JPH11257291A - Diffuser of centrifugal compressor - Google Patents
Diffuser of centrifugal compressorInfo
- Publication number
- JPH11257291A JPH11257291A JP10082988A JP8298898A JPH11257291A JP H11257291 A JPH11257291 A JP H11257291A JP 10082988 A JP10082988 A JP 10082988A JP 8298898 A JP8298898 A JP 8298898A JP H11257291 A JPH11257291 A JP H11257291A
- Authority
- JP
- Japan
- Prior art keywords
- diffuser
- passage
- side wall
- impeller
- throat
- 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.)
- Granted
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
- F04D29/40—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
【０００１】[0001]
【発明の属する技術分野】本発明は、遠心圧縮機におい
て、案内羽根による拡大通路によって流体の運動エネル
ギーを圧力エネルギーに変換するディフューザーの構造
に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a structure of a diffuser in a centrifugal compressor, which converts kinetic energy of fluid into pressure energy by an enlarged passage formed by guide vanes.
【０００２】[0002]
【従来の技術】遠心圧縮機では、羽根車の外周側周囲に
拡大通路によるディフューザーが形成され、羽根車の回
転によって付与された流体の運動エネルギーをディフュ
ーザーによって圧力エネルギーに変換するように構成さ
れる。2. Description of the Related Art In a centrifugal compressor, a diffuser is formed by an enlarged passage around an outer peripheral side of an impeller, and the kinetic energy of fluid given by rotation of the impeller is converted into pressure energy by the diffuser. .
【０００３】このようなディフューザーとして、拡大通
路に案内羽根を備えたものがある。[0003] As such a diffuser, there is one having a guide blade in an enlarged passage.
【０００４】羽根付きディフューザーは、図５に遠心圧
縮機のディフューザー部位の部分概略断面図、図６にそ
のＤ−Ｄ断面図を示すように、羽根車３０の外周側に形
成された回転軸方向前後の側壁１０Ｈ，１０Ｓ（羽根車
のハブ側と対応するハブ側側壁１０Ｈ，羽根車のシュラ
ウド側と対応するシュラウド側側壁１０Ｓ）によって挟
まれた通路空間（ハブ側側壁１０Ｈの内面２０Ｈとシュ
ラウド側側壁１０Ｓの内面２０Ｓの間の空間）が、周方
向に複数配設された案内羽根２１（２１′）…によって
仕切られ、案内羽根２１と隣接する案内羽根２１′の間
に所定の広がり角の拡大通路を形成するように構成され
ている。A diffuser with blades is shown in FIG. 5 in a partial schematic sectional view of a diffuser portion of a centrifugal compressor, and in FIG. A passage space (the inner surface 20H of the hub side wall 10H and the shroud side) sandwiched between the front and rear side walls 10H, 10S (the hub side wall 10H corresponding to the hub side of the impeller, the shroud side wall 10S corresponding to the shroud side of the impeller). The space between the inner surfaces 20S of the side walls 10S is partitioned by a plurality of guide vanes 21 (21 ')... Arranged in the circumferential direction, and a predetermined spread angle is formed between the guide vane 21 and the adjacent guide vane 21'. It is configured to form an enlarged passage.
【０００５】案内羽根２１は、高さ方向（通路の厚さ方
向）で断面形状一定の二次元翼であってその形状は羽根
車３０からの流体の流出角に基づいて設定されるが、羽
根車３０からの流出角は、羽根車３０の形状に起因して
通路の厚さ方向（羽根車３０の回転軸と平行する方向）
で異なって図８に示すように羽根車３０のシュラウド側
で大きくハブ側で小さくなり、また、その流量も厚さ方
向の位置によって分布を有するため、これら流出角分布
及び流量分布を勘案して平均的に高い効率が得られるよ
うに設定される。The guide blade 21 is a two-dimensional blade having a constant cross-sectional shape in the height direction (the thickness direction of the passage) and its shape is set based on the outflow angle of the fluid from the impeller 30. The outflow angle from the wheel 30 depends on the shape of the impeller 30 in the thickness direction of the passage (the direction parallel to the rotation axis of the impeller 30).
