WO2011067965A1 - 遠心圧縮機の羽根車 - Google Patents
遠心圧縮機の羽根車 Download PDFInfo
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- WO2011067965A1 WO2011067965A1 PCT/JP2010/063583 JP2010063583W WO2011067965A1 WO 2011067965 A1 WO2011067965 A1 WO 2011067965A1 JP 2010063583 W JP2010063583 W JP 2010063583W WO 2011067965 A1 WO2011067965 A1 WO 2011067965A1
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- 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
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- 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
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- 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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
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- 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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
Definitions
- the present invention relates to an impeller of a centrifugal compressor used for a vehicle, a marine turbocharger, and the like, and in particular, a blade shape of a splitter blade (short blade) provided between adjacent full blades (all blades).
- the present invention relates to the shape of the wing at the fluid inlet.
- Centrifugal compressors used in compressors for vehicular and marine turbochargers give kinetic energy to the fluid through rotation of the impeller and discharge the fluid radially outward to obtain a pressure increase due to centrifugal force Is. Since this centrifugal compressor is required to have a high pressure ratio and high efficiency in a wide operating range, a splitter blade (short blade) 03 is provided between adjacent full blades (all blades) 01 as shown in FIG. An impeller (impeller) 05 is often used, and various contrivances have been made for its blade shape.
- the full blade 01 and the splitter blade 03 are alternately installed on the surface of the hub 07 as shown in FIGS.
- the general splitter blade 03 has a shape obtained by simply cutting away the upstream side of the full blade 01.
- the inlet end of the splitter blade 03 is located downstream from the inlet edge (LE1) of the full blade 01 by a certain distance.
- the edge (LE2) is located, and the outlet edge (TE) is provided to coincide with the blade angle ⁇ of the inlet edge of the splitter blade 03 (the angle formed between the direction of the inlet edge and the axial direction G of the impeller 05) (Shown) is set to be the same as the flow direction F of the fluid flowing through the flow path between the full blades 01.
- the splitter blade 03 when the splitter blade 03 is designed so that the inlet end edge of the splitter blade 03 is simply cut away from the upstream side of the full blade 01 at the circumferential center position between the full blades 01, the splitter blade 03. Since the difference of A1 ⁇ A2 occurs between the throat area A1 of the pressure surface Sa of the full blade 01 and the throat area A2 of the negative pressure surface Sb formed on both sides of the full blade 01, the flow rate of each flow path is uneven. There is a problem that the fluid cannot be evenly distributed, the blade load becomes uneven, the flow path loss increases, and the impeller efficiency is prevented from being improved.
- the throat area refers to a cross-sectional area at a position that forms the shortest distance from the inlet edge of the splitter blade as shown in FIG. 11 to the pressure surface or the suction surface of the full blade 01.
- Patent Document 1 Japanese Patent Application Laid-Open No. 10-213094
- Patent Document 2 Japanese Patent No. 3876195
- Patent Document 2 Japanese Patent No. 3876195
- the flow velocity is different on both sides of the splitter blade 09, that is, on the pressure surface side and the suction surface side of the full blade 01
- the fluid that has entered between the full blades 01 gathers mainly on the suction surface side. Therefore, even if the cross-sectional area of the passages on both sides of the splitter blade 09 is geometrically equal, the flow rate increases on the negative pressure surface side compared to the pressure surface side, and the flow rate increases. There is a problem that uniformity occurs, the fluid cannot be evenly distributed, the blade load becomes uneven, the flow path loss increases, and the improvement of the impeller efficiency is hindered.
- Patent Document 3 Japanese Patent Laid-Open No. 2002-332992
- Patent Document 3 Japanese Patent Laid-Open No. 2002-332992
- the blade edge ⁇ of the inlet end edge of the splitter blade 011 is left as it is, and the leading edge is deliberately biased toward the suction surface side of the full blade 01 so that A1> A2.
- the flow rate in both side passages of the splitter blade 011 is made uniform.
- Patent Documents 1 to 3 pay attention to the flow distribution of the flow path divided by the splitter blade based on the assumption that the flow between the blades (blades) flows along the full blade.
- the shape has been improved.
- the flow field has a complex aspect, and the conventional blade shape that does not adapt to these complex internal flows results in sufficient impeller performance. It was not done.
