WO2005024242A1 - Radial compressor impeller - Google Patents
Radial compressor impeller Download PDFInfo
- Publication number
- WO2005024242A1 WO2005024242A1 PCT/GB2004/003752 GB2004003752W WO2005024242A1 WO 2005024242 A1 WO2005024242 A1 WO 2005024242A1 GB 2004003752 W GB2004003752 W GB 2004003752W WO 2005024242 A1 WO2005024242 A1 WO 2005024242A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- rotor
- compressor
- flow
- exit
- radial compressor
- Prior art date
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
- F04D29/26—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 /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.
- Fig. 1 shows a cross-sectional view of a radial compressor according to the present invention
- Fig. 2 shows a cross-sectional view of a radial compressor having an alternative vane configuration.
- 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. It will be appreciated that 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.
- FIG. 4 an alternative diffuser vane profile is shown in Fig. 4 in which the vanes 20 are generally curved forwardly in the direction of rotation A.
- the compressor described can be used in a single or multi-stage arrangement and any multistage 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.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04768299.2A EP1682779B1 (de) | 2003-09-09 | 2004-09-02 | Radialverdichterlaufrad |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB0321088A GB0321088D0 (en) | 2003-09-09 | 2003-09-09 | Compressor |
GB0321088.7 | 2003-09-09 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005024242A1 true WO2005024242A1 (en) | 2005-03-17 |
Family
ID=29226749
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/GB2004/003752 WO2005024242A1 (en) | 2003-09-09 | 2004-09-02 | Radial compressor impeller |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP1682779B1 (de) |
GB (1) | GB0321088D0 (de) |
WO (1) | WO2005024242A1 (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011036459A1 (en) | 2009-09-25 | 2011-03-31 | Dynamic Boosting Systems Limited | Diffuser |
WO2015025132A1 (en) * | 2013-08-19 | 2015-02-26 | Dynamic Boosting Systems Limited | Diffuser for a forward-swept tangential flow compressor |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2268929A (en) * | 1939-02-03 | 1942-01-06 | Dupont Emile | Compressor or the like |
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 |
US3369737A (en) | 1962-12-10 | 1968-02-20 | Gen Electric | Radial flow machine |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1158978A (en) * | 1909-03-01 | 1915-11-02 | Wilhelm Honegger | Turbine-pump, turbine-blower, and propeller. |
-
2003
- 2003-09-09 GB GB0321088A patent/GB0321088D0/en not_active Ceased
-
2004
- 2004-09-02 EP EP04768299.2A patent/EP1682779B1/de active Active
- 2004-09-02 WO PCT/GB2004/003752 patent/WO2005024242A1/en active Application Filing
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2268929A (en) * | 1939-02-03 | 1942-01-06 | Dupont Emile | Compressor or the like |
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 |
US3369737A (en) | 1962-12-10 | 1968-02-20 | Gen Electric | Radial flow machine |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011036459A1 (en) | 2009-09-25 | 2011-03-31 | Dynamic Boosting Systems Limited | Diffuser |
WO2015025132A1 (en) * | 2013-08-19 | 2015-02-26 | Dynamic Boosting Systems Limited | Diffuser for a forward-swept tangential flow compressor |
CN105683582A (zh) * | 2013-08-19 | 2016-06-15 | 动力推进系统有限公司 | 用于前掠切向流压缩机的扩散器 |
US20160195107A1 (en) * | 2013-08-19 | 2016-07-07 | Dynamic Boosting Systems Limited | Diffuser for a Forward-Swept Tangential Flow Compressor |
US10174766B2 (en) | 2013-08-19 | 2019-01-08 | Dynamic Boosting Systems Limited | Diffuser for a forward-swept tangential flow compressor |
Also Published As
Publication number | Publication date |
---|---|
EP1682779A1 (de) | 2006-07-26 |
EP1682779B1 (de) | 2016-11-09 |
GB0321088D0 (en) | 2003-10-08 |
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