As shown in FIG. 8, the flow rate is large on the shroud side of the impeller 30 and small on the hub side, and the flow rate also has a distribution depending on the position in the thickness direction. It is set so that high efficiency is obtained on average.
【０００６】尚、羽根付ディフューザーの案内羽根部分
の通路の厚さは通常は一定に設定されるが、希に外周側
が広がるように形成して圧縮機全体の外形を小さく構成
するようにしたものもある。The thickness of the passage of the guide vane portion of the vaned diffuser is usually set to a constant value, but is rarely formed so that the outer peripheral side is widened to reduce the outer shape of the entire compressor. There is also.
【０００７】[0007]
【発明が解決しようとする課題】しかしながら、羽根車
３０の形状に起因する流出角の差異は２０〜３０゜にも
及び、上記従来のごとく案内羽根２１の形状を平均的に
設定した場合、特に流出角が小さい羽根車のハブ側と対
応する案内羽根２１の圧力面２１Ａに流体剥離が発生す
るという問題があった。即ち、図６及びそのＥ矢視図に
相当する通路出口図である図７中に低速領域を示すよう
に、案内羽根２１の後端部のハブ側内面２０Ｈの近傍に
剥離が発生する低速部位がある。However, the difference in the outflow angle due to the shape of the impeller 30 is as large as 20 to 30 °, and when the shape of the guide blade 21 is set averagely as in the above-mentioned conventional case, particularly, There has been a problem that fluid separation occurs on the pressure surface 21A of the guide blade 21 corresponding to the hub side of the impeller having a small outflow angle. That is, as shown in FIG. 6 and FIG. 7 which is a passage exit view corresponding to the view taken in the direction of arrow E, a low-speed region where peeling occurs near the hub-side inner surface 20H at the rear end of the guide blade 21 is shown. There is.
【０００８】このような剥離が生ずると、ディフューザ
ーの全圧損失が増加し、性能低下を来す。[0008] When such peeling occurs, the total pressure loss of the diffuser increases and the performance decreases.
【０００９】本発明は、上記解決課題に鑑みて成された
ものであって、流出角の小さなハブ側においても案内羽
根の圧力面側に剥離を生ずることがなく、ディフューザ
ーの全圧損失の増加を防いで効率向上を可能とする遠心
圧縮機のディフューザーを提供することを目的とする。SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned problems, and does not cause separation on the pressure surface side of the guide blade even on the hub side having a small outflow angle, thereby increasing the total pressure loss of the diffuser. It is an object of the present invention to provide a diffuser for a centrifugal compressor, which can improve efficiency by preventing the occurrence of a diffuser.
【００１０】[0010]
【課題を解決するための手段】上記目的を達成する本発
明に係る遠心圧縮機のディフューザーは、遠心圧縮機に
おいて、案内羽根による拡大通路によって流体の運動エ
ネルギーを圧力エネルギーに変換するディフューザーで
あって、拡大通路を形成する回転軸方向の少なくとも一
方の側壁面が、スロートより下流側の位置から通路厚さ
を縮小する側に傾斜形成されていることを特徴とする。A diffuser for a centrifugal compressor according to the present invention which achieves the above object is a diffuser for converting kinetic energy of fluid into pressure energy by an enlarged passage formed by guide vanes in the centrifugal compressor. At least one side wall surface in the rotation axis direction forming the enlarged passage is inclined from a position downstream of the throat to a side where the passage thickness is reduced.
