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
  • F04D29/40—Casings; Connections of working fluid
  • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
  • F04D29/44—Fluid-guiding means, e.g. diffusers
  • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
  • F04D29/444—Bladed diffusers
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B33/00—Engines characterised by provision of pumps for charging or scavenging
  • F02B33/32—Engines with pumps other than of reciprocating-piston type
  • F02B33/34—Engines with pumps other than of reciprocating-piston type with rotary pumps
  • F02B33/40—Engines with pumps other than of reciprocating-piston type with rotary pumps of non-positive-displacement type
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
  • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
  • F04D17/08—Centrifugal pumps
  • F04D17/10—Centrifugal pumps for compressing or evacuating
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D25/00—Pumping installations or systems
  • F04D25/02—Units comprising pumps and their driving means
  • F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
• • 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
  • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
  • F04D29/056—Bearings
• • 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
  • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
  • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
• • 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
  • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
• • 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
  • F05D2250/00—Geometry
  • F05D2250/50—Inlet or outlet
  • F05D2250/52—Outlet
• • 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
  • F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
• • 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
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T10/00—Road transport of goods or passengers
  • Y02T10/10—Internal combustion engine [ICE] based vehicles
  • Y02T10/12—Improving ICE efficiencies

Definitions

• the invention relates to the field of exhaust gas turbochargers for supercharged internal combustion engines. It relates to a bladed diffuser of a centrifugal compressor such exhaust gas turbocharger and an exhaust gas turbocharger with a centrifugal compressor with such a bladed diffuser in its outflow region.
• single-stage centrifugal compressors with bladed diffusers are generally used downstream of the compressor wheel to increase the intake pressure of the engine to increase the intake pressure of the engine.
• the kinetic energy of the medium to be compressed is converted into static pressure.
• the compressor wheels comprise a certain number of blades and the diffusers have vanes with prismatic, typically aerodynamic profiles (wedge or airfoil shape). Viewed in the direction of the compressor axis, the vanes have a certain tangential angle at the leading edge (entry angle), a certain tangential angle at the exit edge (exit angle), and a certain circumferential angular distance between each two adjacent vanes.
• EP 2014925 A1 discloses how outflow areas of radial compressors can be optimized by diffusers with irregularly distributed guide vanes. For example, seventeen vanes are arranged distributed in two groups of nine or eight vanes, each on a half ring segment.
• the narrowest sectional area between two vanes is not constant in the above example with seventeen vanes circumferentially, with the narrowest cross-sectional areas being round due to the smaller spacing between the individual vanes in a nine-vaned cluster 3 to 5 percent smaller than in the group of eight vanes, resulting in a different ratio of the flow passages at the compressor impeller outlet and at the diffuser inlet over the circumference, which could adversely affect the efficiency and the stability of the compressor stage.
• the object of the present invention is to improve the outflow region of a radial compressor in such a way that the partial flow channels in the bladed diffuser have constant narrowest cross-sectional areas (throat area) distributed over the circumference despite the unequally distributed arrangement of the guide vanes.
• This is achieved according to the invention in that the vanes of the diffuser distributed over the circumference have partially deviating relative angular positions.
• deviating, relative angular position is meant that two by rotation about the axis superimposed vanes have a different angular orientation.
• the inventive design of the diffuser of a centrifugal compressor increases the efficiency of the compressor stage and has a positive effect on the surge margin.
• FIG. 1 shows a section along the compressor axis through a radial compressor with a bladed diffuser
• Fig. 2 shows a section perpendicular to the compressor axis through a first
• Embodiment of an inventively designed diffuser with irregularly arranged vanes Embodiment of an inventively designed diffuser with irregularly arranged vanes
• Fig. 3 shows a section perpendicular to the compressor axis by a second
• Diffusers are arranged distributed.
• Fig. 1 shows the radial compressor of an exhaust gas turbocharger in section through the shaft axis.
• the compressor comprises a compressor wheel arranged on the shaft 12, which comprises a hub 10 and rotor blades 1 1 arranged thereon.
• the blades may be subdivided into main and intermediate vanes, the main vanes extending the full length of the flow channel defined by the hub and adjacent housing part, while the intermediate vanes are typically shortened and have a recessed leading edge.
• one or more intermediate blades per main blade can be arranged.
• the compressor wheel is arranged in the compressor housing, which generally comprises several parts, such as the volute casing 31 and the inlet housing 32. Between the compressor and the turbine, not shown, there is the bearing housing 30, which includes the bearing of the shaft.
• the already mentioned flow channel in the region of the compressor is limited by the compressor housing.
• the diffuser In the area of Ver Whyrrades takes over the hub of the compressor wheel, the radially inner boundary, wherein the blades of the compressor wheel are arranged in the flow channel.
• the diffuser In the flow direction of the medium to be compressed downstream of the compressor wheel, the diffuser is arranged.
