JPH03134298A - Diffuser with vanes of centrifugal compressor - Google Patents
Diffuser with vanes of centrifugal compressorInfo
- Publication number
- JPH03134298A JPH03134298A JP1271654A JP27165489A JPH03134298A JP H03134298 A JPH03134298 A JP H03134298A JP 1271654 A JP1271654 A JP 1271654A JP 27165489 A JP27165489 A JP 27165489A JP H03134298 A JPH03134298 A JP H03134298A
- Authority
- JP
- Japan
- Prior art keywords
- diffuser
- blade
- impeller
- leading edge
- plate side
- Prior art date
- Legal status (The legal status 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 status listed.)
- Pending
Links
- 230000007423 decrease Effects 0.000 claims description 3
- 239000012530 fluid Substances 0.000 claims description 2
- 238000013459 approach Methods 0.000 abstract description 6
- 238000010586 diagram Methods 0.000 description 15
- 238000000034 method Methods 0.000 description 4
- 238000000926 separation method Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000011084 recovery Methods 0.000 description 3
- 230000006866 deterioration Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000002542 deteriorative effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
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
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は広い作動範囲を有する遠心圧縮機の羽根付ディ
フューザに関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a vaned diffuser for a centrifugal compressor having a wide operating range.
ディフューザ羽根を可動とすることなく羽根付ディフュ
ーザの作動範囲と拡大する方法について特公昭６４−５
６１号公報には、ディフューザ羽根のそり線の接線の方
向が半径が大になるにつれて半径方向に近づくように反
りを持たせた翼形とする方法、実公昭６３−４５５９９
号公報に記載のようにディフューザ羽根を挾み込む壁面
を傾斜させる方法が論じられている。Regarding the operating range and method of expanding the operating range of a diffuser with vanes without making the diffuser vanes movable, 1986-5
Japanese Utility Model Publication No. 63-45599 discloses a method of forming an airfoil so that the direction of the tangent to the warp line of the diffuser blade approaches the radial direction as the radius increases.
As described in the above publication, a method is discussed in which the wall surface between which the diffuser blades are sandwiched is inclined.
上記従来技術のうち第１のものは、負圧面が羽根車のあ
る側に凸になっているため、ディフューザ羽根入口の半
径位置のマツハ数が低い亜音速の場合（たとえば０．６
以下）では大きな効果が得られるが、マツハ数が、大き
い高亜音速域では負正面で音速を越える領域が生じ、高
速の流れが壁面に接触していることによる摩擦損失の増
加、衝撃波の発生による境界層の発達などにより性能が
低下する問題があった。第２のものは上記第１の持つ点
は解決されているがディフューザ羽根を挾み込む壁面を
傾斜させる必要があるため製作時の工数が増加する問題
があった。In the first of the above conventional technologies, since the suction surface is convex toward the side where the impeller is located, when the Matsuha number at the radial position of the diffuser blade inlet is low (for example, 0.6
(below), a large effect can be obtained, but in the high subsonic region where the Matsuha number is large, there will be a region where the speed of sound is exceeded in the negative front, increasing friction loss and generating shock waves due to the high-speed flow coming into contact with the wall surface. There was a problem that performance deteriorated due to the development of a boundary layer due to The second method solves the above-mentioned first problem, but there is a problem in that the number of man-hours during manufacturing increases because it is necessary to slope the wall surface that sandwiches the diffuser blades.
本発明の目的は、高亜音速域で良好な性能を有しかつ製
造が容易な遠心圧縮機の羽根付ディフューザを提供する
ことにある。An object of the present invention is to provide a vaned diffuser for a centrifugal compressor that has good performance in a high subsonic speed range and is easy to manufacture.
上記目的を達成するためディフューザ羽根のそり線の形
状を、羽根先端ではほぼ設計条件時の流れの方向とし、
羽根先端と喉部の間では、羽根車の回転軸を中心とする
円の接線とそり線の成す角が一旦減少するように構成す
るとともに前縁付近の羽根表面のうち羽根車に対面する
側は羽根車の側に凸となり、羽根車に対面しない側は羽
根車に対面しない側に凸となる形状としたものである。In order to achieve the above purpose, the shape of the warp line of the diffuser blade is set in the direction of the flow at the blade tip approximately under the design conditions.
Between the tip of the blade and the throat, the angle formed by the tangent to the circle centered on the rotation axis of the impeller and the warp line is once reduced, and the side of the blade surface near the leading edge facing the impeller is is convex toward the impeller, and the side not facing the impeller is convex toward the side not facing the impeller.
