WO2012077580A1 - Turbomachine centrifuge - Google Patents

Turbomachine centrifuge Download PDF

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Publication number
WO2012077580A1
WO2012077580A1 PCT/JP2011/077863 JP2011077863W WO2012077580A1 WO 2012077580 A1 WO2012077580 A1 WO 2012077580A1 JP 2011077863 W JP2011077863 W JP 2011077863W WO 2012077580 A1 WO2012077580 A1 WO 2012077580A1
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WO
WIPO (PCT)
Prior art keywords
diffuser
blade
hub
distribution
blades
Prior art date
Application number
PCT/JP2011/077863
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English (en)
Japanese (ja)
Inventor
和之 杉村
秀夫 西田
小林　博美
俊雄 伊藤
Original Assignee
株式会社日立プラントテクノロジー
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.)
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Application filed by 株式会社日立プラントテクノロジー filed Critical 株式会社日立プラントテクノロジー
Priority to CN201180058898.2A priority Critical patent/CN103314218B/zh
Priority to EP11847208.3A priority patent/EP2650546A1/fr
Priority to US13/992,457 priority patent/US20130309082A1/en
Publication of WO2012077580A1 publication Critical patent/WO2012077580A1/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
    • F04D29/40—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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/06—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially radially
    • 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

Definitions

  • the present invention relates to a centrifugal turbomachine equipped with a centrifugal impeller such as a centrifugal compressor, a centrifugal blower, a centrifugal fan, or a centrifugal pump.
  • a centrifugal impeller such as a centrifugal compressor, a centrifugal blower, a centrifugal fan, or a centrifugal pump.
  • a multistage centrifugal compressor which is a type of centrifugal turbomachine
  • a large number of impellers are attached to the same shaft, and a diffuser and a return guide vane are provided downstream of each impeller.
  • the impeller, diffuser, and return guide vane constitute a paragraph.
  • a vaneless diffuser, a vaned diffuser, a low string ratio diffuser which is a kind of vaned diffuser, and the like are used depending on the purpose and application.
  • the low chord ratio ratio diffuser does not have a geometric throat, and therefore has a characteristic that the choke margin, which is the operating range on the large flow rate side, can be expanded.
  • the blade surface separation is suppressed by the boundary layer sweeping effect on the blade surface due to the secondary flow, so that the surge margin that is the operating range on the small flow rate side can be sufficiently secured. have. For this reason, a low-string ratio diffuser is frequently used.
  • a diffuser with blades for centrifugal turbomachines typified by a low chord joint ratio diffuser
  • a two-dimensional blade in which the same airfoil is stacked in the height direction of the blade is generally used.
  • three-dimensional blades have also been attempted.
  • the difference angle of the cross section of the diffuser blades is gradually changed in the height direction of the diffuser.
  • the wing is designed to achieve both high efficiency and a wide operating range by realizing collisionless inflow for non-uniformly distributed inflow.
  • the central portion of the blade height is curved in the downstream direction at the front edge portion of the diffuser to change the diffuser inlet diameter. This realizes collisionless inflow with respect to the non-uniformly distributed inflow, thereby achieving both high efficiency and a wide operating range.
  • the diffuser blade when forming a three-dimensional diffuser blade, the diffuser blade is virtually divided into a plurality of axial directions (directions from the hub surface toward the shroud surface). It is described that they are stacked. At that time, a bow diffuser blade has been suggested in which the lean angle, which is the angle formed by the blade stacking direction with respect to the direction perpendicular to the hub surface or the shroud surface, is changed along the span of the diffuser blade.
  • the inflow angle is matched by applying a lean to a local portion called the diffuser leading edge, but the configuration of the curve element diffuser is not adopted, and the curve There is no consideration for controlling the secondary flow of the flow path between the diffuser blades that becomes noticeable when the element diffuser is employed.
  • the present invention has been made in view of the above-described problems of the prior art, and the object thereof is a secondary flow between blades in a bladed diffuser used in a centrifugal turbomachine when a curved element diffuser is used to improve efficiency. Is to effectively suppress the performance and improve the performance.
  • Another object of the present invention is to obtain a stacking pattern of divided blades for improving performance in such a curved element diffuser used in a centrifugal compressor.
