WO1999036701A1 - Turbomachines centrifuges - Google Patents

Turbomachines centrifuges Download PDF

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Publication number
WO1999036701A1
WO1999036701A1 PCT/JP1999/000077 JP9900077W WO9936701A1 WO 1999036701 A1 WO1999036701 A1 WO 1999036701A1 JP 9900077 W JP9900077 W JP 9900077W WO 9936701 A1 WO9936701 A1 WO 9936701A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
impeller
outlet
inlet
hub
Prior art date
Application number
PCT/JP1999/000077
Other languages
English (en)
Japanese (ja)
Inventor
Hideomi Harada
Shin Konomi
Original Assignee
Ebara Corporation
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 Ebara Corporation filed Critical Ebara Corporation
Priority to EP99900291A priority Critical patent/EP1048850B1/fr
Priority to US09/600,237 priority patent/US6338610B1/en
Priority to DE69932408T priority patent/DE69932408T2/de
Publication of WO1999036701A1 publication Critical patent/WO1999036701A1/fr

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
    • F04D29/18—Rotors
    • F04D29/22—Rotors specially for centrifugal pumps
    • F04D29/24—Vanes
    • F04D29/242—Geometry, shape
    • 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

Definitions

  • the present invention relates to an improvement of an impeller of a machine generally called a "turbo machine” such as a centrifugal liquid pump for pumping a liquid and a blower and a compressor for pumping a gas.
  • aturbo machine such as a centrifugal liquid pump for pumping a liquid and a blower and a compressor for pumping a gas.
  • FIGS. 9A to 10B show a typical turbomachine, in which a casing (not shown) having required piping is provided with a hub 2, a shroud 4, and an impeller 6 including a plurality of blades 3 therebetween. And a rotary shaft 1 connected to a rotary drive source.
  • the upper end 3a of the blade 3 is covered with a shroud surface 4a, and a space surrounded by two adjacent blades 3, a hub surface 2a and a shroud surface 4a flows.
  • the road is constructed.
  • the impeller 6 rotates at the rotational angular velocity ⁇ about the rotation axis 1, so that the fluid flowing into the flow path from the impeller inlet 6 a via the suction pipe and the like to the impeller outlet 6 b Transported to the outside of the machine via a discharge pipe.
  • the surface facing the rotating direction of the blade 3 is the pressure surface 3b.
  • the opposite surface is the suction surface 3c.
  • the three-dimensional shape of the closed impeller is schematically shown with most of the shroud surface broken.
  • a separate part for forming the shoulder surface 4 Although there is no material, the casing outside the figure surrounding the impeller 6 mechanically also serves as the shroud surface 4, and there is no difference in the basic structure of the fluid dynamics from the closed impeller. The following description proceeds with an example of a closed impeller.
  • the low-energy fluid in the boundary layer that is accumulated in a specific area of the flow channel due to the action of the secondary flow induces large-scale flow separation, causing a rising characteristic to the right, resulting in a stable turbomachine. It is known to cause inconvenience such as hindering driving.
  • the secondary flow in the impeller is roughly classified into a secondary flow between blades generated along the shroud surface or hub surface, and a secondary flow in the meridian plane generated along the pressure surface or suction surface of the blade. It is known that secondary flow between blades can be suppressed by curving the blade shape backward.
  • the other secondary flow on the meridian plane requires detailed optimization of the three-dimensional shape of the flow channel and cannot be easily weakened or canceled.
  • the distribution of the relative pressure field p * is high on the hub side and low on the shroud side so as to balance the centrifugal force W 2 ZR toward the hub side and the corerica 2 ⁇ W ⁇ in FIG. 9B. Distribution. In the boundary layer along the blade surface, the relative velocity W decreases due to the effect of the wall surface, so the centrifugal force W 2 / R and the corioliser 2 w W 6 acting on the fluid inside the boundary layer are small. Therefore, it cannot be balanced with the mainstream pressure field p * described above.
  • the low-energy fluid in the boundary layer moves toward the region with a small relative pressure p *, and on the pressure surface 3 b or the suction surface 3 c of the blade 3, along the blade surface from the hub side to the shroud side.
  • Meridian secondary flow toward. are indicated in FIG. 9A by dashed arrows on pressure surface 3b of blade 3 and solid arrows on suction surface 3c.
  • the secondary flow on the meridional surface can occur on both the suction surface 3c and the pressure surface 3b of the blade 3, but since the boundary layer on the suction surface 3c is generally thicker, the secondary flow on the suction surface 3c It is known that the generation of the next flow greatly affects the performance characteristics of turbomachines.
  • a circumferential blade inclination is formed so as to precede the rotation direction of the impeller, so that a force having a component directed toward the shroud surface 4 acts on the fluid, and
  • the relative pressure field in the road generates a high relative pressure P * on the shroud surface side and a low relative pressure p * on the hub surface 2 side in order to balance against the force component going to the shroud surface.
  • the blade inclination angle is configured to exhibit a small inclination as the dimensionless meridian length m increases, the blade inclination is simply shifted in the circumferential direction by the blade on the side of the circle. As compared with the case, the effect of the inclination of the blade can be made higher.
  • the root of such a blade is a welded structure when the impeller is welded, and it is easy to cause welding problems if the blade is inclined, and if the blade is insufficient, it is rotated. This may cause cracks in that area, leading to destruction. Also, high stresses in this area affect the service life of the impeller, and therefore place high demands on welding techniques and materials, which in turn increases production costs. Also, in the case of manufacturing by machine cutting, complicated machining must be performed, resulting in an increase in manufacturing cost. Disclosure of the invention
  • the present invention effectively reduces the secondary flow in the impeller flow path without causing an excessive increase in manufacturing cost, thereby reducing the loss.
  • the objective is to provide an efficient centrifugal turbomachine by minimizing wastewater.
  • a plurality of blades are provided between an inlet on the center side and an outlet on the outer peripheral side, and a flow path for sending a fluid from the inlet to the outlet is formed between the blades by rotation of the impeller.
  • the blade inclination angle defined as the angle the blade makes with respect to the plane perpendicular to the hub surface, has a decreasing tendency from the inlet to the outlet, and therefore, when viewed from the front of the blade inlet.