ディフューザ羽根前縁のそり線が、はぼ設計条件時の流
れの方向でありかつ、ディフューザ羽根の表面の羽根車
に対面しない側（圧力面）が、同じ側に凸となっている
ので一１流れが羽根車に対面しない表面から剥離する傾
向が強い設計条件より大流量の条件でも流れは羽根表面
に密着して流れるので、圧力回復性能の低下が少ない。The warpage line of the leading edge of the diffuser blade is in the direction of flow under the flow design conditions, and the side of the surface of the diffuser blade that does not face the impeller (pressure surface) is convex on the same side. Even under high flow conditions, the flow flows in close contact with the impeller surface, so there is less deterioration in pressure recovery performance, compared to the design condition where the flow tends to separate from the surface that does not face the impeller.
羽根先端と喉部の間では羽根車の回転軸を中心とする円
の接線とそり線の成す角が一旦減少し、かつ羽根車に対
面する羽根表面（負圧面）が羽根車の側に凸になってい
るのでディフューザ羽根前縁付近の羽根表面は、羽根車
の回転′軸を中心とする円の接線に近い方向に延在する
。このため流れが羽根車に対面する側の面からはく離す
る傾向が強い設計条件より小流量の状態でも流れが羽根
表面に密着して流れるので失速が生じにくく振動の防止
あるいは、サージングに入りにくくすることが可能であ
る。また１羽根車の回転軸を中心とす円の接線とそり線
の成す角が羽根先端と喉部の間で一旦減少した後は更に
増加させることができるので、十分な喉部面積が確保で
きるので、この点でも、設計条件および設計条件より大
流量の条件における圧力回復性能の低下を防ぐことがで
きる。Between the tip of the blade and the throat, the angle formed by the tangent line of the circle centered on the rotation axis of the impeller and the warp line temporarily decreases, and the blade surface facing the impeller (negative pressure surface) is convex toward the impeller side. Therefore, the blade surface near the leading edge of the diffuser blade extends in a direction close to the tangent of a circle centered on the rotational axis of the impeller. For this reason, compared to the design condition where the flow tends to separate from the side facing the impeller, the flow flows closely to the blade surface even at a small flow rate, making it difficult to stall and prevent vibration or surging. Is possible. In addition, the angle formed by the tangent line of the circle centered on the rotation axis of one impeller and the warp line can be increased further after being reduced between the blade tip and the throat, so a sufficient throat area can be secured. Therefore, in this respect as well, it is possible to prevent the pressure recovery performance from deteriorating under design conditions and conditions where the flow rate is larger than the design conditions.
以下１本発明の−・実施例を第１図〜第５図に示す。 Embodiments of the present invention are shown in FIGS. 1 to 5 below.
第１図は羽根車の回転軸の方向から羽根車とディフュー
ザ羽根を見た図、第２図は羽根車の回転軸を含む断面図
、第３図はディフューザ羽根の先端部分を拡大して示し
た図、第４図、第９図は本実施例の作用を示す図である
。Figure 1 is a view of the impeller and diffuser blade viewed from the direction of the impeller's rotation axis, Figure 2 is a sectional view including the impeller's rotation axis, and Figure 3 is an enlarged view of the tip of the diffuser blade. FIGS. 4 and 9 are diagrams showing the operation of this embodiment.
