually has an inlet channel in which an inner wall is inserted, which on the one hand forms the main channel contour and on the other hand limits an annular circulation chamber surrounding the main channel.
  • the interior of the annular chamber for example, through an opening with the Compressor inlet and be connected in the region of the compressor wheel through a ring slot in the contour wall of the annular chamber with the inlet channel.
  • the contour wall can be held concentrically via support ribs to the housing.
  • the envisaged in compressors of this kind annular chamber is a so-called map-stabilizing measure.
  • the desired map expansion of the compressor is purchased in addition to loss of efficiency and often by inadmissible noise and vibration development.
  • responsible for such vibration excitations in the blades may include the support ribs, with which the inner wall of the annular chamber may be attached, for example, to the housing.
  • a compressor of an exhaust gas turbocharger includes a compressor wheel rotatable about an axis, a main flow passage for supplying a medium to be compressed to the compressor wheel, an outer compressor housing, and an element, particularly a housing insert, disposed radially between the compressor wheel and the compressor housing.
  • the element, in particular the housing insert is configured to form an annular, surrounding the main flow channel stabilizer channel when installed.
  • the stabilizer channel there are provided a number V of struts identical to V> m co + B arranged circumferentially, where m co is the absolute minimum order of all non-propagating acoustic modes at the first sheet pass frequency, and B is the number of rotor blades the compressor wheel is.
  • a compressor is provided by the compressor according to the invention, which has a lower noise and vibration development compared to known compressors.
  • the compressor according to the invention allows the restoration of a simple acoustic field, so that wall-mounted silencer (WSD) can advantageously be installed.
  • WSD wall-mounted silencer
  • an exhaust gas turbocharger with a compressor according to one of the embodiments described herein is provided, so that advantageously an improved exhaust gas turbocharger can be provided.
  • an exhaust gas turbocharger can be provided which can be made quieter, cheaper, lighter, more efficient and more compact than exhaust gas turbochargers known from the prior art.
  • Figure 1 is a schematic isometric sectional view of a section of a compressor according to embodiments described herein;
  • Figure 2a is a schematic representation of a first position of the im
  • Main flow channel disposed rotatable compressor wheel relative to arranged in the stabilizer channel struts
  • Figure 2b is a schematic representation of a second position of the im
  • Main flow channel disposed rotatable compressor wheel relative to arranged in the stabilizer channel struts
  • Figure 3 is a schematic representation of an axial frontal
  • Figure 4 is a schematic representation of a radial plan view of a Section of a stabilizer channel of a compressor according to another embodiment described herein,
  • Figure 5 is a schematic representation of the arranged in a stabilizer channel struts according to another embodiment of the compressor described herein;
  • Figures 6a-6d are schematic representations of possible
  • FIG. 1 shows a schematic isometric sectional view of a section of a compressor 100 of an exhaust gas turbocharger according to embodiments described herein.
  • the compressor may for example be a radial compressor, as shown by way of example in FIG.
  • the compressor embodiments described herein are not limited to a radial compressor.
  • the embodiments of the compressor described herein can also be used in an axial compressor.
  • the compressor 100 comprises a compressor wheel 110 rotatable about an axis 111, a main flow passage 120 for supplying a medium to be compressed to the compressor wheel 110, an outer compressor housing 125, and an element 130, in particular one Housing insert, which is arranged radially between the compressor 110 and the compressor housing 125.
  • the element 130, in particular the housing insert is typically configured in such a way as to be annular when installed and surrounding the main flow passage Stabilizer channel 135 to form.
  • an annular stabilizer channel means a channel which forms an annular structure arranged around the main flow channel.
  • the annular structure may have any inner contour wall geometry.
  • the stabilizer channel may be annular, with one or both inner contour walls (ie the radially inner contour wall of the stabilizer channel and / or the radially outer contour wall of the stabilizer channel) may be wavy, or may have a differently structured inner contour wall geometry.
  • a number V of struts 140 identical to V> m co + B which are circumferentially arranged periodically.
  • m co corresponds to the smallest circumferential order of all non-propagatable acoustic modes
  • B corresponds to the number of rotor blades of the compressor wheel.
  • an improved compressor is provided which, as compared to compressors known in the art, has less noise and vibration development ,
  • the minimum number Vmin of the identical struts V m can be in> 23.
  • the embodiments of the compressor according to the invention described herein advantageously make it possible to restore a simple acoustic field, so that optionally wall-mounted silencers (WSD) can advantageously be installed in the main flow channel.
  • WSD wall-mounted silencers
  • the stabilizer channel 135 is formed in the interior of the compressor housing 125 as an annular circulation space which radially encloses the main flow channel and which extends from the intake 113 to an at least partially circulating circulation opening 114 in the region of the blades of the compressor wheel 110 extends.
  • the circulation space is opened via two openings to the main flow channel.
  • the circulation opening 114 Upstream of the compressor wheel can be arranged a radial inlet opening (not shown) and downstream of the leading edge of the compressor wheel and in the overlap area to the inlet, the circulation opening 114 may be arranged.
  • the stabilizer passage 135 is aerodynamically connected to the main flow passage 120.
  • the contour wall 115 can be, for example, a wall of the element 130, in particular of the housing insert, which is designed to form the annular, the main flow channel surrounding stabilizer channel 135 in the installed state.
  • the struts 140 are typically with a surface opposite the contour wall 115, i. an inner wall of the stabilizer channel connected.