- the present invention has been made in view of these problems, and a full blade provided adjacent to each other from the inlet portion to the outlet portion of the fluid, and a splitter provided from the middle of the flow path to the outlet portion between the full blades.
- a centrifugal compressor impeller equipped with a blade the centrifugal blade achieves a high pressure ratio and high efficiency by avoiding interference of the inlet edge of the splitter blade with a leakage vortex from the tip of the inlet edge of the full blade. It is an object to provide an impeller for a compressor.
- the present invention provides a plurality of full blades provided on the hub surface from the inlet portion to the outlet portion of the fluid and a halfway of a flow path formed between the full blades provided adjacent to each other.
- an impeller of a centrifugal compressor provided with a splitter blade provided from an outlet portion to an outlet portion, it rotates adjacent to the rear full blade from an inlet end edge of a rear full blade located on the rear side in the rotation direction of the compressor.
- the flow direction downstream of the fluid flowing between the full blades from the leakage vortex line formed by connecting the center position of the throat forming the minimum distance to the front full blade provided on the front side and the inlet edge of the front full blade The inlet edge of the splitter blade is positioned on the side.
- the position of the inlet end of the splitter blade is provided on the front side in the rotational direction adjacent to the rear full blade from the inlet end edge of the rear full blade located on the rear side in the rotational direction of the compressor.
- Flow of fluid flowing between the full blades rather than the leakage vortex line formed by connecting the center position of the so-called throat forming the minimum distance to the front full blade and the inlet edge of the front full blade By providing it on the downstream side in the direction, leakage vortices generated from the tip end portion (casing side) of the inlet edge of the full blade are avoided from interfering with the inlet edge of the splitter blade.
- the leakage vortex generated from the inlet blade tip of the full blade is, according to the numerical analysis result, the center position of the throat formed between the rear full blade located on the rear side in the rotation direction of the compressor and the front side It has been confirmed that a leakage vortex flows along a line formed by connecting the inlet end edge of the full blade, and the position of the inlet end edge of the splitter blade is set based on the knowledge.
- the tip end portion in the blade height direction of the inlet end edge of the splitter blade is inclined toward the front full blade side. According to such a configuration, the leakage vortex generated from the tip end portion (casing side) of the inlet end edge of the full blade mainly interferes with the tip end portion at the inlet end edge of the splitter blade. By inclining to, the interference of leakage vortices can be avoided more reliably.
- the inlet edge of the splitter blade is positioned so as to be greatly lowered downstream in the flow direction of the fluid flowing between the full blades, the length of the splitter blade will be shortened, and the splitter blade's original high pressure ratio and high efficiency function Therefore, it is possible to effectively avoid the leakage vortex while ensuring the length of the splitter blade.
- the inclination angle toward the front full blade side is further inclined by 5 ° to 8 ° with respect to the inclination angle along the rear full blade. Based on the numerical analysis results, if the angle is less than 5 °, the effect of avoiding the leakage vortex flow due to the inclination cannot be expected, and if the inclination exceeds 8 °, the inclined portion is between the splitter blade and the front full blade. In this case, it is desirable to incline by 5 ° to 8 °.
- the inlet end edge of the splitter blade may be positioned to be deviated toward the front full blade side from a circumferential intermediate position between the front full blade and the rear full blade.
- a blade of a centrifugal compressor provided with a full blade provided adjacent to each other from the inlet portion to the outlet portion of the fluid, and a splitter blade provided between the full blade and the middle portion of the flow path to the outlet portion.
- FIG. 6 is an explanatory diagram showing a standing state of a wing in the X direction view in FIGS.
- FIG. 1 is a perspective view showing a main part of an impeller (impeller) of a centrifugal compressor to which a splitter blade of the present invention is applied.
- the impeller 1 includes a plurality of adjacent full blades (all blades) 5 on a top surface of a hub 3 fitted to a rotor shaft (not shown), and splitter blades (short blades) 7 provided between the full blades 5. , Are alternately erected at an equal pitch in the circumferential direction.
- the splitter blade 7 is shorter than the full blade 5 in the fluid flow direction, and is provided from the middle of the flow path 9 formed between the full blades 5 and 5 to the outlet portion.
- FIG. 2 shows the relationship between the splitter blade 7 and the full blade 5 in a sectional shape along the longitudinal direction of the blade (corresponding to a sectional view taken along line AA in FIG. 10).