羽根車１により運動エネルギを与えられた流れ３ａ、３
ｂはディフューザ羽根２を通過する際に運動エネルギの
一部を圧力に変換される。設計条件より大流量の状態で
は流れ３ａのようにディフューザ羽根２のそり線４の延
長より半径方向に近い方向からディフューザ羽根２に近
づき設計条件より小流量の状態では、流れ３ｂのように
そり線４の延長より半径方向から遠い方向からディフュ
ーザ羽根２に近づく。ディフューザ羽根２の先端は第３
図に示すように、そり線４と羽根車１の回転軸を中心と
する円の接線の成す角は前縁と、負圧面２ａの側に隣接
する羽根の前ＡｉＮＡと負圧面２ａの間の最短距離であ
る喉部の幅ＡＢの延長の間でαｌ〉α２．αＳ〉α２と
なるように構成され、更に負圧面２ａは前縁Ａ付近では
羽根車１の側に凸となり、圧力面２ｂは羽根車１に面し
ない側に凸となるように構成されている。α８〉α２と
するのはα３≦α２とすると喉部の幅ＡＢが小さくなり
、この部分の流速の増加による摩擦損失の増加、喉部よ
り下流側の減速量の増加による減速損失の増加によって
ディフューザ性能が低下するので、これを防止するため
に必要である。Flows 3a, 3 given kinetic energy by impeller 1
When b passes through the diffuser blade 2, part of the kinetic energy is converted into pressure. When the flow rate is larger than the design condition, the diffuser blade 2 approaches from a direction closer to the radial direction than the extension of the warp line 4 of the diffuser blade 2, as shown in flow 3a, and when the flow rate is smaller than the design condition, the warp line approaches the flow line 3b, as shown in flow 3b. The diffuser blade 2 is approached from a direction farther from the radial direction than the extension of the diffuser blade 2. The tip of diffuser blade 2 is the third
As shown in the figure, the angle formed by the warp line 4 and the tangent to the circle centered on the rotation axis of the impeller 1 is between the leading edge, the front AiNA of the blade adjacent to the suction surface 2a, and the suction surface 2a. Between the extension of the throat width AB, which is the shortest distance, αl>α2. αS>α2, and the negative pressure surface 2a is convex toward the impeller 1 near the leading edge A, and the pressure surface 2b is convex toward the side not facing the impeller 1. . The reason why α8>α2 is set is that when α3≦α2, the throat width AB becomes smaller, and the diffuser This is necessary to prevent this, since performance will deteriorate.
本実施例の羽根付ディフューザは、このように構成され
ているから、従来の羽根付ディフューザより広い流量範
囲で高い性能を維持できる。第４図、第５図にその状況
を示す。第４図は従来の羽根付ディフューザで前縁にお
けるそり線４の接線と羽根車１の回転軸を中心とする円
の接線の成す角α１を大流量に合わせて設計した場合で
ある。Since the vaned diffuser of this embodiment is configured in this way, it can maintain high performance over a wider flow rate range than conventional vaned diffusers. The situation is shown in Figures 4 and 5. FIG. 4 shows a conventional bladed diffuser in which the angle α1 formed by the tangent to the warp line 4 at the leading edge and the tangent to the circle centered on the rotational axis of the impeller 1 is designed to accommodate a large flow rate.
この場合、大流量時には流入する流れ３ａは負圧面２ａ
に衝突する方向から流入するので負圧面２ａの側の流れ
は羽根面に沿って流れる。圧力面２ｂの側ｌ±流れ３ａ
と圧力面２ｂの方向大差なく、かつ流れが隣接するディ
フューザ羽根の負圧面に衝突する方向であるため、羽根
面に沿って流れる。In this case, when the flow is large, the inflowing flow 3a is on the negative pressure surface 2a.
Since the flow flows from the direction of collision with the suction surface 2a, the flow on the side of the negative pressure surface 2a flows along the blade surface. Side l of pressure surface 2b±flow 3a
There is no significant difference in direction between the pressure surface 2b and the pressure surface 2b, and the flow is in the direction in which it collides with the suction surface of the adjacent diffuser blade, so it flows along the blade surface.
−カポ流量で運転しようとすると流れは３ｂの方向から
流入するため圧力面２ｂの側の流れは羽根面に沿って流
れるが負圧面２ａの側は流れ３ｂと負圧面２ａの成す角
が大きくかつ対面するディフューザ羽根が無いため羽根
面から、はく離し、ディフューザが失速する。失速が全
ディフューザ羽根でなく一部で生ずると旋回失速による
振動が発生し、全ディフューザ羽根が失速するとサージ
に入る。このため小流量側の運転限界は、流れが羽根面
に沿って流れる範囲に限られる。第５図は角α１を減゛
少させて負圧面が小流量時の流れの方向に沿うようにし
て、はく離が生じなり）ようにしたものである。この場
合、大流量の流れ３ａに対しては圧力面２ｂの方向の不
一致が大きいため、流れがはく離する。圧力面２ｂのは
く離の場合、流入する流れ３ａが隣接するディフューザ
羽根の負圧面によって抑えられる方向であることなどか
ら第５図に示すように流れは再び圧力面２ｂに付着する
傾向が強いので、ディフューザの失速が生ずることは少
ない。しかし、はく離が部分的であっても境界層の発達
は大きく、プロツケージの発達によってディフューザの
圧力回復性能が低下する。- When operating at a capo flow rate, the flow flows in from the direction 3b, so the flow on the pressure surface 2b side flows along the blade surface, but on the suction surface 2a side, the angle between flow 3b and suction surface 2a is large and Since there are no diffuser blades facing each other, they separate from the blade surface, causing the diffuser to stall. If the stall occurs in some but not all the diffuser blades, vibrations will occur due to the rotating stall, and if all the diffuser blades stall, a surge will occur. Therefore, the operating limit on the small flow rate side is limited to the range in which the flow flows along the blade surface. In FIG. 5, the angle α1 is reduced so that the negative pressure surface is along the flow direction at a small flow rate, so that no separation occurs. In this case, since there is a large mismatch in the direction of the pressure surface 2b with respect to the flow 3a with a large flow rate, the flow separates. In the case of separation of the pressure surface 2b, since the inflowing flow 3a is suppressed by the negative pressure surface of the adjacent diffuser blade, the flow has a strong tendency to adhere to the pressure surface 2b again as shown in FIG. Diffuser stalling is less likely to occur. However, even if the separation is partial, the boundary layer will develop significantly, and the pressure recovery performance of the diffuser will deteriorate due to the development of the blockage.