  • An impeller characterized in that the center lines of the blades on the shroud side and the hub side intersect in a dimensionless radius position indicated by a ratio with respect to the exit radius of the impeller in a range of 0.8 to 0.95. is there.
  • an impeller rotatably accommodated in the casing is provided, and a plurality of blades are provided between an inlet on the center side and an outlet on the outer peripheral side of the impeller, and the impeller rotates between these blades.
  • a flow path for sending fluid from the inlet to the outlet is formed by the blade, the blade has a circumferential blade inclination such that the hub side precedes the shroud side of the blade in the rotation direction of the impeller.
  • the blade inclination angle defined as the angle formed by the blade with respect to the plane perpendicular to the hub surface shows a decreasing tendency from the inlet to the outlet.
  • FIGS 1A and 1B are diagrams schematically showing the shapes of the blades of the turbomachine according to the embodiment of the present invention.
  • FIG. 1A is a meridional view
  • FIG. 1B is a front view
  • 2A and 2B are diagrams schematically showing the shapes of the blades of a turbo machine according to another embodiment of the present invention.
  • FIG. 2A is a meridional view
  • FIG. 2B is a front view.
  • FIG. 3A and 3B are diagrams schematically showing the shapes of the blades of a turbomachine according to another embodiment of the present invention.
  • FIG. 3A is a meridional view
  • FIG. 3B is a front view.
  • FIG. 4A and 4B are diagrams schematically showing the shapes of the blades of a turbomachine according to another embodiment of the present invention, wherein FIG. 4A is a meridional view and FIG. 4B is a front view.
  • Fig. 5 is a diagram showing the relationship between the lean angle ⁇ at the tip of the blade at the entrance of the closed impeller and the stress generated at the root of the blade on the exit side of the impeller.
  • Fig. 6 shows the relationship between the rake angle y of the closed impeller and the stress at the root of the blade at the entrance of the impeller.
  • FIG. 7A and 7B are diagrams showing the shape of an impeller as a simulation model for advancing the analysis.
  • FIG. 7A is a meridional view
  • FIG. 7B is a front view.
  • FIG. 8 is a graph showing a result of a test in which an impeller having a shape according to the present invention was attached to a stage of a compressor.
  • FIGS. 9A and 9B are views showing the shape of an impeller of a conventional centrifugal turbomachine, FIG. 9A is a perspective view, and FIG. 9B is a meridional view.
  • FIG. 1OA and 1OB are diagrams showing the shape of the blades of the impeller of the conventional centrifugal turbomachine, FIG. 1OA is a cross-sectional view, and FIG. 10B is a front view.
  • Figures 11A and 11B also show other impellers of a conventional centrifugal turbomachine. It is a figure which shows the shape of a blade
  • FIGS. 12A and 12B are views showing the shape of the blades of another impeller of the conventional centrifugal turbomachine.
  • FIG. 12A is a sectional view
  • FIG. 12B is a front view. It is. BEST MODE FOR CARRYING OUT THE INVENTION
  • FIGS. 1A to 4B Embodiments of the impeller having such a shape are shown in FIGS. 1A to 4B.
  • FIGS. 1A and 1B show a specific speed of 500
  • FIGS. 2A and 2B show a specific speed of 400
  • FIGS. 3A and 3B show a specific speed of 350
  • 4A and FIG. 4B show a specific speed of 250.
  • These impellers are designed based on the following ideas.
  • the inventor of the present invention has a circumferential blade inclination such that the hub side of the blade precedes the rotating direction of the impeller with respect to the blade side of the blade as shown in FIGS. 11A and 11B, As the dimensionless meridian length m increases, the blade inclination angle, defined as the angle formed by the center line of the blade cross section with respect to the plane perpendicular to the hub surface, decreases on the impeller flow path cross section. Based on the impeller with a tendency to show a shape, we simulated it by changing several parameters with the aim of suppressing excessive inclination. As a guideline for such a maximum value of the inclination angle, 110% of the stress acting when there is no inclination was considered appropriate.
  • Figure 5 shows the angle (lean angle) between the line connecting the center of the blade on the shroud side and the hub, and the line connecting the center of the blade on the hub side and the center of the impeller at the tip of the blade at the entrance of the closed impeller.
  • ⁇ is plotted on the horizontal axis, and the stress generated at the root of the blade on the exit side of the impeller is calculated. It is shown on the basis of the time. From this figure, it can be seen that the stress increases as the lean angle increases. In this figure, if the allowable stress of the slat is defined as 110% of the stress when the lean angle is 0 degree, the limit angle at that time is 25 degrees.
  • Fig. 6 shows the angle between the line connecting the shroud side of the closed impeller and the center of the blade on the hub side and the plane perpendicular to the hub surface (rake angle ⁇ ) on the horizontal axis.
  • the ordinate shows the stress at the root of the blade, and it can be seen that the stress increases as the rake angle increases. In this figure, if the allowable stress of the blade is defined as 110% of the stress at a rake angle of 0 degree, the limit angle at that time is 20 degrees.
  • Figures 7 7 and 7 ⁇ show the shape of the impeller as a simulation model for further analysis.
  • Fig. 7A shows a meridional view
  • Fig. 7B shows a front view.
  • a straight line is connected between the inlet and the outlet on the hub side and the chassis side of the impeller.
  • the shape of the blade is slightly different from this shape because it is composed of curves.
  • FIG. 1A to 4B show a front view and a meridional view of impellers developed by the inventors, each having a different specific speed.
  • the center lines of the blades on the shroud side and the hub side intersect near the exit of the impeller, and the intersection is defined by the ratio to the exit radius of the impeller. It can be seen that the dimensional radius position is in the range of 0.8 to 0.95.
  • Fig. 8 shows an example of the result of a test in which the impeller according to the present invention was attached to a stage of a compressor, and it was found that the performance was significantly better than that of a stage having a conventional shape of an impeller. I will.
  • the secondary flow in the impeller flow path is effectively reduced without causing an excessive increase in the manufacturing cost, and the loss due to the secondary flow is minimized.
  • An efficient centrifugal turbomachine can be provided.
  • the present invention has industrial application by being used for an impeller of a machine generally called a "turbo machine” such as a centrifugal liquid pump and a blower and a compressor for pumping gas.
  • a Turbo machine such as a centrifugal liquid pump and a blower and a compressor for pumping gas.

