US20050196272A1 - Compressor - Google Patents

Compressor Download PDF

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Publication number
US20050196272A1
US20050196272A1 US11/061,993 US6199305A US2005196272A1 US 20050196272 A1 US20050196272 A1 US 20050196272A1 US 6199305 A US6199305 A US 6199305A US 2005196272 A1 US2005196272 A1 US 2005196272A1
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US
United States
Prior art keywords
impeller
compressor
blade
housing
annular
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.)
Abandoned
Application number
US11/061,993
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English (en)
Inventor
Bahram Nikpour
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
Assigned to HOLSET ENGINEERING COMPANY, LIMITED reassignment HOLSET ENGINEERING COMPANY, LIMITED ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: NIKPOOUR, BAHRAM
Publication of US20050196272A1 publication Critical patent/US20050196272A1/en
Priority to US12/148,667 priority Critical patent/US7686586B2/en
Abandoned 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
    • F04D29/26—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
    • F04D29/30—Vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24F—AIR-CONDITIONING; AIR-HUMIDIFICATION; VENTILATION; USE OF AIR CURRENTS FOR SCREENING
    • F24F7/00—Ventilation
    • F24F7/02—Roof ventilation
    • 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

Definitions

  • the present invention relates to a compressor.
  • the invention relates to a centrifugal compressor such as, for example, the compressor of a turbocharger.
  • a compressor comprises an impeller, carrying a plurality of blades (or vanes) mounted on a shaft for rotation within a compressor housing. Rotation of the impeller causes gas (e.g. air) to be drawn into the impeller and delivered to an outlet chamber or passage.
  • gas e.g. air
  • the outlet passage is in the form of a volute defined by the compressor housing around the impeller. Gas flows through the impeller to the outlet volute via an annular outlet passage referred to as the diffuser.
  • the diffuser has an upstream annular inlet surrounding the impeller and a downstream annular outlet opening into the volute.
  • the impeller is mounted to one end of a turbocharger shaft and is rotated by an exhaust driven turbine wheel mounted within a turbine housing at the other end of the turbocharger shaft.
  • the shaft is mounted for rotation on bearing assemblies housed within a bearing housing positioned between the compressor and the turbine housing.
  • a conventional compressor impeller comprises a back plate supporting an array of blades about a central hub.
  • the blades extend generally axially from the back plate and radially from the hub, tapering from a relatively long base at the hub to a relatively short tip which sweeps around the diffuser inlet.
  • Each impeller blade can be regarded as having a back edge where the blade is supported by the back plate of the impeller, a front edge extending generally radially from the hub and a curved edge defined between the front edge and the tip.
  • the curved edge sweeps across a wall of the compressor housing between the compressor inducer (inlet) and diffuser.
  • the diameter of the front of the impeller, defined by the front edges of the blades, is referred to as the impeller inducer diameter.
  • the ratio of the impeller inducer diameter to the impeller outer diameter (defined by the blade tips) is referred to as the “squareness” of the impeller.
  • the ratio of the outer diameter of the impeller to the diffuser outlet diameter is referred to as the diffuser radius ratio.
  • Conventional compressors typically have a diffuser radius ratio in the range of 1.6 to 2.0 and conventional impeller wheels typically have a squareness in the range of 0.64 to 0.71.
  • compressor impeller blades It is usual for compressor impeller blades to be backswept relative to direction of rotation of the impeller. That is, cach blade is curved backwards relative to the direction of rotation of the impeller.
  • the angle of backsweep at any point on a blade surface is the angle defined between a tangent to the blade surface at that point in a plane normal to the axis and a radial line extending through the axis of the wheel.
  • Impeller blades generally curve from the base to the tip so that the angle of backsweep varies across the surface of the blade.
  • Conventional impeller blades typically have a backsweep angle in the range of between 30° and 40° measured at any point on the blade surface.
  • impeller blades It is also conventional for impeller blades to be raked backwards having regard to the direction of rotation of the impeller. That is, the back edge of each blade (defined where the blade meets the back disc) lies behind the front edge of the blade (relative to the direction of rotation) so that the tip of the blade (and normally the base), is skewed relative to the axis of the impeller.