- the shape here indicates the shape at the casing side position, that is, at the blade tip position.
- the impeller 1 shall rotate in the arrow direction.
- the inlet edge 7a which is the leading edge of the splitter blade 7 is located downstream of the inlet edge 5a which is the leading edge of the full blade 5 in the flow direction, and the outlet edge 7b of the trailing edge of the splitter blade 7;
- the position of the trailing edge of the full blade 5 coincides with the outlet edge 5b.
- the flow path 9 formed between the pressure surface side Sa of the full blade 5 and the negative pressure surface side Sb of the full blade 5 is positioned so as to be equally divided in the circumferential direction by the splitter blade 7,
- a flow path 11 is formed between the wall surface of the full blade 5 on the pressure surface side Sa and a flow path 13 is formed between the wall surface of the negative pressure surface side Sb.
- the shape of the splitter blade 7 extends along the full blade 5, and the inclination angle ⁇ of the inlet end edge 7 a is the same as that of the full blade 5.
- the impeller 1 configured as described above is configured as an open impeller having a blade tip clearance between a full blade 5 and a casing (not shown) that covers the splitter blade 7. Therefore, the blade end leakage flow W in which the fluid on the pressure surface side of the full blade 5 in the adjacent fluid passage leaks to the suction surface side of the full blade 5 through the gap portion between the inlet end portion of the full blade 5 and the casing. Occurs.
- Blade tip leakage flows through a gap B between the leading edge 5a of the full blade 5 and the casing.
- the blade tip leakage flow W is accompanied by a strong vortex flow (blade tip leakage vortex) as shown in FIG. 5 and has a strong blocking action against the flow along the full blade 5.
- the flow does not flow along the full blade 5, but generates a drift M toward the inlet edge of the splitter blade 7 using the vortex as a nucleus.
- the inlet full edge 5a of the rear full blade 5R is adjacent to the rear full blade 5R.
- a line formed by connecting the center position P of the so-called throat SR that forms the minimum distance to the suction surface side Sb of the front full blade 5F provided on the front side in the rotation direction and the inlet edge 5a of the front full blade 5F. can do.
- the leakage vortex is a portion where the low energy fluid accumulates. Therefore, when this interferes with the inlet edge 7a of the splitter blade 7, loss generation due to separation or generation of a vortex structure increases. Therefore, it is necessary to install the inlet edge 7a of the splitter blade 7 so as to avoid the leakage vortex line WL.
- the range of ⁇ 4 ° to 5 °, for example, around the leakage vortex line WL is set as the region of the leakage vortex range, and the inlet edge 7a of the splitter blade 7 is avoided so as to avoid this region. Is shifted to the downstream side in the flow direction of the fluid flowing between the front full blade 5F and the rear full blade 5R to avoid interference of the inlet edge 7a of the splitter blade 7 with respect to the leakage vortex.
- the impeller of a centrifugal compressor that achieves high pressure ratio and high efficiency can be obtained.
- the range of ⁇ for setting the leakage vortex range is the width obtained from the result of specifying the vortex existence range using the physical quantity called vorticity from the numerical analysis result, and is the minimum that does not affect the leakage vortex Set as a range.
- the inlet end edge 7a of the splitter blade 7 is formed upright in the vertical direction on the surface of the hub 3, as shown in FIG. 6A. .
- the position of the inlet end edge 7a of the splitter blade 7 is provided on the downstream side in the fluid flow direction from the leakage vortex line WL, so that the leakage vortex of the splitter blade 7 is reduced. It is possible to avoid the problem that the loss generation of the flow increases due to the separation generated by interference with the inlet edge 7a and the generation of a further vortex structure, leading to a decrease in efficiency, and the efficiency decrease of the impeller 1 is prevented, and the high pressure ratio and High efficiency can be achieved.
- the inlet edge 7a of the splitter blade 7 is installed so as not to be located within the leakage vortex range ⁇ described in the first embodiment, and the height direction of the inlet edge 7a of the splitter blade 7 is further increased.
- the front end portion, that is, the casing side portion of the inlet end edge 7a of the splitter blade 7 is formed to be inclined toward the front full blade 5F.