  • FIG. 1 is a plan view of one diffuser blade for explaining the movement of an airfoil
  • FIG. 2 is a perspective view showing one blade of a diffuser with blades taken out. It is a figure which shows a mode that it accumulates in a direction.
  • the coordinate system is a cylindrical coordinate system (R, ⁇ , Z) in which the radial direction of the impeller is R, the rotational direction of the impeller is ⁇ , and the axial direction of the rotation shaft is Z.
  • Z is positive in the direction from the shroud 102 side toward the hub 101 side.
  • Chord (C) A line connecting the leading edge 208 and the trailing edge 209 in the airfoil 104 as a reference of the diffuser blade 103.
  • Lean Degree of inclination of the diffuser blade 103 with respect to the hub 101 surface, which can be regarded as a combination of sweep and dihedral described below.
  • Misalignment angle ( ⁇ SG ): Angle formed by the chord C and the radial direction (R direction) (tan ⁇ SG dC / dR).
  • Sweep ( ⁇ ) In the case represented by the one-dot chain line in FIG. 1, the case where the airfoil 104 of the diffuser blade 103 is moved in the chord C direction and moved downstream is defined as positive.
  • Blade height (h) The height of the diffuser blade measured from the hub surface side. When the hub surface and the shroud surface are parallel walls perpendicular to the axis, the height is in the ⁇ Z direction. If at least one of the hub surface and the shroud surface is an inclined surface, the height from the line connecting the leading edge and the trailing edge on the hub side of the diffuser blade is set. The height of the middle point in the flow direction between the leading edge and trailing edge, with reference to the line connecting the hub edge of the diffuser blade and the leading edge of the shroud and the line connecting the hub edge of the diffuser blade and the trailing edge of the shroud To decide.
  • the total height of the wing is represented by H.
  • the present invention uses such a definition to include a hub, a shroud, and a plurality of blades arranged at intervals in the circumferential direction between the hub and the shroud on the same rotating shaft.
  • a centrifugal turbomachine equipped with at least one impeller and having a vaned diffuser downstream of at least one of the at least one impeller, the vaned diffuser is formed on the downstream side of the impeller.
  • a plurality of blades are arranged in the flow path at intervals in the circumferential direction, and each blade has a shape in which the reference blades are stacked in the blade height direction, which is the axial direction of the rotating shaft.
  • the hub It is characterized in that it has a non-uniform towards the intermediate portion of the blade height from the hub-side end portion in the side.
  • each of the diffuser blades is a distribution that increases from the hub side end portion toward the middle portion of the blade height, and each of the diffuser blades is the leading edge portion of the hub side end portion. It is preferable that an imaginary plane and the suction surface of the diffuser blade form an obtuse angle.
  • the dihedral distribution is a distribution that increases from the shroud side end toward the middle part of the blade height, and each of the diffuser blades is a plane that is virtually formed at the front edge of the shroud side end. It is preferable to make an obtuse angle with the suction surface of the diffuser blade.
  • the dihedral distribution of each diffuser blade is a distribution that decreases from the end on the hub side to the middle portion of the blade height, and is parallel to the chord direction of the reference blade and downstream.
  • the sweep distribution in which the movement is a positive movement may be a distribution that decreases from the hub side end toward the middle of the blade height.
  • each of the diffuser blades preferably has at least one of the dihedral distribution and the sweep distribution applied to at least the first half of the flow direction of the blade.
  • a curved element three-dimensional blade is applied to a diffuser blade, and a flow distribution loss to the diffuser blade is reduced by giving a sweep distribution and a dihedral distribution.
  • the flow in the blade intermediate part can be controlled, the secondary flow between the blades can be effectively suppressed, and the diffuser performance and the compressor performance can be improved.
  • FIG. 1 is a longitudinal sectional view of an embodiment of a centrifugal turbomachine according to the present invention. It is a figure explaining the classification
  • FIG. 6 is a perspective view and a partially enlarged view of a diffuser having a dihedral distribution shown in FIG. 5.
  • FIG. 8 is a perspective view of a diffuser having a dihedral distribution shown in FIG. 7 and a partially enlarged view thereof. It is a figure which shows the dihedral distribution and sweep distribution of further another Example of the diffuser which the compressor shown in FIG. 3 has.