以上からすると圧力面２ｂは第４図、負圧面２ａは第５
図の形状とすると、大流量、小流量いずれの場合も流れ
が羽根面に沿うようにできるが、羽根厚さが大きくなり
高亜音速域で使用するディフューザには適さなくなる。From the above, the pressure surface 2b is shown in Figure 4, and the negative pressure surface 2a is shown in Figure 5.
With the shape shown in the figure, the flow can be made to follow the blade surface for both large and small flow rates, but the blade thickness increases, making it unsuitable for a diffuser used in a high subsonic speed range.
第６図から第９図にその様子を概念的に示す。第６図は
第４図のディフューザ羽根の前縁付近、第７図は第５図
のディフューザ羽根前縁付近の拡大図である。第８図は
第６図の圧力面２ｂと第７図の負圧面２ａを組合わせた
羽根であり厚みが大幅に増加する。第９図は第７図の圧
力面２ｂの前縁付近を削除して負圧面２ａの形状は第７
図とほぼ同一でかつ、圧力面２ｂの形状は第６図とほぼ
同一になるようにしたものである。この場合第８図のご
とく羽根厚さを大きくする必要が無く高亜音速流に適し
た羽根形状が得られる。そり線４は羽根前縁付近のみ半
径方向に近づく形状となり本実施例の羽根形状の特徴を
成す。The situation is conceptually shown in FIGS. 6 to 9. 6 is an enlarged view of the vicinity of the leading edge of the diffuser blade of FIG. 4, and FIG. 7 is an enlarged view of the vicinity of the leading edge of the diffuser blade of FIG. 5. FIG. 8 shows a blade in which the pressure surface 2b of FIG. 6 and the suction surface 2a of FIG. 7 are combined, and the thickness is significantly increased. In Figure 9, the vicinity of the front edge of the pressure surface 2b in Figure 7 has been deleted, and the shape of the negative pressure surface 2a is the same as that of the seventh figure.
It is almost the same as the figure, and the shape of the pressure surface 2b is almost the same as in FIG. 6. In this case, as shown in FIG. 8, there is no need to increase the blade thickness, and a blade shape suitable for high subsonic flow can be obtained. The warp line 4 has a shape that approaches in the radial direction only near the leading edge of the blade, which is a characteristic of the blade shape of this embodiment.
尚ディフューザ羽根前縁付近からの流れのばくりについ
ては、前縁付近の羽根形状以外にも、たとえば、前轍と
のど部ＡＢの間の羽根形状、のど部面積、のど部より下
流の減速量２羽根卓出口の流れ分布などの重要な因子が
ある。本実施例の目的はこれらの因子の影響を制御する
ことではなく、これらの因子の条件が類似の場合に、流
れの（まくりが生じにくい形状を提供することにある。Regarding the flow from the vicinity of the leading edge of the diffuser blade, in addition to the shape of the blade near the leading edge, for example, the shape of the blade between the front rut and the throat AB, the area of the throat, and the amount of deceleration downstream from the throat There are important factors such as the flow distribution at the exit of the two-blade table. The purpose of this embodiment is not to control the influence of these factors, but to provide a flow shape that is less likely to cause curling when the conditions of these factors are similar.
第１０図〜第１３図は本発明の他の実施例を示す図であ
る。10 to 13 are diagrams showing other embodiments of the present invention.