- the inclination angle is such that the shape of the splitter blade 7 follows the shape of the full blade, and the inclination angle ⁇ of the inlet edge 7a is the same as the inclination ⁇ of the rear full blade 5R. (Refer to FIG. 2)
- the inlet edge 7a of the splitter blade 7 is positioned so as to be greatly lowered downstream in the flow direction of the fluid flowing between the front full blade 5F and the rear full blade 5R, the length of the splitter blade 7 is shortened. 7 Since the original high pressure ratio and high efficiency functions cannot be exhibited, it is possible to effectively avoid the leakage vortex while ensuring the length of the splitter blade 7, and even if the impeller 1 is downsized, it is appropriate. Can achieve the effect of avoiding various leakage vortices. 3 in the second embodiment, the inlet edge 7a of the splitter blade 7 is inclined to the front full blade 5F side on the surface of the hub 3 as shown in FIG. 6B. It is formed.
- the inlet edge 7a of the splitter blade 7 is positioned so as not to be located within the leakage vortex range ⁇ described in the first embodiment.
- the blade 5F and the rear full blade 5R are positioned so as to be biased toward the front full blade 5F side from the intermediate position in the circumferential direction.
- the splitter blade 7 is erected vertically on the surface of the hub 3 as shown in FIG. 6C, and the inlet edge 7a of the splitter blade 7 is erected vertically. , The position is shifted by ⁇ L toward the front full blade 5F side from the circumferential intermediate position.
- the flow velocity is different on both sides of the splitter blade 7, that is, the suction surface side Sb of the front full blade 5F and the pressure surface side Sa of the rear full blade 5R, and the fluid is a distribution in which fast flows mainly gather on the suction surface side Sb. It becomes. For this reason, even if the flow path cross-sectional areas of the both side passages of the splitter blade 7 are geometrically equal, the flow rate increases because the suction surface side Sb has a higher flow velocity than the pressure surface side Sa.
- the original high pressure of the splitter blade 7 can be achieved without significantly lowering the inlet edge 7a of the splitter blade 7 on the downstream side in the flow direction of the fluid flowing between the front full blade 5F and the rear full blade 5R. Ratio and high efficiency can be achieved, the length is secured, the flow distribution of the flow paths 11 and 13 in the full blade divided by the splitter blade 7 can be made uniform, Avoidance can be effectively obtained.
- a single splitter blade is provided in the flow path between the full blades.
- the present invention is applied to a double splitter blade that is provided in the flow path between the single splitter blades and is shorter than the single splitter blade.
- the minimum distance from the inlet edge of the rear full blade located on the rear side in the rotation direction of the compressor to the front full blade provided on the front side in the rotation direction adjacent to the rear full blade is formed. Since the inlet edge of the splitter blade is positioned downstream of the leakage vortex line formed by connecting the center position of the throat and the inlet edge of the front full blade in the flow direction of the fluid flowing between the full blades, The interference of the inlet edge of the splitter blade to the leakage vortex from the tip of the inlet edge of the blade can be avoided, and a high pressure ratio and high efficiency can be achieved, so that the centrifugal compressor equipped with the splitter blade can be impeller. Suitable for use.