  • the angle of rake at any point on a blade surface is the angle between a tangent to a line defined by a constant radius cross section through a blade and a line parallel to the impeller axis.
  • Impeller blades may be curved so that the angle of rake varies from the base of the blade to the tip. Conventional impellers typically have a rake angle between 0 and 35° at any point on the blade surface.
  • a blade with a constant 0° rake angle extends from the impeller backplate in a direction parallel to the axis of the impeller wheel (note however that such a blade does not necessarily extend strictly radially as it may well be swept backwards as mentioned above).
  • a blade with a 0° rake angle at its base and a 20° rake angle at its tip will have a base lying along the axis of the impeller and a tip edge lying at a 20° angle to the axis.
  • Compressor performance can be characterised by plotting changes in pressure ratio across the compressor (that is outlet pressure/inlet pressure) for different gas mass flow rates through the compressor at different impeller rotational speeds.
  • the plot of the pressure ratio against flow rate for a variety of rotational speeds is known as a “compressor map”. It is also common to include with a compressor map a plot of the compressor efficiency against mass flow rate through the compressor at maximum operating speed.
  • the map of any particular compressor is bounded by a surge line and a choke line.
  • the surge line is defined by pressure ratio/mass flow rate points at which the compressor will surge for a range of impeller speeds. This is the low flow operating limit of the compressor.
  • the choke line is defined by pressure ratio/mass flow rate points at which the compressor will choke for a range of impeller speeds. This represents the maximum flow capacity of the compressor for any impeller speed.
  • the maximum pressure ratio available from the compressor is normally the surge point of the maximum speed line.
  • the available mass flow range between the surge line and choke line is referred to as the “map width”.
  • Compressor operation is extremely unstable under surge conditions due to large fluctuations in pressure and mass flow rate through the compressor.
  • compressor supplies air to a reciprocating engine
  • fluctuations in mass flow rate are unacceptable.
  • surge margin there is a continuing requirement to extend the usable flow range of compressors, in particular by improving surge margin.
  • a compressor for compressing a gas comprising:
  • Adoption of the design parameters of the present invention runs counter to conventional compressor design procedures. For instance, in modern compressor design, particularly for compressors to be fitted to vehicles, there is emphasis on reduced size and weight. Adopting an unusually low impeller squareness, in accordance with the present invention, increases the overall size of the impeller (for a given flow/inducer diameter) as compared with a conventional design. However, any adverse impact of this increased size is more than compensated for by the improvement in performance. Similarly, the adoption of unusually high backsweep angles (and in preferred embodiments rake angles) leads to more complex tooling and manufacturing procedures which leads to increased expense compared to a conventional impeller. However, again the improvement in performance more than compensates for the increased complexity and manufacturing costs.
  • the average angle of backsweep of each blade may be between 50° and 55°.
  • each impeller blade is raked backwards relative to the direction of rotation of the impeller, preferably at an angle in the range of 35° to 55°. In some embodiments of the invention the average rake angle of each blade is in the range of 35° to 40°.
  • angles of backsweep and rake assuming a blade of zero thickness relate to such “zero” thickness blades and may in practice be subject to some minor variation as a result of varying blade thickness.
  • the compressor inlet has a structure that has become known as a “map width enhanced (MWE)” structure.
  • MWE map width enhanced
  • An MWE structure is described for instance in U.S. Pat. No. 4,743,161.
  • the inlet of such an MWE compressor comprises two coaxial tubular inlet sections, an outer inlet section forming the compressor intake and an inner inlet section defining the compressor inducer, or main inlet.
  • the inner inlet section is shorter than the outer inlet section and has an inner surface which is an extension of a surface of an inner wall of the compressor housing which is swept by the curved edges of the impeller blades.
  • An annular flow path is defined between the two tubular inlet sections which is open at its upstream end (relative to the intake) and is provided with apertures at its downstream end (relative to the intake) which communicate with the inner surface of the compressor housing which faces the impeller.
  • the pressure within the annular flow passage surrounding the compressor inducer is normally lower than atmospheric pressure.
