EP1682779B1 - Rotor de compresseur radial - Google Patents

Rotor de compresseur radial Download PDF

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Publication number
EP1682779B1
EP1682779B1 EP04768299.2A EP04768299A EP1682779B1 EP 1682779 B1 EP1682779 B1 EP 1682779B1 EP 04768299 A EP04768299 A EP 04768299A EP 1682779 B1 EP1682779 B1 EP 1682779B1
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EP
European Patent Office
Prior art keywords
centrifugal compressor
rotor
compressor according
flow
passage
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Active
Application number
EP04768299.2A
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German (de)
English (en)
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EP1682779A1 (fr
Inventor
Andrew John Vine
Keith Robert Pullen
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.)
Dynamic Boosting Systems Ltd
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Dynamic Boosting Systems Ltd
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Publication of EP1682779A1 publication Critical patent/EP1682779A1/fr
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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
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors

Definitions

  • the invention relates to a compressor, in particular a compressor of the radial or centrifugal type for a turbo machine.
  • the compressor comprises a rotor driven by a turbine or other machine having a plurality of generally radial blades which divert axially flowing inlet gas such as air at the centre to provide a pressure rise at the circumference exit.
  • inlet gas such as air
  • diffusers in the form of tangential vanes are provided to slow down airflow at the exit and hence convert the kinetic energy of the airflow to a pressure rise.
  • a multi-stage compressor comprises a plurality of concentrically nested rotors in a correspondingly nested stator configuration. Each stator stage has diffuser vanes and a flow passage to the axial air inlet in the next rotor stage.
  • the vane profiles are effectively laminar or plate like occupying a minimal volume of the compressor space and this is termed here a "full entry" compressor.
  • a particularly effective embodiment described in GB2366333 relies on a wedge shaped blade occupying a substantial fraction of the compressor volume and this is termed here a "partial entry" compressor.
  • a problem with full entry turbomachines is that they must operate at a particular speed for a given flow rate and pressure rise - the science behind this can be quantified using the concept of specific speed. If the flow rate is relatively low, the shaft speed must be high in order to maintain the correct physical dimensions. This creates a problem in that once speeds get over about 20,000 rpm, it is not easy to find a drive system.
  • the drives do exist but are expensive - ie a low speed motor with a gearbox or a high speed motor (inverter driven). Once speeds get above 100,000 rpm then it is very difficult to find an appropriate drive.
  • Using partial entry is a way of reducing flow rate without increasing shaft speed.
  • partial entry compressors are being able to operate at a much reduced shaft speed in comparison to conventional radial compressors.
  • a compressor for 10 m 3 /s can operate at 60,000 rpm as opposed to 600,000 rpm. It can be used as a single stage - generally the pressure ratio is limited to 1.6:1 but in most cases, a multistage device is required to achieve higher pressure ratios.
  • the pressure ratio is the multiple of the pressure ratio for each stage and the number of stages. 5 stages each of pressure ratio 1.6:1 can achieve 10.48:1 (neglecting interstage pressure losses).
  • the partial entry compressor provides an interupted flow of gas to the diffuser at the exit. This is because the flow passages only occupy a fraction of the available area, the rest of which is contained within enclosed islands comprising the partial entry blades.
  • the flow leaves the rotor it is in the form of a number of rotating discrete jets of number equal to the number of rotor passages.
  • Such a flow will enter the diffuser whose purpose is to recover as much kinetic energy as possible and convert this to useable static pressure rise.
  • the diffuser will experience a pulsating flow from the jets, the efficiency of diffusion is quite poor.
  • a further problem is windage loss caused by movement of rotor parts adjacent to generally stationary gas causing the gas to move, drawing power from the rotor which is not useful.
  • the windage problem is severe for partial entry compressors, increasing approximately with the fifth power of diameter of the rotor.
  • the nested configuration solves some of the problem because rotors are adjacent to moving gas from the rotor from which they are nested , the use of partial entry rotors still means that the ratio windage losses to useful work goes up by a factor of 4.