• the diffuser serves, as mentioned above, the slowing down of the accelerated by the compressor wheel flow. This is done on the one hand by the guide vanes 21 of the diffuser, on the other hand by the volute casing, from where the compressed medium is supplied to the combustion chambers of an internal combustion engine.
• the vanes of the diffuser are connected to one or both sides of the flow channel with a diffuser wall 22, a housing part. Each two vanes of the diffuser arranged adjacent to one another bound together with the diffuser walls a diffuser channel.
• the diffuser serving as the basis for the invention described here has a plurality of stator blades with at least partially different angular distances.
• the angle distance between the entry edges of two adjacently arranged vanes is referred to here as the angular distance.
• the angle between two other, corresponding points of two adjacently arranged vanes may be referred to as angular distance, then, for example, when the leading edges are at different radii.
• the angular distance can be referred to as the angle between the exit edges or the angle between the profile centers.
• the angular distances between adjacently arranged vanes are therefore not identical over the entire circumference.
• the angular distances a x are different for all pairs of guide vanes 21 of the diffuser arranged adjacent to one another, ie no two of the illustrated angular distances between two adjacent vanes are identical.
• angular distances ao, CM, C (2, C (3) are also distributed irregularly in the example shown
• the angular distances could also increase or decrease regularly in a circumferential direction, or only increase and then decrease again be achieved when the angular distances of a harmonic function, such as the sine function, following and greater get smaller.
• two angular distances ao and ai are distributed over two groups of guide vanes. On the left half of the diffuser, a group with eight vanes 210, on the right half of a group with nine vanes 21 1 is arranged.
• the guide vanes are oriented such that the narrowest cross-sectional area T extending in each case in the diffuser channel between two adjacently arranged guide vanes over the blade height is constant. This is achieved in that the guide vanes are oriented differently, ie have different angular positions ßo, ßi, ß2, ß3 relative to the Tangentialline at the leading edge. Depending on the relative degree of steepness of two adjacently arranged blades, the position of the narrowest cross-sectional area T migrates along the blade surface.
• the narrowest cross-sectional area T intersects the corresponding guide blade in each case in the region of the blade inlet edge, while on the suction side the intersection line of the narrowest cross-sectional area with the respective guide blade can sometimes move all the way to the end of the guide blade.
• the respective relative degree of steepness between two guide vanes of a group is relatively constant due to the constant angular spacing, that is to say the respective relative angular position is approximately constant. Deviating angular positions, however, result in the transitional region of the two groups. Further, not shown embodiments are also possible. In this case, for example, all angular distances of the guide vanes can be identical except for one or a few.
• the individual vanes of the diffuser may differ in shape, length, entry and exit angles, and entry and exit radii, to introduce additional inequalities into the diffuser.
• the different training can be done both in the axial direction (with respect to the compressor axis), ie in the direction of the blade height, as well as in the circumferential direction. In this case, all or only a few guide vanes can be shaped or arranged differently.
• Such irregularly formed diffusers may be formed in one or more stages, with several stages arranged in the radial direction one behind the other, ie concentrically with respect to the compressor axis.
• the narrowest cross-sectional area in the diffuser channel between two vanes and above the diffuser channel height is constant. If the diffuser has a variable, ie non-constant, diffuser channel height distributed over the circumference, the guide vanes are to be arranged in accordance with the invention so that the narrowest cross-sectional area calculated from the spacing between the adjacent guide vanes and the diffuser channel height is constant.
• the irregularly formed in the circumferential direction diffuser can be positioned with respect to the circumferentially asymmetric spiral housing in a fixed angular position.
• the size of the different angular distances and their distribution along the circumference can be aligned with the asymmetrically formed volute casing downstream of the guide vanes.
• the angular distances can increase, for example, along the circumference analogous to the radius of the spiral housing.
• Leitschaufelplo which is arranged in the region of the Spiralzept culinarys, may have a different angular distance from the other Leitschaufelbin.
• positioning means ensure that the diffuser is in each case in the intended angular position relative to the spiral housing.
• the envisaged angular position is advantageously the one in which a minimum resonance oscillation is generated during operation.
• This angular position from diffuser to volute with minimal resonant vibration generation can optionally be calculated or determined experimentally.
• a possible positioning means is indicated in Fig. 2, with a positioning cam 23 on the radially outer edge of the diffuser wall 22, which engages in a positioning groove 33 in the spiral housing.
• Other positive positioning means are conceivable, such as a positioning pin, which is arranged in recesses bored on both sides.
• the indirect positioning via a third component, such as the inlet housing 32 or the bearing housing 30 are conceivable. LIST OF REFERENCE NUMBERS

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Supercharger (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=53434360

Family Applications (1)

Country Status (6)

Families Citing this family (9)

Family Cites Families (8)

• 2015
  • 2015-06-22 EP EP15730184.7A patent/EP3161325A1/de not_active Withdrawn
  • 2015-06-22 JP JP2016575229A patent/JP2017519154A/ja active Pending
  • 2015-06-22 WO PCT/EP2015/063944 patent/WO2015197536A1/de active Application Filing
  • 2015-06-22 CN CN201580034307.6A patent/CN106460870A/zh active Pending
  • 2015-06-22 KR KR1020177001872A patent/KR20170026493A/ko unknown
• 2016
  • 2016-12-23 US US15/390,449 patent/US20170108003A1/en not_active Abandoned

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