  • the stabilizer channel 135 may be designed to be axisymmetric, for example symmetrically about the axis 111 of the rotatable compressor wheel 110.
  • the stabilizer channel 135 may be designed to provide an axisymmetric flow.
  • Form recirculation channel wherein the flow recirculation channel is interrupted by regularly arranged, equally spaced in the circumferential direction, identical struts.
  • struts 140 may be integral with the element 130, in particular the housing insert executed.
  • the strut-comprising element 130, in particular the housing insert may be made in one piece, e.g. be executed as a casting.
  • all circumferential spacing between adjacent struts of the number V of struts 140 are identical.
  • the struts 140 may be arranged symmetrically about the axis 111 of the rotatable compressor wheel 110, as shown by way of example in FIG. 1. Such an embodiment may be particularly advantageous in terms of a lower noise and vibration development.
  • FIG. 2a shows the rotor blades 112 of the compressor wheel 110 in a first position (t, ⁇ )
  • FIG. 2b shows the rotor blades 112 of the compressor wheel 110 in a second position (t + At, ⁇ + ⁇ ).
  • FIGS. 2a and 2b show only three rotor blades of the compressor wheel 110 and seven struts 140 arranged in the stabilizer channel.
  • the point O corresponds to an observation point and ⁇ corresponds to the rotational speed of the compressor wheel in revolutions per second.
  • the compressor moves in a rotation about the axis of rotation of a first position PI at a first time t and a first angle ⁇ to a second position P2 at a second time t + At and a second angle ⁇ + ⁇ . Due to the circumferential periodic arrangement of the struts 140, the observation point O experiences the same pressure in the first position PI and in the second position P2.
  • B corresponds to the number of rotor blades of the compressor wheel
  • k x corresponds to the axial wave number
  • x corresponds to the axial coordinate
  • a mn corresponds to the wave amplitude
  • j corresponds to the order of the harmonics
  • i denotes the complex notation
  • m corresponds to the circumferential order of acoustic mode, where m is an arbitrary natural number may be (including 0)
  • J m represents the Bessel function of the first kind of order m
  • the Number V of struts provided in the stabilizer channel are selected according to the formula V> m co + jB.
  • m co corresponds to the smallest circumferential order of all non-propagatable acoustic modes
  • j corresponds to the order of the harmonics
  • B corresponds to the number of rotor blades of the compressor wheel.
  • acoustic liners or acoustic resonators may be disposed in an area facing the main flow channel.
  • the struts 140 may be circumferentially tilted at an angle ⁇ , as exemplified in FIG.
  • the struts 140 may be curved in the circumferential direction, as shown by way of example in FIG. This can have an advantageous effect on a lower noise and vibration development.
  • the struts may be relative to the direction of the axis 111 of the rotatable compressor wheel 110 be inclined by an angle ß, as shown by way of example in Figure 4. This can lead to an alternative or additional advantageous reduction of the noise and vibration development.
  • the struts 140 may be arranged such that in the axial direction of view between adjacent struts a fluid free space 150 is provided for the medium, as shown for example in FIG. 5 is shown.
  • the struts 140 may be arranged circumferentially so as not to overlap in the axial direction.
  • the struts may be arranged such that they are tilted in the direction of the axis (111) of the rotatable compressor wheel (110).
  • the struts 140 may have a circular cross section or an elliptical cross section, as shown by way of example in FIGS. 6a and 6b.
  • the struts 140 may have a triangular cross-section or a diamond-shaped cross-section, as shown by way of example in FIGS. 6c and 6d.
  • the strut cross sections illustrated in FIGS. 6a-6d can extend over the entire length of the strut.
  • the strut cross sections shown in FIGS. 6a-6d may be limited to a certain length range of the struts, for example, the struts may be configured such that a circular cross section merges into an elliptical cross section.
  • Figure 1 shows a radial compressor
  • the present invention is not limited to a radial compressor, but can also be applied to axial compressor.
  • an axial compressor may also be as described herein Element, in particular a housing insert having a stabilizer channel with a number V of V> m co + jB identical struts, which are circumferentially arranged periodically.
  • the design of the compressor in particular in the design of the struts in the stabilizer channel, advantageously structures in the main flow channel are taken into account, so that an optimization of the compressor with respect to a reduction of noise and vibration development is made possible.
  • the structures in the secondary flow field ie in the stabilizer channel
  • the number of struts is determined solely for structural mechanics considerations. This leads to a scattering of the acoustic modes and a destruction of the otherwise simple acoustic field, which can be substantially prevented in the embodiments described herein.
  • an exhaust gas turbocharger may be provided which is quieter, cheaper, lighter, more efficient and more compact than currently known exhaust gas turbochargers.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un compresseur (100) d'un turbocompresseur de gaz d'échappement, comprenant : une roue de compresseur (110) pouvant tourner autour d'un axe (111), un canal d'écoulement principal (120) pour l'alimentation d'un fluide à compresser sur la roue de compresseur (110), un boîtier de compresseur extérieur (125), et un élément (130) disposé radialement entre la roue de compresseur (110) et le boîtier de compresseur (125). L'élément (130) est configuré pour former, dans l'état monté, un canal de stabilisation (135) en forme d'anneau entourant le canal d'écoulement principal, le canal de stabilisation (135) étant muni d'un nombre (V) de V≥ mco + jB entretoises identiques (140) disposées selon une période circonférentielle, mco étant le premier mode circonférentiel, j étant l'ordre des harmoniques, et B étant le nombre de pales de rotor de la roue de compresseur.
PCT/EP2018/058395 2017-03-31 2018-04-03 Compresseur d'un turbocompresseur de gaz d'échappement Ceased WO2018178385A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017107014.1A DE102017107014A1 (de) 2017-03-31 2017-03-31 Verdichter eines abgasturboladers
DE102017107014.1 2017-03-31