  • FIG. 10 is a perspective view of a diffuser having a dihedral distribution and a sweep distribution shown in FIG. 9 and a partially enlarged view thereof. It is a figure which shows an example of the performance diagram in the centrifugal compressor provided with the diffuser which concerns on this invention.
  • a multistage centrifugal compressor 300 as an example of a centrifugal turbomachine will be described with reference to a longitudinal sectional view of FIG.
  • the multistage centrifugal compressor 300 is a two-stage centrifugal compressor.
  • the subject of the present invention may be a single-stage or multi-stage centrifugal turbomachine, and is not particularly limited to a two-stage compressor.
  • the multistage centrifugal compressor 300 shown in FIG. 3 is a two-stage compressor including a first stage 301 and a second stage 302.
  • the first stage impeller 308 and the second stage impeller 311 are attached to the same rotating shaft 303 to constitute a rotating body.
  • the rotary shaft 303 is rotatably supported by a journal bearing 304 and a thrust bearing 305 attached to a compressor casing 306 that houses the rotary shaft 303 and the impellers 308 and 311.
  • a diffuser 309 that recovers the pressure of the working gas compressed by the impeller 308 to form a radially outward flow, and a working gas that is made radially outward by the diffuser 309.
  • a return guide vane 310 is arranged to guide the second flow impeller 311 inward in the radial direction.
  • a diffuser 312 and a collecting means 313 called a collector or a scroll for collectively sending the working gas whose pressure has been increased by the two-stage diffuser 312 to the outside of the apparatus are arranged downstream of the two-stage impeller 311, a diffuser 312 and a collecting means 313 called a collector or a scroll for collectively sending the working gas whose pressure has been increased by the two-stage diffuser 312 to the outside of the apparatus are arranged downstream of the two-stage impeller 311, a diffuser 312 and a collecting means 313 called a collector or a scroll for collectively sending the working gas whose pressure has been increased by the two-stage diffuser 312 to the outside
  • the impellers 308 and 311 at each stage have a plurality of blades 308c and 311c arranged at substantially equal intervals in the circumferential direction between the core plates 308a and 311a and the side plates 308b and 311b and the core plates 308a and 311a and the side plates 308b and 311b. And have.
  • a suction labyrinth seal 315 is disposed on the outer peripheral portion of the impellers 308 and 311 on the side plate 308b and 311b side, and shaft seals 316 and 317 are disposed on the back side of the core plates 308a and 311a.
  • the working gas flowing in from the suction nozzle 307 passes through the first stage impeller 308, the vaned diffuser 309, the return guide vane 310, the second stage impeller 311, and the vaned diffuser 312 in this order, and a collecting means such as a collector and a scroll. Guided to 313 without leaking.
  • the diffusers 309 and 312 used in the centrifugal compressor 300 configured as described above will be described in detail below.
  • the diffuser 309 is attached to a diaphragm constituting a part of the compressor casing 306, and a hub 309 a whose flow path surface is substantially in the same axial position as the flow path surface of the impeller 308, and a surface around the hub 309. And a plurality of wings 309c erected at intervals in the direction.
  • the wall surface of the inner casing which comprises a part of compressor casing 306 forms a flow path as a shroud surface.
  • the diffuser 312 has the same configuration. In the present embodiment, the above configuration will be described. However, the configuration of the diffuser is not limited to this, and a configuration in which the diffuser is separated from the diaphragm is included in the present invention.
  • FIG. 4 shows the vaned diffuser 400 used for the following description in a classified manner.
  • FIG. 4A is a cross-sectional view of the diffuser 400.
  • a plurality of diffuser blades 420a are erected on the hub plate 410a at substantially equal intervals in the circumferential direction.
  • a flow exiting an impeller (not shown) is guided to flow along the blade 420a from the inner peripheral side as indicated by an arrow FL in the figure. Rotational direction of the impeller (not shown) this time is the direction of the arrow R N.
  • the shape of the diffuser is represented by a conventionally used two-dimensional diffuser (FIG. 4 (b)), a linear element having a lean three-dimensional diffuser (FIG. 4 (c)), and a set of curved elements having the same lean.