  • US patent number 3,369,737 relates to a radial flow machine and, more particularly, to a radial outflow compressor that pumps to high compression ratio in a single stage.
  • the invention relates to a radial compressor having swept forward partial entry blades, that is, the blades are curved forwardly in the direction of rotation.
  • the forward sweep is turned extensively towards the tangential direction in the direction of rotor rotation such that the resultant exit flow from the exaggerated forward swept flow passage has a tangential velocity greater than the velocity of the compressor blade tips.
  • Fig. 1 shows a rotor 10 having a plurality of partial entry blades 12.
  • the rotor 10 is driven by a shaft 13 such that air inducted at an axial inlet passage 14 is driven generally outwardly in the passages 16 between adjacent blades 12 to a circumferential exit at 18 when the compressor rotor is rotating in the direction shown by arrow A.
  • the exit air is diffused by a plurality of generally linear, tangentially extending diffusers 20 which are angled in the direction of rotation and are wedge shaped, tapering inwardly to a point adjacent the circumferential exit 18 of the compressor rotor 10.
  • the diffuser passage wall is preferably close in the radial direction to the rotor exit guiding the flow in an almost tangential direction, maintaining the correct flow angle at the rotor exit and hence maintaining the required pressure ratio.
  • the increased pressure air exits the diffuser to the load or to another stage as appropriate.
  • the rotor blade 12 can be solid or hollow and includes a concave forward face 22 in the direction of flow A and an increased curvature concave rear face 24 forming generally a D shape profile pointing away from the direction of flow.
  • the blade 22 occupies a significant proportion of the volume of the rotor space as a result, a "dead space" being defined between the front and rear faces.
  • the forward face is angled generally tangentially and in the direction of flow at the radially innermost inlet region 26 and curves through approximately 180 degrees to extend generally tangentially once again at the radially outer most exit region 28.
  • the opposing rear face 24 of an adjacent blade 12 is profiled to provide a curved flow passage 16 therebetween which exits generally tangentially and is of generally constant width.
  • the specific profile of the blades/volumes of the blades depends on the gas being compressed and the rotor speed and can be optimised for each case as will be apparent to the skilled reader.
  • the exit blade angle is preferably between 20 degrees and 90 degrees (tangential) to a radius of the rotor, as long as sufficient forward speed is provided to allow the flows in the passages of the compressor to re-converge, minimising the pulsation effect.
  • the rotor is also profiled in the axial direction but this can be in an entirely conventional manner which will be apparent to the skilled person and so is not described here.
  • the pressure rise of a turbo compressor is a direct function of the change in tangential velocity of the gas in a rotor such that the greater the change in velocity, the greater the pressure rise.
  • the work input to the gas depends on the change in tangential velocity multiplied by the blade speed, and pressure ratio is a direct function of work input.
  • the exit velocity increases with the tip speed of the blades and hence the diameter of the rotor.
  • the gas is forced to jet forward faster than the blade speed, the tangential velocity is greater still at the exit and hence so is the pressure increase.
  • the blade speed (product of rotor radius and shaft speed) can be reduced and the pressure ratio can be achieved with a lower than normal diameter, in comparison with radial, moderately forward swept or back swept passages. Since the diameter of the rotor is lower, the windage losses are significantly reduced as they are approximately proportionate of the fifth power of diameter of the rotor. For the partial entry machine, it is worth suffering the penalty of low efficiency due to forward sweep since the reduction in windage losses more than makes up for this.
  • a rotor with moderately forward swept blades requires a diameter of 90mm at a speed of 60,000 rpm in order to achieve a pressure ratio of 1.6:1 in air.
  • This same pressure ratio can be achieved according to the invention with a rotor diameter of only 70mm at the same speed and a decrease in windage losses to about 30% of the original value.
  • the compressor described can be used in a single or multi-stage arrangement and any multi-stage arrangement can be nested or a more conventional axial system.
  • the compressor can be driven by any appropriate machine such as a turbine or electrical machine and can be used in any appropriate implementation.