Publications (1)

Publication Number Publication Date
WO2018178385A1 true WO2018178385A1 (fr) 2018-10-04

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PCT/EP2018/058395 Ceased WO2018178385A1 (fr) 2017-03-31 2018-04-03 Compresseur d'un turbocompresseur de gaz d'échappement

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DE (1) DE102017107014A1 (fr)
WO (1) WO2018178385A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2023173389A1 (fr) * 2022-03-18 2023-09-21 Wuxi Cummins Turbo Technologies Company Ltd. Compresseur

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070271921A1 (en) * 2006-05-24 2007-11-29 Honeywell International, Inc. Inclined rib ported shroud compressor housing
EP2110557A1 (fr) * 2008-04-17 2009-10-21 Honeywell International Inc. Compresseur centrifuge avec contrôle de surtension et procédé associé
EP2194279A1 (fr) * 2007-09-28 2010-06-09 Mitsubishi Heavy Industries, Ltd. Compresseur
DE102015008014A1 (de) * 2014-06-27 2015-12-31 Electro-Motive Diesel, Inc. Turbolader mit einem mit Flügeln versehenen Kompressoreinlassrückzirkulationsdurchlass

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2262031A1 (de) * 1972-12-19 1974-06-20 Klein Schanzlin & Becker Ag Eintritts-leitapparat fuer stroemungsmaschinen
JP5039673B2 (ja) * 2008-02-27 2012-10-03 三菱重工業株式会社 ターボ型圧縮機のストラット構造

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070271921A1 (en) * 2006-05-24 2007-11-29 Honeywell International, Inc. Inclined rib ported shroud compressor housing
EP2194279A1 (fr) * 2007-09-28 2010-06-09 Mitsubishi Heavy Industries, Ltd. Compresseur
EP2110557A1 (fr) * 2008-04-17 2009-10-21 Honeywell International Inc. Compresseur centrifuge avec contrôle de surtension et procédé associé
DE102015008014A1 (de) * 2014-06-27 2015-12-31 Electro-Motive Diesel, Inc. Turbolader mit einem mit Flügeln versehenen Kompressoreinlassrückzirkulationsdurchlass

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2023173389A1 (fr) * 2022-03-18 2023-09-21 Wuxi Cummins Turbo Technologies Company Ltd. Compresseur
US12442390B2 (en) 2022-03-18 2025-10-14 Wuxi Cummins Turbo Technologies Company Ltd. Compressor
EP4493827A4 (fr) * 2022-03-18 2025-12-24 Wuxi Cummins Turbo Tech Company Ltd Compresseur

Also Published As

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