第１０図は第２の実施例のディフューザ羽根を示す図で
第１の実施例を示す第２図のディフューザ羽根２の周辺
を拡大して図に相当する。ディフューザ羽根２は側板側
５の前縁部分６１よ１羽根卓出口の近くにある。これに
対し各板側７の前縁部分８は側板側部分６より羽根車１
から離れてν）る。FIG. 10 is a view showing the diffuser blade of the second embodiment, and corresponds to an enlarged view of the vicinity of the diffuser blade 2 of FIG. 2 showing the first example. The diffuser blade 2 is located closer to the leading edge portion 61 of the side plate side 5 than the blade outlet. On the other hand, the front edge portion 8 of each plate side 7 is closer to the impeller 1 than the side plate side portion 6.
move away from ν).
この実施例の特徴はディフューザ羽根前縁の羽根車に近
い部分が少ないので、ディフューザ羽根あるいは羽根車
の受ける流体力の低減、騒音の低減に効果があり、高密
度の気体を扱う機種しこ適する。The feature of this embodiment is that the leading edge of the diffuser blade has a small portion close to the impeller, so it is effective in reducing the fluid force applied to the diffuser blade or impeller and reducing noise, making it suitable for models that handle high-density gas. .
この実施例の場合、前縁部分６．前縁部分８及びその中
間の少なくとも一ケ所の断面形状は第７図の形状とする
。In this embodiment, the leading edge portion 6. The cross-sectional shape of the front edge portion 8 and at least one place in between is the shape shown in FIG.
第１１図は他の実施例を示す図でディフューザ羽根２の
各板側７を羽根車に近づけた場合である。FIG. 11 is a diagram showing another embodiment, in which each plate side 7 of the diffuser blade 2 is brought close to the impeller.
第１２図、第１３図は更に他の実施例を示す図で、第１
２図はディフューザ羽根の前縁を階段状番こ構成して単
純化を図ったもの、第１３図（±前縁を直線で構成し第
１１図の実施例の簡略イヒを図ったものである。第１４
図は第１０図、第１２図、第１３図の実施例で最も効果
的な前縁各部の寸法関係を説明する図で羽根車の半径ｒ
＋、側板側の前縁部分６の半径位置ｒＳ、心板側板側縁
部分８の半径位ｉｒｈの間に、１＜ｒｓ＜ｒｔ≦１．１
≦ｒｈ／ｒ□の間係、および側板側の前縁部分の平均的
な高さｂＬとディフューザ羽根の高さｂの間に０．１＜
ｂｌ／ｂ＜０．６の関係がある場合に効果力４ｉ）。FIG. 12 and FIG. 13 are diagrams showing still other embodiments.
Figure 2 shows a simplified example in which the leading edge of the diffuser blade is configured with a step-like guard, and Figure 13 (in which the leading edge of the diffuser blade is configured with a straight line to simplify the embodiment shown in Figure 11). .14th
The figure is a diagram explaining the most effective dimensional relationship of each part of the leading edge in the embodiments shown in FIGS. 10, 12, and 13, and shows the radius r of the impeller.
+, 1<rs<rt≦1.1 between the radial position rS of the leading edge portion 6 on the side plate side and the radial position irh of the side edge portion 8 of the core plate side plate.
≦rh/r□ and 0.1< between the average height bL of the front edge portion on the side plate side and the height b of the diffuser blade.
Effectiveness 4i) if there is a relationship of bl/b<0.6.
第１１図の実施例での寸法関係は第１０図のＪヒ板側と
側板側を入れ替えて同じ関係が成り立つようにすれば良
い。The dimensional relationship in the embodiment shown in FIG. 11 may be changed by replacing the J-hi plate side and the side plate side in FIG. 10 so that the same relationship holds true.
第１５図から第１８図はそれぞれ更に他の実施例を示す
図で、第１５図は第２の実施例を示す第１０図に相当す
る図である。この実施例ではディフューザ羽根２の内周
に近い側に、ディフューザ羽根２よりも弦長が短くかつ
高さが同等以下の補助羽根９を側板５上に設けディフュ
ーザ羽根２の前縁及び補助羽根９の前縁の両方ある０１
よ一方の断面形状は第９図の形状としたものである。こ
の実施例の特徴は、補助羽根９が独立してν＼るので少
流量側の失速部止が一層効果的に行える。褪ムこある。15 to 18 are diagrams showing still other embodiments, and FIG. 15 is a diagram corresponding to FIG. 10 showing the second embodiment. In this embodiment, on the side near the inner circumference of the diffuser blade 2, an auxiliary blade 9 having a chord length shorter than that of the diffuser blade 2 and a height equal to or less than that is provided on the side plate 5, and the leading edge of the diffuser blade 2 and the auxiliary blade 9 are provided. Both leading edges of 01
The cross-sectional shape of the other side is as shown in FIG. The feature of this embodiment is that the auxiliary vanes 9 are independently ν\, so that stalling on the low flow rate side can be more effectively stopped. It's faded.