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

Abstract

Turbomachine centrifuge permettant d'éviter une augmentation excessive des coûts de fabrication, conçue pour limiter efficacement un écoulement secondaire dans un passage d'écoulement de roue à aubes, ainsi que la perte inhérente à cet écoulement secondaire, et possédant une capacité élevée. Cette turbomachine comprend une roue à aubes composée d'une pluralité d'aubes (3) situées entre une entrée centrale (6a) et une sortie périphérique extérieure (6b), et un passage d'écoulement situé entre ces aubes et servant à envoyer un liquide depuis l'entrée jusqu'à la sortie sous l'effet de la rotation de la roue à aubes, les parties des aubes (3) placées du côté d'un moyeu (2) présentant une inclinaison périphérique précédant dans le sens de rotation de la roue à aubes celle des parties des aubes situées sur le côté d'un carénage (4), l'angle d'inclinaison des aubes défini en tant qu'angle des aubes situées dans un plan observé depuis la sortie du passage d'écoulement par rapport à un plan perpendiculaire à la surface du moyeu, tendant à diminuer depuis l'entrée vers la sortie, les lignes médianes d'une partie côté carénage et d'une partie côté moyeu observées depuis une section avant de l'entrée de l'aube, venant en intersection dans une position dans laquelle le rapport entre un rayon sans dimension et un rayon de la sortie est égal à 0,8-0,95.
PCT/JP1999/000077 1998-01-14 1999-01-13 Turbomachines centrifuges WO1999036701A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP99900291A EP1048850B1 (fr) 1998-01-14 1999-01-13 Turbomachines centrifuges
US09/600,237 US6338610B1 (en) 1998-01-14 1999-01-13 Centrifugal turbomachinery
DE69932408T DE69932408T2 (de) 1998-01-14 1999-01-13 Radiale strömungsmaschine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP1017898 1998-01-14
JP10/17898 1998-01-14