  • the curved element is classified into a three-dimensional diffuser (FIG. 4D).
  • each of the diffuser blades 420b to 420d is represented as a shape in which the contours of the hub plate side cross sections 421b to 421d and the contours of the shroud side cross sections 422b to 422d are connected by line elements 423b to 423d.
  • the same flow is discharged from the impeller to each of the diffuser blades 420b to 420d to form a diffuser inlet flow 402.
  • the linear element two-dimensional diffuser blade 420b shown in FIG. 4B is a two-dimensional diffuser composed of non-inclined linear elements 423b that stack the same airfoil straight in the height direction of the blade 420b. That is, the linear element 423b is perpendicular to the hub plate 410a.
  • a diffuser having such a blade 420b it is possible to prevent the flow from colliding with the blade 420b at any height direction (h direction) position of the leading edge of the blade 420b when the inflow flow 402 is distributed.
  • h direction height direction
  • the difference angle ( ⁇ SG ) is changed to give a twist to the diffuser blade 420c.
  • the flow exiting the impeller can flow in without colliding with the diffuser blade 420c. That is, even if a non-uniform flow is discharged from the impeller, the front edge portion of the diffuser blade 420c can have a blade 420c shape corresponding to the inflow flow 402.
  • the linear element 423c that connects the contour of the hub plate side section 421c and the contour of the shroud side section 422c is a straight line, and the lean distribution in the height direction (h direction) of the blade 420c is also a straight line.
  • the line element 423c is not necessarily perpendicular to the hub surface 410a.
  • the airfoil shape of the blade 420c is basically formed by, for example, a NACA blade, and therefore cannot be changed to a value corresponding to the flow angle. Therefore, although an improvement in efficiency can be expected as compared with the two-dimensional diffuser, it is difficult to sufficiently control the flow.
  • the airfoils are stacked along an arbitrary curved element 423d. That is, the curved element 423d that connects the outline of the hub plate side section 421d and the outline of the shroud side section 422d is a curve.
  • the lean angle is varied in the height direction (h direction) of the blade 420d. Therefore, the curved element three-dimensional diffuser can not only realize collisionless inflow at the leading edge of the blade 420d, but also can change the direction of operation of the blade force by curving the flow path surface of the blade 420d.
  • the vaned diffusers 309 and 312 that collect the dynamic pressure at the outlets of the impellers 308 and 311 as static pressures are formed into a three-dimensional curved element.
  • the diffuser three-dimensional By the way, various methods are conceivable for making the diffuser three-dimensional, but if the above-described dihedral and sweep are used, the three-dimensionalization can be handled systematically. Therefore, a specific example of a curved element three-dimensional diffuser represented by using a dihedral and a sweep will be described with reference to FIGS. In the following description, the first-stage diffuser 309 will be described as an example, but the second-stage and subsequent diffusers can be handled in the same manner.
  • FIG. 5 is a diagram showing a dihedral distribution with respect to the blade height direction (h direction) of the blade 620.
  • the amount of the die helical ( ⁇ ) is dimensionless by the chord length (C), and the blade height is dimensionless at the total height H. It has become.
  • 6A and 6B are perspective views of the diffuser 600 having the dihedral distribution of FIG. 5, in which FIG. 6A is an overall perspective view, FIG. 6B is a detailed view of a portion C of FIG. 5A, and FIG. (A) is the D section detailed drawing of figure (a).
  • the diffuser plate 610 is attached to the hub side of the impeller.
  • the negative pressure surface of the diffuser blade 620 is a blade surface on the back side with respect to the rotation direction of the impeller.
  • the influence of the dihedral distribution and the sweep distribution on the performance is generally small in a portion other than the rounded portion 501, that is, the vicinity of the hub side end surface 501. . Therefore, the part other than the hub side end face vicinity 501 can set the die-hedra distribution and the sweep distribution in consideration of the workability and handleability of the blade 309c.
  • a blade force component 602 is generated in the blade height direction.
  • the blade force component 602 has an effect of pushing back the secondary flow because the boundary layer on the hub surface 603 is in the opposite direction to the secondary flow that tries to go around the hub-side negative pressure surface 601. Therefore, according to the present embodiment, the secondary flow is suppressed, the flow distribution between the blades is made uniform, and the diffuser performance is improved.