第１６図は補助羽根９の配置を示すため羽根車１の回転
軸方向から見たディフューザを示す。FIG. 16 shows the diffuser viewed from the direction of the rotation axis of the impeller 1 to show the arrangement of the auxiliary blades 9.
第１７図は補助羽根９を側板側７番こ設もｔだ場合、第
１８図は補助羽根９の前縁を傾斜させた図である。これ
らの実施例でもディフューザ羽根２．補助羽根９の少な
くとも一方の前縁１士第９図の形状とする。第１７図の
実施例の特徴側よ１ひ板側しこ低エネルギ流れが生ずる
性質の羽根車の場合しこ適しており、第１８図の実施例
では、騒音、振動力１低０点にある。FIG. 17 shows the case where the auxiliary blade 9 is also installed on the side plate side, and FIG. 18 shows the front edge of the auxiliary blade 9 inclined. In these embodiments, the diffuser blade 2. At least one leading edge of the auxiliary blade 9 has the shape shown in FIG. The feature of the embodiment shown in Fig. 17 is that it is suitable for impellers that produce low-energy flows from side to side, and in the embodiment shown in Fig. 18, noise and vibration force are reduced to 1 and 0 points. be.
本発明によれば羽根付ディフューザの羽根前縁部分の形
状に起因する流れのはく離を防止できるので、小流量側
の失速限界を更に小流量側しこ移動させるとともに大流
量側の性能低下を防止できるので、ディフューザの作動
範囲を拡大でき、従つて圧縮機の運転範囲を拡大できる
効果がある。According to the present invention, it is possible to prevent flow separation due to the shape of the leading edge of the vane of a vaned diffuser, so the stall limit on the small flow rate side can be further shifted toward the small flow rate side, and performance deterioration on the high flow rate side can be prevented. As a result, the operating range of the diffuser can be expanded, and therefore the operating range of the compressor can be expanded.
第１図は本発明の一実施例のディフューザを羽根を羽根
車の回転軸の方向から見た図、第２図は本発明のディフ
ューザを適用した遠心圧縮機の縦断面図、第３図は本発
明のディフューザの羽根の先端部分の詳細図、第４図、
第５図から第９図は本発明の詳細な説明する図、第１０
図から第１３図はそれぞれ他の実施例を示す図、第１４
図は第１０図から第１３図の実施例の効果的な寸法関係
を示す図、第１５図は更に他の実施例の断面図、第１６
図は第１５図のものを羽根車の回転軸方向から見た図、
第１７図は更に他の実施例を示す図、第１８図は更に他
の実施例を示す図である。１・・・羽根車、２・・・デ
ィフューザ羽根、４・・・そり線、９１
国
不
図
２−−−−７”ｘ；ｈ−”ｉ”導峡
不
乙
図
図
纂
図
■
図
第
乙
因
夏
図
■
／θ
図
篤
１
図
纂
１４
図
どｐ −−−１℃本反イ毘りＱ＃秀象Ｊ印ジグｔｚ半夕
Ｌｂ−一升止１ｆ）高１
ｂｒ−４す１１スｌ之イ暴り司肩５Ｒ１丁シカ’＋７）
円乙丸柔り白韓７ヒ；二ニア
図
不
３
図Fig. 1 is a view of a diffuser according to an embodiment of the present invention, with the blades viewed from the direction of the rotation axis of the impeller, Fig. 2 is a longitudinal cross-sectional view of a centrifugal compressor to which the diffuser of the present invention is applied, and Fig. 3 is a view of the diffuser according to an embodiment of the present invention. Detailed view of the tips of the blades of the diffuser of the present invention, FIG.
5 to 9 are diagrams explaining the present invention in detail, and FIG.
Figures 13 to 13 show other embodiments, and Figure 14 shows other embodiments.
The figures are diagrams showing the effective dimensional relationships of the embodiments shown in FIGS. 10 to 13, FIG. 15 is a sectional view of still another embodiment, and FIG.