【００１１】[0011]
【発明の実施の形態】以下添付図面を参照して本発明の
実施の形態について説明する。図１は、本発明に係る遠
心圧縮機のディフューザーの一構成例を適用した圧縮機
のディフューザー部位の部分概略断面図であり、図２は
そのＡ−Ａ断面図、図３は図２のＢ−Ｂ断面図である。Embodiments of the present invention will be described below with reference to the accompanying drawings. FIG. 1 is a partial schematic cross-sectional view of a diffuser portion of a compressor to which a configuration example of a diffuser of a centrifugal compressor according to the present invention is applied, FIG. 2 is a cross-sectional view taken along line AA, and FIG. It is -B sectional drawing.
【００１２】図示圧縮機１は、ケーシング１０によっ
て、羽根車室１１とその外周側の渦形室１２の間にディ
フューザー２０が形成されており、羽根車室１１内に配
設された羽根車３０が図示しない回転駆動手段によって
回転駆動されて、吸気口１３から吸入した流体に径方向
の運動エネルギーを与えると共にディフューザー２０で
圧力エネルギーに変換して渦形室１２に吐出するように
なっている。The illustrated compressor 1 has a casing 10 in which a diffuser 20 is formed between an impeller chamber 11 and a spiral chamber 12 on the outer periphery thereof, and an impeller 30 disposed in the impeller chamber 11 is provided. Are rotationally driven by rotation driving means (not shown) to apply kinetic energy in the radial direction to the fluid sucked from the intake port 13 and convert the fluid into pressure energy by the diffuser 20 and discharge the pressure energy to the spiral chamber 12.
【００１３】ディフューザー２０は、羽根車３０の外周
側に、ケーシング１０の側壁（羽根車１３のハブ側と対
応するハブ側側壁１０Ｈ，羽根車１３のシュラウド側と
対応するシュラウド側側壁１０Ｓ）に挟まれた通路空間
（ハブ側側壁１０Ｈの内面２０Ｈとシュラウド側側壁１
０Ｓの内面２０Ｓの間の空間）が周方向に複数配設され
た案内羽根２１（２１′）…によって仕切られ、案内羽
根２１と隣接する案内羽根２１′の間にスロートから下
流が半径方向に所定の広がり角で拡大通路を形成してい
る。The diffuser 20 is sandwiched on the outer peripheral side of the impeller 30 by the side wall of the casing 10 (a hub side wall 10H corresponding to the hub side of the impeller 13 and a shroud side wall 10S corresponding to the shroud side of the impeller 13). Passage space (the inner surface 20H of the hub side wall 10H and the shroud side wall 1).
The space between the inner surfaces 20S of the outer and outer guides 21S is partitioned by a plurality of guide vanes 21 (21 ')... An enlarged passage is formed at a predetermined spread angle.
【００１４】ここで、ハブ側側壁１０Ｈの内面２０Ｈ
は、スロートより下流側の所定位置：Ｓから、通路厚さ
を縮小させる側に傾斜形成されている。Here, the inner surface 20H of the hub side wall 10H.
Is inclined from a predetermined position S downstream of the throat to a side where the thickness of the passage is reduced.
【００１５】このように、ハブ側側壁１０Ｈの内面２０
Ｈがスロートより下流側の位置：Ｓから通路面積を縮小
させる側に傾斜形成されていることにより、案内羽根２
１の後端に発達する剥離を抑制することが可能となる。As described above, the inner surface 20 of the hub side wall 10H is formed.
Since H is formed at a position downstream of the throat: from S to the side for reducing the passage area, the guide blade 2
It is possible to suppress the peeling that develops at the rear end of No. 1.