  • the pressure in the area swept by the impeller is less than that in the annular passage.
  • FIG. 1 is a cross-section through a generic MWE compressor housing and impeller
  • FIG. 2 is a front view of the compressor impeller of FIG. 1 ;
  • FIG. 3 is a side view of the impeller of FIG. 1 ;
  • FIG. 4 is an over-plot comparing the performance map of a conventional compressor with a compressor in accordance with a first embodiment of the present invention.
  • FIG. 5 is an over-plot comparing the performance map of a conventional compressor with a compressor according to a second embodiment of the present invention.
  • FIG. 1 this illustrates a cross-section of generic MWE compressor of a general design typically included in a turbocharger.
  • the compressor comprises an impeller 1 mounted within a compressor housing 2 on one end of a rotating shaft (not shown) extending along an axis 2 a .
  • the shaft (not shown) extends through a bearing housing, part of which is indicated at 3 , to a turbine housing (not shown).
  • the impeller has a plurality of blades 4 each of which has a front edge 5 , a tip 6 and a curved edge 7 extending between the front edge 5 and tip 6 .
  • the impeller is described in more detail below with reference to FIGS. 2 and 3 .
  • the compressor housing 2 defines an outlet volute 8 surrounding the impeller 1 , and an MWE inlet structure comprising an outer tubular wall 9 extending upstream of the impeller 1 and defining an intake 10 for gas (such as air), and an inner tubular wall 11 which extends part way into the intake 10 and defines the compressor inducer 12 .
  • the inner surface of the inner tubular wall 11 is an upstream extension of a housing wall surface 13 which is swept by the curved edges 7 of the impeller blades 4 .
  • An annular flow passage 14 surrounds the inducer 12 between the inner and outer walls 11 and 9 respectively.
  • the flow passage 14 is open to the intake 10 at its upstream end and is closed its downstream end by an annular wall 15 of the housing 2 .
  • the annular passage 14 however communicates with the impeller 1 via apertures 16 formed through the housing (through the tubular inner wall 11 in this instance) and which communicate between a downstream portion of the annular flow passage 14 and the inner surface 13 of the housing 2 which is swept by the curved edges 7 of the impeller blades 4 .
  • An annular passage known as the diffuser 19 , is defined by the housing 2 around the impeller blade tips 6 and has an annular outlet 19 a communicating with the volute 8 .
  • the conventional MWE compressor illustrated in FIG. 1 operates as is described above.
  • air passes axially along the annular flow path 14 towards the impeller 1 , flowing to the impeller through the apertures 16 .
  • the direction of air flow through the annular passage 14 is reversed so that air passes from the impeller 1 , through the apertures 16 , and through the annular flow passage 14 in an upstream direction and is reintroduced into the air intake 10 for re-circulation through the compressor.
  • FIGS. 2 and 3 illustrate features of the impeller 1 in more detail.
  • the blades 4 comprise main blades 4 a and smaller intermediate “splitter” blades 4 b .
  • the blades 4 are supported by a backplate 17 around a central impeller hub 18 .
  • the front edge 5 of each blade extends generally radially to the axis 2 a of the impeller, the maximum diameter defined by the front edges 5 being known as the inducer diameter of the impeller.
  • the outer diameter of the impeller is defined by the diameter of the blade tips 6 .
  • the impeller inducer diameter is marked as D 1 on FIG. 1 and the impeller outer diameter is marked as D 2 on FIG. 1 .
  • the diffuser outlet diameter is marked as D 3 on FIG. 1 .
  • the ratio of the impeller inducer diameter D 1 to the impeller outer diameter D 2 is referred to as the “squareness” of the impeller.
  • the ratio of the diffuser outlet diameter D 3 to the impeller outer diameter D 2 is referred to as the diffuser radius ratio.
  • Conventional turbocharger compressors typically have an impeller with a squareness in the range 0.64 to 0.71 and a diffuser radius ratio in the range 1.6 to 2.0. However, in accordance with the present invention the squareness is in the range 0.59 to 0.63 and the diffuser radius ratio is in the range 1.4 to 1.55.
  • the backsweep of the impeller blades 4 is also apparent from FIG. 2 and FIG. 3 .
  • the angle of backsweep is measured between a radial line extending through the axis of the impeller and a line extending at a tangent to the blade surface at a given point, and lying in a plane normal to the axis (i.e. parallel to the back plate 17 ).
  • FIG. 2 the backsweep angle B measured at the tip of a blade is shown. Due to curvature of each blade, the backsweep angle may vary along the surface of the blade but for conventional turbocharger compressors the backsweep angle at any point of the surface of the blade typically lies between 30° to 40°. However, with the present invention the backsweep angle measures at any point on the surface of the blade that lies in the range of 45° to 55°.