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Abstract
Description
この一般的なスプリッタブレード03の場合は、図11(図10のA-A線断面図)のように、フルブレード01の入口端縁(LE1)より一定距離下流側にスプリッタブレード03の入口端縁(LE2)が位置され、出口端縁(TE)は一致して設けられ、スプリッタブレード03の入口端縁の翼角θ(入口端縁の方向とインペラ05の軸方向Gとの成す角度として示す)は、フルブレード01間の流路を流れる流体の流れ方向Fと同一に設定されている。
また、スプリッタブレードの入口端部を、フルブレードの負圧面側に傾けたものとして特許文献2(特許3876195号公報)についても知られている。
しかし、特に、翼端隙間を有するオープン型インペラの場合には、流れ場は複雑な様相を呈しており、これら複雑な内部流動に適合しない従来の翼形状では、結果として十分なインペラ性能が得られていなかった。
すなわち、従来型インペラ構造ではこのフルブレードの入口端縁の先端からの漏れ渦とスプリッタブレードの入口端縁との干渉に対する対策がなされていないため、十分な性能が得られていなかった。
かかる構成によると、フルブレードの入口端縁の先端部(ケーシング側)から発生する漏れ渦は、主にスプリッタブレードの入口端縁における先端部に干渉するため、この先端部をさらに前側フルブレード側に傾斜させることで、漏れ渦の干渉をさらに確実に回避できようになる。
すなわち、スプリッタブレードの入口端縁を、フルブレード間を流れる流体の流れ方向下流側に大きく下げて位置させるとスプリッタブレードの長さが短くなり、スプリッタブレード本来の高圧力比および高効率化の機能を発揮できなくなるため、スプリッタブレードの長さは確保しつつ前記漏れ渦に対する回避を効果的に得ることができる。
数値解析結果に基づいて、5°未満であると、傾斜させることによる漏れ渦流れに対する回避効果が期待できず、また8°を超えて傾斜させるとその傾斜部分がスプリッタブレードと前側フルブレードの間を流れる流体の流れに対して流路抵抗を生じ問題があるため、5°~8°傾斜していることが望ましい。
このように構成することによって、漏れ渦流れに対する回避ができる上にさらに、スプリッタブレードによって分割されるフルブレード間内の各通路の流量配分の均一化が図れる。
すなわち、スプリッタブレードの両側、つまりフルブレードの圧力面側と負圧面側とで流速が異なることから、フルブレードの間に入ってきた流体は、主に負圧面側に速い流れが集まる分布となるため、スプリッタブレードの両側通路の流路断面積を幾何学的に等しくしても、負圧面側が圧力面側に比べて流速が速い分、流量が増え各流路の流量に不均一が生じ、流体を均等分配することができず、翼負荷が不均等となり流路損失も増えて、羽根車の効率向上が妨げられる問題があるが、このような問題に対して、前側フルブレード側に寄せて、つまり負圧面側に寄せて流路断面積を狭めることによって、スプリッタブレードによって分割されるフルブレード間内の各通路の流量配分の均一化が図れる。
図1は本発明のスプリッタブレードが適用される遠心圧縮機のインペラ(羽根車)の要部を示す斜視図である。インペラ1は、図示しないローター軸に嵌着されたハブ3の上面に複数の互いに隣り合うフルブレード(全翼)5と、そのフルブレード5の間に設けられるスプリッタブレード(短翼)7とが、周方向に等ピッチで交互に立設されている。そして、スプリッタブレード7は、フルブレード5よりも流体の流れ方向に対して長さが短く、フルブレード5、5の間に形成される流路9の途中から出口部にかけて設けられている。
また、フルブレード5の圧力面側Saとフルブレード5の負圧面側Sbとの間に形成される流路9をスプリッタブレード7によって周方向に二等分割するように位置され、スプリッタブレード7とフルブレード5の圧力面側Saの壁面との間に流路11が形成され、負圧面側Sbの壁面との間に流路13が形成されている。
また、スプリッタブレード7の形状はフルブレード5に沿うようになっていて、入口端縁7aの傾斜角度θはフルブレード5と同一になっている。
フルブレード5のリーディングエッジ5a部の先端部のケーシングとの隙間部Bを通って翼端漏れ流れが生じる。この翼端漏れ流れWは、図5のように、強い渦流(翼端漏れ渦)を伴っており、フルブレード5に沿う流れに対して強いブロック作用を有するため、スプリッタブレード7の入口端縁7aの近傍では、流れはフルブレード5に沿った流れとはならず、前記渦を核としてスプリッタブレード7の入口端縁に向かう偏流Mを生じる。
なお、漏れ渦範囲を設定するためのαの範囲については、数値解析結果から渦度という物理量を用いて渦の存在範囲を特定した結果から求めた幅であり、漏れ渦の影響が及ばない最小範囲として設定する。
次に、図3を参照して第2実施形態について説明する。
第2実施形態は、スプリッタブレード7の入口端縁7aが第1実施形態で説明した漏れ渦範囲α内に位置しないように設置した上にさらに、スプリッタブレード7の入口端縁7aの高さ方向の先端部が、つまりスプリッタブレード7の入口端縁7aのケーシング側の部分を、前記前側フルブレード5F側に傾斜して形成されている。
なお、この第2実施形態における図3のX矢視は、図6(b)に示すようにハブ3面上に、スプリッタブレード7の入口端縁7aが前側フルブレード5F側に傾斜して立設して形成されている。