The figure is the one in Figure 15 viewed from the direction of the impeller's rotation axis,
FIG. 17 is a diagram showing still another embodiment, and FIG. 18 is a diagram showing still another embodiment. 1... Impeller, 2... Diffuser blade, 4... Sled wire, 91 Kunibuzu 2-----7"x;h-"i" Dokyo Futsuzu map ■ Figure No. Otsuin Summer Diagram■ /θ Diagram Atsushi 1 Diagram Collection 14 Diagram p ---1℃ Honri Ibi Q# Shuzo J-in Jig tz Hanyu Lb-1sho 1f) High 1 br-4s 11 5 R1 Shika' + 7)
En Otomaru Wari Hakuhan 7 Hi; Ninia Zufu 3 Figure
Claims (1)
羽根車から吐出される流体の運動エネルギーを静止羽根
の作用によつて圧力に変換する遠心圧縮機のディフュー
ザにおいて、ディフューザ羽根のそり線と、羽根車の回
転軸を中心とする円の交点における、それぞれの曲線に
対する接線の成す角が、該ディフューザ羽根の前縁から
、該ディフューザ羽根の半径方向内側に隣接したディフ
ューザ羽根前縁と同前縁に面した該ディフューザ羽根面
の最短距離を結ぶ直線の延長上に達するまでに一旦減少
することを特徴とする遠心圧縮機の羽根付ディフューザ
。 ２、請求項１記載のディフューザにおいて、そり線と羽
根車の回転軸を中心とする円の接線の成す角が一旦減少
する位置での羽根表面のうち羽根車に対面する側は羽根
車の側に凸となり、羽根車に対面しない側は対面しない
側に凸となることを特徴とする遠心圧縮機のディフュー
ザ。 ３、ディフューザ羽根の側板側を心板側より羽根車方向
に延設して前記ディフューザ羽根の前縁を心板側から側
板側に傾斜させ、かつ側板側に近い前縁、心板側に近い
前縁及び、これらの中間部分の前縁の少なくとも一ケ所
は請求項１あるいは請求項２の形状を有することを特徴
とする遠心圧縮機のディフューザ。 ４、ディフューザ羽根の心板側より羽根車方向に延設し
て前記ディフューザ羽根の前縁を側板側より心板側に傾
斜させ、かつ側板側に近い前縁、心板側に近い前縁及び
これらの中間部分の前縁の少なくとも一ケ所は請求項１
あるいは請求項２の形状を有することを特徴とする遠心
圧縮機のディフューザ。 ５、ディフューザ羽根の内周に近い側に、該ディフュー
ザ羽根よりも弦長が短くかつ、高さが同等以下の補助羽
根を心板側、側板側の一方あるいは両方に設け該補助羽
根の一方の羽根面のみを前記ディフューザ羽根に対向さ
せ、かつディフューザ羽根、補助羽根の少なくともいず
れか一方の前縁が請求項１あるいは請求項２の形状を有
することを特徴とする遠心圧縮機のディフューザ。 ６、請求項５記載の羽根付ディフューザにおいて、補助
羽根の前縁の一部が、羽根車から遠ざかる方向に傾斜し
たことを特徴とする遠心圧縮機の羽根付ディフューザ。[Claims] 1. A plurality of diffuser blades are arranged around the outer periphery of the impeller,
In a diffuser for a centrifugal compressor that converts the kinetic energy of fluid discharged from an impeller into pressure by the action of stationary blades, at the intersection of the warp line of the diffuser blade and a circle centered on the rotation axis of the impeller, The angle formed by the tangent to each curve is the line connecting the shortest distance from the leading edge of the diffuser blade to the leading edge of the diffuser blade adjacent to the inside in the radial direction of the diffuser blade and the diffuser blade surface facing the same leading edge. A vaned diffuser for a centrifugal compressor, characterized in that the blade decreases once before reaching the extension. 2. In the diffuser according to claim 1, the side of the blade surface facing the impeller at the position where the angle between the warp line and the tangent to the circle centered on the rotation axis of the impeller once decreases is the side of the impeller. A diffuser for a centrifugal compressor, characterized in that the side that does not face the impeller is convex on the side that does not face the impeller. 3. The side plate side of the diffuser blade extends from the core plate side toward the impeller, so that the leading edge of the diffuser blade is inclined from the core plate side to the side plate side, and the leading edge close to the side plate side is close to the core plate side. A diffuser for a centrifugal compressor, characterized in that at least one portion of the leading edge and the leading edge of an intermediate portion thereof has the shape according to claim 1 or claim 2. 4. Extending from the core plate side of the diffuser blade toward the impeller so that the front edge of the diffuser blade is inclined from the side plate side to the core plate side, and a leading edge close to the side plate side, a leading edge close to the core plate side, and At least one portion of the front edge of these intermediate portions is defined in claim 1.