Publications (1)

Publication Number Publication Date
WO1999036701A1 true WO1999036701A1 (fr) 1999-07-22

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PCT/JP1999/000077 WO1999036701A1 (fr) 1998-01-14 1999-01-13 Turbomachines centrifuges

Country Status (1)

Country Link
WO (1) WO1999036701A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2009057959A (ja) * 2007-08-03 2009-03-19 Hitachi Plant Technologies Ltd 遠心圧縮機とその羽根車およびその運転方法
CN102472293A (zh) * 2009-07-29 2012-05-23 三菱重工业株式会社 离心压缩机的叶轮
WO2013073469A1 (fr) * 2011-11-17 2013-05-23 株式会社日立プラントテクノロジー Machine à fluide centrifuge
JP2015071972A (ja) * 2013-10-03 2015-04-16 株式会社Ihi 遠心圧縮機
WO2016157584A1 (fr) * 2015-03-30 2016-10-06 三菱重工業株式会社 Hélice et compresseur centrifuge
RU2661801C1 (ru) * 2017-07-10 2018-07-19 Общество с ограниченной ответственностью Научно-производственная фирма "АДЕС" Рабочее колесо центробежного насоса
JP2020518761A (ja) * 2017-07-03 2020-06-25 ▲広▼▲東▼威▲靈▼▲電▼机制造有限公司 インペラ、ファン及びモータ

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5784394U (fr) * 1980-11-12 1982-05-25
JPS6029840B2 (ja) * 1980-12-19 1985-07-12 株式会社日軽技研 羽根車の製造方法
JPS6133963B2 (fr) * 1981-04-13 1986-08-05 Nitsukei Giken Kk
JPS6235100A (ja) * 1985-08-07 1987-02-16 Matsushita Electric Ind Co Ltd 送風装置

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5784394U (fr) * 1980-11-12 1982-05-25
JPS6029840B2 (ja) * 1980-12-19 1985-07-12 株式会社日軽技研 羽根車の製造方法
JPS6133963B2 (fr) * 1981-04-13 1986-08-05 Nitsukei Giken Kk
JPS6235100A (ja) * 1985-08-07 1987-02-16 Matsushita Electric Ind Co Ltd 送風装置

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2009057959A (ja) * 2007-08-03 2009-03-19 Hitachi Plant Technologies Ltd 遠心圧縮機とその羽根車およびその運転方法
CN102472293A (zh) * 2009-07-29 2012-05-23 三菱重工业株式会社 离心压缩机的叶轮
US8956118B2 (en) 2009-07-29 2015-02-17 Mitsubishi Heavy Industries, Ltd. Impeller of centrifugal compressor
WO2013073469A1 (fr) * 2011-11-17 2013-05-23 株式会社日立プラントテクノロジー Machine à fluide centrifuge
JP2013104417A (ja) * 2011-11-17 2013-05-30 Hitachi Plant Technologies Ltd 遠心式流体機械
US10125773B2 (en) 2011-11-17 2018-11-13 Hitachi, Ltd. Centrifugal fluid machine
JP2015071972A (ja) * 2013-10-03 2015-04-16 株式会社Ihi 遠心圧縮機
WO2016157584A1 (fr) * 2015-03-30 2016-10-06 三菱重工業株式会社 Hélice et compresseur centrifuge
US10947988B2 (en) 2015-03-30 2021-03-16 Mitsubishi Heavy Industries Compressor Corporation Impeller and centrifugal compressor
JP2020518761A (ja) * 2017-07-03 2020-06-25 ▲広▼▲東▼威▲靈▼▲電▼机制造有限公司 インペラ、ファン及びモータ
RU2661801C1 (ru) * 2017-07-10 2018-07-19 Общество с ограниченной ответственностью Научно-производственная фирма "АДЕС" Рабочее колесо центробежного насоса
WO2019013672A1 (fr) * 2017-07-10 2019-01-17 Общество с ограниченной ответственностью Научно-производственная фирма "АДЕС" Roue de travail d'une pompe centrifuge

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