次に、図4を参照して第3実施形態について説明する。
第3実施形態は、スプリッタブレード7の入口端縁7aが第1実施形態で説明した漏れ渦範囲α内に位置しないように位置させた上にさらに、スプリッタブレード7の入口端縁7aを前側フルブレード5Fと後側フルブレード5Rとの周方向中間位置より前記前側フルブレード5F側に偏って位置されるものである。
すなわち、スプリッタブレード7の両側、つまり前側フルブレード5Fの負圧面側Sbと、後側フルブレード5Rの圧力面側Saとでは流速が異なり流体は、主に負圧面側Sbに速い流れが集まる分布となる。このため、スプリッタブレード7の両側通路の流路断面積を幾何学的に等しくしても、負圧面側Sbが圧力面側Saに比べて流速が速い分、流量が増え各流路の流量に不均一が生じ、流体を均等分配することができず、翼負荷が不均等となり流路損失も増えて、インペラ効率の向上が妨げられる問題があるが、このような問題に対して、前側フルブレード5F側に寄せて、つまり負圧面側Sbに寄せて流路断面積を狭めることによって、スプリッタブレード7によって分割されるフルブレード間内の各流路11、13の流量配分の均一化が図れる。
以上のように、本第3実施形態によれば、前側フルブレード5Fの翼端からの漏れ流れによる渦の影響を受けず、さらに、スプリッタブレード7によって分割されるフルブレード間内の各流路11、13の流量配分の均一化が図れる。
次に、図5を参照して第4実施形態について説明する。
第4実施形態は、第3実施形態のスプリッタブレード7の入口端縁7aについて、さらに第2実施形態のように入口端縁7aの高さ方向の先端部が、つまり入口端縁7aのケーシング側の部分が、前側フルブレード5F側に傾斜して形成されている。
Claims (4)
- ハブ面上に流体の入口部から出口部にかけて複数設けられるフルブレードと、互いに隣り合わせて設けられる前記フルブレードの間に形成される流路の途中から出口部にかけて設けられるスプリッタブレードとを備えた遠心圧縮機の羽根車において、
前記圧縮機の回転方向後側に位置する後側フルブレードの入口端縁から該後側フルブレードに隣接して回転方向前側に設けられる前側フルブレードへの最小間隔を形成するスロートの中心位置と前記前側フルブレードの入口端縁とを結んで形成される漏れ渦ラインよりもフルブレード間を流れる流体の流れ方向下流側に前記スプリッタブレードの入口端縁を位置させてなることを特徴とする遠心圧縮機の羽根車。 - 前記スプリッタブレードの入口端縁の翼高さ方向の先端部を前記前側フルブレード側に傾斜していることを特徴とする請求項1記載の遠心圧縮機の羽根車。
- 前記前側フルブレード側への傾斜角度は、前記後側フルブレードに沿った傾斜角度に対して、さらに5°~8°傾斜していることを特徴とする請求項2記載の遠心圧縮機の羽根車。
- 前記スプリッタブレードの入口端縁を前記前側フルブレードと前記後側フルブレードとの周方向中間位置より前記前側フルブレード側に偏って位置されることを特徴とする請求項1または2に記載の遠心圧縮機の羽根車。
Priority Applications (4)
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EP10834418.5A EP2428684B1 (en) | 2009-12-02 | 2010-08-10 | Impeller for centrifugal compressor |
US13/381,064 US9140271B2 (en) | 2009-12-02 | 2010-08-10 | Impeller of centrifugal compressor |
CN201080029404.3A CN102472292B (zh) | 2009-12-02 | 2010-08-10 | 离心压缩机的叶轮 |
KR1020117031358A KR101276957B1 (ko) | 2009-12-02 | 2010-08-10 | 원심 압축기의 임펠러 |
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JP2009274645A JP5308319B2 (ja) | 2009-12-02 | 2009-12-02 | 遠心圧縮機の羽根車 |
JP2009-274645 | 2009-12-02 |
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EP (1) | EP2428684B1 (ja) |
JP (1) | JP5308319B2 (ja) |
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US9140271B2 (en) | 2015-09-22 |
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JP5308319B2 (ja) | 2013-10-09 |
EP2428684B1 (en) | 2019-05-08 |
KR101276957B1 (ko) | 2013-06-19 |
CN102472292A (zh) | 2012-05-23 |
CN102472292B (zh) | 2015-04-08 |
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