Alternatively, a diffuser for a centrifugal compressor having the shape according to claim 2. 5. On the side close to the inner circumference of the diffuser blade, provide an auxiliary blade with a chord length shorter than that of the diffuser blade and the same or less height on one or both of the core plate side and side plate side. 3. A diffuser for a centrifugal compressor, wherein only the blade surface faces the diffuser blade, and a leading edge of at least one of the diffuser blade and the auxiliary blade has the shape according to claim 1 or claim 2. 6. The vaned diffuser for a centrifugal compressor according to claim 5, wherein a part of the leading edge of the auxiliary vane is inclined in a direction away from the impeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1271654A JPH03134298A (en) | 1989-10-20 | 1989-10-20 | Diffuser with vanes of centrifugal compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1271654A JPH03134298A (en) | 1989-10-20 | 1989-10-20 | Diffuser with vanes of centrifugal compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH03134298A true JPH03134298A (en) | 1991-06-07 |
Family
ID=17503049
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1271654A Pending JPH03134298A (en) | 1989-10-20 | 1989-10-20 | Diffuser with vanes of centrifugal compressor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH03134298A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05106597A (en) * | 1991-10-21 | 1993-04-27 | Hitachi Ltd | Centrifugal compressor |
| WO2005090794A1 (en) * | 2004-03-23 | 2005-09-29 | Mitsubishi Heavy Industries, Ltd. | Centrifugal compressor and method of manufacturing impeller |
| CN100406746C (en) * | 2004-03-23 | 2008-07-30 | 三菱重工业株式会社 | Centrifugal compressor and manufacturing method for impeller |
| JP2009538403A (en) * | 2006-05-26 | 2009-11-05 | アーベーベー ターボ システムズ アクチエンゲゼルシャフト | Diffuser |
| CN105736457A (en) * | 2016-03-10 | 2016-07-06 | 中国航空动力机械研究所 | Centrifugal compressor |
| CN107676305A (en) * | 2017-08-10 | 2018-02-09 | 中国北方发动机研究所(天津) | A kind of stepped guide vane vaned diffuser structure |
| EP3805572A1 (en) * | 2019-10-07 | 2021-04-14 | Siemens Aktiengesellschaft | Diffuser, radial turbocompressor |
| CN113464497A (en) * | 2021-06-24 | 2021-10-01 | 珠海格力电器股份有限公司 | Diffuser, compressor and air cycle machine |
| EP4215759A1 (en) * | 2022-01-25 | 2023-07-26 | Siemens Energy Global GmbH & Co. KG | Diffuser for a radial turbocompressor |
-
1989
- 1989-10-20 JP JP1271654A patent/JPH03134298A/en active Pending
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05106597A (en) * | 1991-10-21 | 1993-04-27 | Hitachi Ltd | Centrifugal compressor |
| WO2005090794A1 (en) * | 2004-03-23 | 2005-09-29 | Mitsubishi Heavy Industries, Ltd. | Centrifugal compressor and method of manufacturing impeller |
| KR100730840B1 (en) * | 2004-03-23 | 2007-06-20 | 미츠비시 쥬고교 가부시키가이샤 | Centrifugal compressor and method of manufacturing impeller |
| CN100406746C (en) * | 2004-03-23 | 2008-07-30 | 三菱重工业株式会社 | Centrifugal compressor and manufacturing method for impeller |
| JP2009538403A (en) * | 2006-05-26 | 2009-11-05 | アーベーベー ターボ システムズ アクチエンゲゼルシャフト | Diffuser |
| CN105736457A (en) * | 2016-03-10 | 2016-07-06 | 中国航空动力机械研究所 | Centrifugal compressor |
| CN107676305A (en) * | 2017-08-10 | 2018-02-09 | 中国北方发动机研究所(天津) | A kind of stepped guide vane vaned diffuser structure |
| EP3805572A1 (en) * | 2019-10-07 | 2021-04-14 | Siemens Aktiengesellschaft | Diffuser, radial turbocompressor |
| CN113464497A (en) * | 2021-06-24 | 2021-10-01 | 珠海格力电器股份有限公司 | Diffuser, compressor and air cycle machine |
| EP4215759A1 (en) * | 2022-01-25 | 2023-07-26 | Siemens Energy Global GmbH & Co. KG | Diffuser for a radial turbocompressor |
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