  • FIG. 7 is a dihedral distribution diagram
  • FIG. 8 is a perspective view of the diffuser 800 having the dihedral distribution shown in FIG. 8A is a perspective view of the entire diffuser 800
  • FIG. 8B is a detailed view of an E portion of FIG. 8A
  • FIG. 8C is a detailed view of an F portion of FIG. 8A.
  • the diffuser plate 810 is attached to the hub side of the impeller. It differs from the above embodiment in that the die heddle is reduced in the blade height direction in the vicinity of the shroud side end face (circled 702).
  • the influence of the dihedral distribution was large on the hub surface side, but it was found that the dihedral distribution on the shroud surface side also affected the diffuser depending on the flow flowing out of the impeller. Even in this case, the shroud-side dihedral distribution needs to be the same as in the above embodiment. A specific example will be described below.
  • the dihedral amount ( ⁇ ) is increased in the blade height direction (h direction) in the same manner as in the above embodiment (see circle 701). Also in this embodiment, the sensitivity given to the performance by the dihedral distribution and the sweep distribution in the center region in the blade height direction excluding the two regions near the hub side end surface and the shroud side end surface was small. That is, in the vicinity of both end surfaces on the hub side and the shroud side, the angle formed between the suction surfaces 801 and 802 of the diffuser blade 820 and the hub end surface and the shroud end surface is an obtuse angle. The flow can be suppressed.
  • the distribution shown in FIG. 7 should be used.
  • the distribution shown in FIG. 5 should be used. This is because the diffuser blade 820 is affected by the uniformity of the impeller exit flow. In other words, if the non-uniformity of the impeller exit flow is strong, if the flow on the hub surface side where the main flow exists is controlled intensively, the high-energy part in the flow is controlled, so the entire flow is effectively Can be controlled.
  • FIG. 9A is a dihedral distribution diagram
  • FIG. 9B is a sweep distribution diagram that is dimensionless by the chord length.
  • 10 is a perspective view of the diffuser 309 having the distribution shown in FIG. 9, where FIG. 10A is an overall view of the diffuser, FIG. 10B is a detailed view of the G portion of FIG. 9A, and FIG. c) is a detailed view of a portion H in FIG.
  • the hub plate 1010 is attached to the hub side of the impeller.
  • the hub-side dihedral distribution is important, and increasing in the blade height direction is effective from the viewpoint of flow control, but the dihedral distribution in the blade height direction is reduced. Even in this case, it has been found that the effect may be obtained by combining with the sweep. A specific example will be described below.
  • the die heddle is reduced in the blade height direction in the vicinity of the hub side end surface (see the circled box 901), and the sweep is performed in the vicinity of the same hub side end surface (see the circled box 902). It is decreased by. That is, the diffuser 1000 is a lean combined with a dihedral and a sweep, and uses a three-dimensional curve element. Since the sensitivity to performance was small in a region other than the vicinity of the hub side end face, any of the dihedral and the sweep can be arbitrarily determined within a range where no extreme change occurs.
  • the direction of the dihedral at the hub side end face is opposite to that of each of the above-described embodiments.
  • the angle formed by the surface of the hub plate 1010 and the diffuser negative pressure surface 1001 becomes an acute angle, and a blade force opposite to the blade force 601 shown in FIG. 6 is generated.
  • the reverse wing force seems to increase the secondary flow at first glance, but actually acts to suppress the secondary flow. The reason is as follows.
  • the diffuser blade 1020 is configured by combining a die heddle and a sweep. Since the diffuser blade 1020 has the sweep 1002, a notch-shaped gap 1003 is formed between the front edge 1005 of the diffuser blade 1020 and the surface of the hub plate 1010. In this notch-shaped gap 1003, a flow that wraps around from the pressure surface of the diffuser blade 1020 to the suction surface is generated, and a vertical vortex 1004 is generated. At the corner portion formed by the suction surface of the diffuser blade 1020 and the surface of the hub plate 1010, a vorticity 1006 that suppresses the secondary flow is generated.
  • the blade surface separation at the diffuser blade 1020 is suppressed by the promotion of stirring with the surrounding fluid and the negative pressure effect at the center of the vortex.