Claims (12)

  1. Un compresseur centrifuge comprenant une pluralité de pales de rotor à entrée partielle à flèche négative (12), possédant chacune une face antérieure (22) dans le sens de rotation, et comprenant en outre un diffuseur possédant une pluralité de parois de passage du diffuseur (20);
    caractérisé en ce que les pales de rotor (22) comprennent chacune une partie de sortie (28) s'étendant dans une direction substantiellement tangentielle à la circonférence du rotor, et les parois de passage du diffuseur (20) s'étendent chacune dans une direction substantiellement tangentielle à la circonférence du rotor, et sont positionnées suffisamment près de la partie de sortie (28) dans une direction radiale, de façon à guider le débit d'air dans une direction substantiellement tangentielle.
  2. Un compresseur centrifuge selon la revendication 1, dans laquelle la pluralité de pales de rotor (12) définit entre elles des passages de flux à flèche négative (16), la flèche des passages de flux (16) étant suffisamment négative pour permettre une convergence des flux d'écoulement provenant de passages individuels à proximité de la sortie du passage (18).
  3. Un compresseur centrifuge selon une quelconque des revendications précédentes, dans lequel chaque pale de rotor (12) présente une face antérieure (22) dans le sens de rotation, et une face postérieure (24) définissant une zone entre elles.
  4. Un compresseur centrifuge selon la revendication 3, dans lequel la face antérieure (22) de la pale de rotor (12) est concave dans le sens de rotation, et la face postérieure (24) de la pale de rotor (12) présente une courbure supérieure, et est convexe dans le sens opposé au sens de rotation.
  5. Un compresseur centrifuge selon la revendication 4, dans lequel la face antérieure (22) est inclinée de façon généralement tangentielle et dans le sens de rotation dans sa région radialement interne (26), et est incurvée d'environ 180 degrés, pour se déployer une nouvelle fois de façon généralement tangentielle lorsqu'elle se trouve dans sa zone radialement externe (28).
  6. Un compresseur centrifuge selon une quelconque des revendications 3 à 5, dans lequel les faces antérieure (22) et postérieure (24) des pales de rotor adjacentes respectives définissent entre elles un passage de flux (16).
  7. Un compresseur centrifuge selon la revendication 6, dans lequel le passage de flux (16) entre des pales de rotor (12) présente une largeur substantiellement constante.
  8. Un compresseur centrifuge selon la revendication 6 ou la revendication 7, dans lequel le passage de flux (16) entre des pales de rotor (12) adjacentes présente une largeur substantiellement constante.
  9. Un compresseur centrifuge selon une quelconque des revendications précédentes, dans lequel les parois de passage du diffuseur (20) sont généralement à flèche négative dans le sens de rotation.
  10. Un compresseur centrifuge selon une quelconque des revendications 6 à 9, dans lequel la largeur tangentielle maximale de chaque pale de rotor est sensiblement plus élevée que la largeur de chaque passage de flux, au point sur le passage qui est adjacent à la partie la plus large de la pale.
  11. Un compresseur centrifuge selon une quelconque des revendications 6 à 9, dans lequel la largeur tangentielle maximale de chaque pale est au moins trois fois plus élevée que la largeur de chaque passage de flux, au point du passage qui est adjacent à la partie la plus large de la pale.
  12. Un compresseur centrifuge selon une quelconque des revendications précédentes, comprenant une pluralité de rotors (10) dans une configuration à plusieurs étages.
EP04768299.2A 2003-09-09 2004-09-02 Rotor de compresseur radial Active EP1682779B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0321088A GB0321088D0 (en) 2003-09-09 2003-09-09 Compressor
PCT/GB2004/003752 WO2005024242A1 (fr) 2003-09-09 2004-09-02 Rotor de compresseur radial

Publications (2)

Publication Number Publication Date
EP1682779A1 EP1682779A1 (fr) 2006-07-26
EP1682779B1 true EP1682779B1 (fr) 2016-11-09

Family

ID=29226749

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04768299.2A Active EP1682779B1 (fr) 2003-09-09 2004-09-02 Rotor de compresseur radial

Country Status (3)

Country Link
EP (1) EP1682779B1 (fr)
GB (1) GB0321088D0 (fr)
WO (1) WO2005024242A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0916901D0 (en) 2009-09-25 2009-11-11 Dynamic Boosting Systems Ltd Diffuser
GB2519503B (en) * 2013-08-19 2015-08-12 Dynamic Boosting Systems Ltd Diffuser for a forward-swept tangential flow compressor

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1158978A (en) * 1909-03-01 1915-11-02 Wilhelm Honegger Turbine-pump, turbine-blower, and propeller.
US3369737A (en) * 1962-12-10 1968-02-20 Gen Electric Radial flow machine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR849795A (fr) * 1939-02-03 1939-12-01 Turbine pour la transformation de la pression d'un fluide en travail ou inversement
US2418012A (en) * 1943-09-20 1947-03-25 Chester Thomas Impeller for centrifugal apparatus
US2681760A (en) * 1949-02-26 1954-06-22 Curtiss Wright Corp Centrifugal compressor
US2845216A (en) * 1952-11-15 1958-07-29 Neu Sa Centrifugal apparatus for the circulation of fluids
CH365822A (de) * 1958-12-24 1962-11-30 Bruno Dr Ing Eck Mit Schaufeln besetztes Laufrad zur Radialförderung von Luft oder Flüssigkeiten
US3140042A (en) * 1961-08-15 1964-07-07 Fujii Noriyoshi Wheels for centrifugal fans of the forward curved multiblade type

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1158978A (en) * 1909-03-01 1915-11-02 Wilhelm Honegger Turbine-pump, turbine-blower, and propeller.
US3369737A (en) * 1962-12-10 1968-02-20 Gen Electric Radial flow machine

Also Published As

Publication number Publication date
WO2005024242A1 (fr) 2005-03-17
EP1682779A1 (fr) 2006-07-26
GB0321088D0 (en) 2003-10-08

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