  • FIG. 2 also illustrate the rake angle of the impeller blades 4 .
  • the rake angle of a blade at any point on the blade surface can be measured between a line parallel to the axis of the impeller and a line tangential to the blade at that point in a direction defined by a radial cross-section through the blade. Because of the typical curvature of the impeller blades 5 , the rake angle may change across the surface of a blade.
  • FIG. 3 illustrates the rake angle R measured at the tip of a blade 5 .
  • Conventional turbocharger compressors typically have a back rake angle between 0° and 35°. Compressors in accordance with the present invention may have a back rake angle within this range, but it is preferred that the back rake angle is in the range of 35° to 55°.
  • FIG. 4 is an over-plot of the performance of a first embodiment of a compressor according to the present invention (the plot shown in dotted lines), in comparison with the performance of a conventional MWE compressor (the plot shown in solid lines).
  • the conventional compressor has blades with an average backsweep angle of 40° and a rake angle of 35°.
  • the impeller has a squareness of 0.68 and the compressor has a diffuser radius ratio of 1.65.
  • Each of the impeller blades of the embodiment of the present invention has an average impeller backsweep angle of about 52° (the backsweep angle varies between 48.5° and 55° across each blade surface).
  • the rake angle is substantially constant at 40° (subject to variations due to varying blade thickness).
  • the impeller has a squareness of 0.6 and the diffuser radius ratio is 1.52.
  • the lower plot is the performance map which, as is well known, plots air flow rate through the compressor against pressure ratio from the compressor inlet to outlet for a variety of impeller rotational speeds.
  • the flow axis is normalised to 100%.
  • the left hand line of the map represents the flow rates at which the compressor will surge for various turbocharger speeds and is known as the surge line. It can be seen that the compressor according to the present invention has a significantly improved surge margin compared to the surge margin of the conventional compressor. The maximum flow (choke flow) is largely unaffected (shown by the right hand line of the map).
  • the surge margin is increased over a range of pressure ratios and in particular is significantly increased at high pressure ratios above 3:1. It can also be seen that the flow capacity of the compressor at maximum operating speed is increased compared with the conventional compressor. Specifically, the surge margin is increased by up to 20% at high pressure ratio, and the pressure ratio capability is increased by up to 15% ratio.
  • Superimposed on the compressor map are two engine operating lines L 1 and L 2 .
  • L 1 represents the running conditions of a typical conventional turbocharged diesel engine whereas L 2 shows the running conditions of a typical turbocharged diesel engine being developed to meet new emission targets. This clearly shows the advantages of the present invention when incorporated in a turbocharger for a diesel engine designed to meet new emission regulations.
  • FIG. 4 plots the compressor efficiency as a function of air flow. Again, the plot relating to the embodiment of the present invention is shown in dashed lines. It can be seen that at high operating speeds the present invention provides an improvement in efficiency (up to 3% at high pressure ratios).
  • FIG. 5 is a an over-plot of the compressor map of a second embodiment of the present invention, in comparison with the same conventional MWE compressor as used for the comparison of FIG. 4 .
  • the compressor in accordance with the present invention has impeller blades with a backsweep angle varying between 51° and 55° across each blades surface giving an average backsweep angle of about 53°.
  • the rake angle is substantially constant at 35°.
  • the impeller has a squareness of 0.63 and the compressor diffuser radius ratio is 1.4. Again, improvements in surge margin, maximum flow at maximum operating speed, and efficiency at maximum operating speed can be seen. Again it can be seen that the most significant increase in surge margin is obtained at high pressure ratios above about 3:1.
  • surge margin is improved by up to 30%
  • pressure ratio capability is improved by up to 7%
  • efficiency at high pressure ratio is increased by up to 5%.
  • engine operating conditions for a conventional turbocharged diesel engine and for a typical next generation diesel engine are illustrated by lines L 1 and L 2 respectively.
  • compressors according to the present invention have particular utility as part of a turbocharger, other applications will be apparent to the readily skilled person. Similarly, possible modifications to the detailed structure as described above will be readily apparent to the appropriately skilled person.