  • the secondary flow is suppressed by the action of the vertical vortex, the flow field is made uniform, and the performance of the curved element three-dimensional diffuser is improved.
  • FIG. 11 shows how the performance of the compressor is improved when the curved element three-dimensional diffuser shown in the present embodiment is used for the compressor using the linear element two-dimensional diffuser.
  • the horizontal axis of the graph is the flow rate Q made dimensionless by the design point flow rate Qdes, and the vertical axis is the adiabatic efficiency ⁇ of the compressor stage made dimensionless by 2DIM and the pressure coefficient ⁇ of the two-dimensional diffuser. This is the pressure coefficient ⁇ made dimensionless by 2DIM .
  • the diffuser blade has at least one of a sweep distribution and a dihedral distribution, thereby realizing a curved element three-dimensional diffuser.
  • the secondary flow near the hub wall surface and shroud wall surface of the diffuser and the collision flow near the front edge of the diffuser blade are controlled by the method of tilting these diffuser blades.
  • the performance of the diffuser can be improved.
  • the sweep distribution and the dihedral distribution shown in each of the above-described examples are merely exemplary, and both distributions regarding a part that is not limited in shape because the sensitivity to performance is small are also illustrated. Not too much.
  • the characteristics of the shape shown in each embodiment be in the entire blade.
  • the shape of the first half (upstream side) of the diffuser blade has a relatively large influence on the performance, the flow of the diffuser is particularly important. Even if it has the shape described above only in the first half of the direction, the effect of the present invention can be obtained. Therefore, it is possible to use a linear element two-dimensional diffuser or the like frequently used in the latter half of the flow direction.
  • the diffuser blades are provided on the hub plate.
  • the diffuser blades may be provided on the plate facing the hub plate, that is, on the shroud surface side. In any case, it is attached to either the hub side or the shroud side for ease of assembly.

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  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
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Abstract

L'invention concerne une machine centrifuge (300) à fluide dans laquelle un ou plusieurs impulseurs sont fixés à un même arbre de rotation. Un diffuseur à aubes est installé en aval d'au moins un des impulseurs. Une pluralité de diffuseurs à aubes est disposée sur une plaque concentrique (309a) par intervalles dans une direction circonférentielle de celle-ci, et chacun des diffuseurs est un diffuseur tridimensionnel à élément curviligne doté d'ailettes (309c) qui se prolongent d'un côté moyeu de l'impulseur à un côté carénage de celui-ci. Les ailettes sont formées de telle façon qu'une ailette servant de référence est empilée dans le sens de la hauteur de l'ailette, qui est la direction d'un écartement entre le moyeu et le carénage. Une distribution du dièdre dans laquelle une direction perpendiculaire à la direction d'une corde reliant un bord d'attaque de l'ailette servant de référence à un bord de fuite de celle-ci, c'est-à-dire dans le sens opposé au sens de rotation de l'impulseur, est prise comme mouvement positif, est non uniforme d'une partie d'extrémité côté moyeu à une partie intermédiaire de la hauteur de l'ailette.
PCT/JP2011/077863 2010-12-10 2011-12-01 Turbomachine centrifuge WO2012077580A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
CN201180058898.2A CN103314218B (zh) 2010-12-10 2011-12-01 离心型涡轮机械
EP11847208.3A EP2650546A1 (fr) 2010-12-10 2011-12-01 Turbomachine centrifuge
US13/992,457 US20130309082A1 (en) 2010-12-10 2011-12-01 Centrifugal turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2010275839A JP5608062B2 (ja) 2010-12-10 2010-12-10 遠心型ターボ機械
JP2010-275839 2010-12-10

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WO2012077580A1 true WO2012077580A1 (fr) 2012-06-14

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EP (1) EP2650546A1 (fr)
JP (1) JP5608062B2 (fr)
CN (1) CN103314218B (fr)
WO (1) WO2012077580A1 (fr)

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CN103314218A (zh) 2013-09-18
JP2012122443A (ja) 2012-06-28
EP2650546A1 (fr) 2013-10-16
CN103314218B (zh) 2016-03-09
US20130309082A1 (en) 2013-11-21

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