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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)
US11/061,993 2004-02-21 2005-02-21 Compressor Abandoned US20050196272A1 (en)

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US12/148,667 US7686586B2 (en) 2004-02-21 2008-04-21 Compressor

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GB0403869.1 2004-02-21
GBGB0403869.1A GB0403869D0 (en) 2004-02-21 2004-02-21 Compressor

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US (2) US20050196272A1 (fr)
EP (1) EP1566549B1 (fr)
JP (1) JP4717465B2 (fr)
KR (1) KR20060043038A (fr)
CN (1) CN100443730C (fr)
GB (1) GB0403869D0 (fr)

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US20040255917A1 (en) * 2003-06-20 2004-12-23 Mokry Peter G. Impeller and a supercharger for an internal combustion engine
US20090136357A1 (en) * 2007-11-27 2009-05-28 Emerson Electric Co. Bi-Directional Cooling Fan
US20110020152A1 (en) * 2008-04-08 2011-01-27 Volvo Lastvagnar Ab Compressor
US20130200218A1 (en) * 2012-02-08 2013-08-08 Bong H. Suh Rotorcraft escape system
US20130343886A1 (en) * 2012-06-20 2013-12-26 Ford Global Technologies, Llc Turbocharger compressor noise reduction system and method
US20140356124A1 (en) * 2013-06-04 2014-12-04 Hamilton Sundstrand Corporation Air compressor backing plate
US20180274376A1 (en) * 2017-03-27 2018-09-27 General Electric Company Diffuser-deswirler for a gas turbine engine
US10337529B2 (en) 2012-06-20 2019-07-02 Ford Global Technologies, Llc Turbocharger compressor noise reduction system and method

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US9879594B2 (en) 2015-03-09 2018-01-30 Caterpillar Inc. Turbocharger turbine nozzle and containment structure
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US10066639B2 (en) 2015-03-09 2018-09-04 Caterpillar Inc. Compressor assembly having a vaneless space
US9683520B2 (en) 2015-03-09 2017-06-20 Caterpillar Inc. Turbocharger and method
US9739238B2 (en) 2015-03-09 2017-08-22 Caterpillar Inc. Turbocharger and method
EP3334984A1 (fr) * 2015-08-11 2018-06-20 Carrier Corporation Système cvc, à faible prg et à faible capacité
CN105201905B (zh) * 2015-10-16 2018-09-11 珠海格力电器股份有限公司 离心叶轮组件及离心压缩机
US10221858B2 (en) 2016-01-08 2019-03-05 Rolls-Royce Corporation Impeller blade morphology
US11053950B2 (en) 2018-03-14 2021-07-06 Carrier Corporation Centrifugal compressor open impeller
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GB2576565B (en) * 2018-08-24 2021-07-14 Rolls Royce Plc Supercritical carbon dioxide compressor
CN109162960A (zh) * 2018-09-03 2019-01-08 中国科学院高能物理研究所 一种2k冷压缩机叶轮
EP4080060A3 (fr) * 2021-04-19 2023-01-25 Bloom Energy Corporation Soufflante centrifuge avec moteur intégré et volute de soufflante servant de dissipateur thermique pour le moteur

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US7686586B2 (en) 2010-03-30
EP1566549A2 (fr) 2005-08-24
KR20060043038A (ko) 2006-05-15
EP1566549A3 (fr) 2009-11-18
EP1566549B1 (fr) 2012-09-26
JP2005233188A (ja) 2005-09-02
GB0403869D0 (en) 2004-03-24
JP4717465B2 (ja) 2011-07-06
CN100443730C (zh) 2008-12-17
US20080232959A1 (en) 2008-09-25
CN1657786A (zh) 2005-08-24

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