【００１６】即ち、隣接する案内羽根１２によって形成
された拡大通路内では、案内羽根２１の圧力面側２１Ａ
に流体剥離を生じ易いが、羽根車３０の形状に起因する
通路厚さ方向の流出分布により、流出角の大きいシュラ
ウド側側壁１０Ｈの内面２０Ｈの境界層内に案内羽根２
１の負圧面２１Ｂ側から圧力面２１Ａ側へ流れる二次流
れが生じ、この二次流れが圧力面２１Ａに衝突した後圧
力面２１Ａに沿ってハブ側側壁１０Ｈ（内面２０Ｈ）に
向かうためにこれによって剥離が押さえられ、二次流れ
の大きい案内羽根１２の先端部位では剥離が小さく、案
内羽根１２の後端のハブ側側壁１０Ｈの内面２０Ｈ近傍
に剥離領域が形成される。That is, in the enlarged passage formed by the adjacent guide blades 12, the pressure surface side 21A of the guide blade 21
However, due to the outflow distribution in the thickness direction of the passage due to the shape of the impeller 30, the guide blades 2 are formed in the boundary layer of the inner surface 20H of the shroud side wall 10H having a large outflow angle.
The secondary flow that flows from the negative pressure surface 21B side to the pressure surface 21A side occurs, and this secondary flow collides with the pressure surface 21A and then goes to the hub side wall 10H (the inner surface 20H) along the pressure surface 21A. The separation is suppressed at the leading end portion of the guide blade 12 where the secondary flow is large, and a separation region is formed near the inner surface 20H of the hub side wall 10H at the rear end of the guide blade 12.
【００１７】一方、拡大通路は、案内羽根１２の先端部
と隣接する案内羽根１２の負圧面１２Ｂとの間に形成さ
れるスロート面積を最小として所定角度で拡大するた
め、流体の流入量はこのスロート面積によって決まる。On the other hand, since the enlarged passage expands at a predetermined angle while minimizing the throat area formed between the distal end portion of the guide blade 12 and the suction surface 12B of the adjacent guide blade 12, the inflow amount of the fluid is It depends on the throat area.
【００１８】従って、流体剥離が発生する案内羽根１２
の後端と対応するスロートより下流側の側壁１０Ｈ（又
は１０Ｓ）の内面２０Ｈ（又は２０Ｓ）を傾斜させて通
路厚さを縮小することで、流量は変わらず下流側の通路
面積が通常の案内羽根高さ一定の通路面積よりも絞られ
ることとなり、その結果、剥離の生ずる低速領域を減少
させることができるものである。Accordingly, the guide blades 12 at which fluid separation occurs are provided.
By reducing the passage thickness by inclining the inner surface 20H (or 20S) of the side wall 10H (or 10S) downstream of the throat corresponding to the rear end of the throat, the flow rate does not change and the passage area on the downstream side is normal. As a result, the blade area is narrowed more than the passage area having a fixed blade height, and as a result, a low-speed region where peeling occurs can be reduced.
【００１９】通路幅の縮小率（１−ｂｏ／ｂｉ）は、主
流域の流速の増大を伴うことなく低速領域が消滅する程
度に設定する。図２のＣ矢視図に相当する通路出口図で
ある図４中に低速領域（剥離部位）を示すように、略
０．２程度とすることで剥離抑制効果が最大となって最
も好ましく、それ以上では主流の流速が増大して効率が
低下する。尚、図中（Ａ）は縮小率：０．０５，（Ｂ）
は縮小率：０．１，（Ｃ）は縮小率：０．２の例であ
る。The reduction rate of the passage width (1-bo / bi) is set to such an extent that the low-speed region disappears without increasing the flow velocity in the main flow region. As shown in FIG. 4, which is a passage exit diagram corresponding to the view taken in the direction of arrow C in FIG. Above that, the flow velocity of the main stream increases and the efficiency decreases. In the figure, (A) shows the reduction ratio: 0.05, (B)
Is an example of a reduction ratio: 0.1, and (C) is an example of a reduction ratio: 0.2.
【００２０】上記のごとく、スロートより下流側の所定
位置から側壁内面２０Ｈを傾斜させて通路厚さを縮小さ
せることにより、案内羽根２１の圧力面２１Ａの後端近
傍での流体剥離を抑制することができ、ディフューザー
の全圧損失の増加を防いで効率を向上させることができ
る。また、スロート面積は縮小されることはないために
圧縮機の流量特性の変化を考慮する必要がなく、従来と
同様にして案内羽根形状を設定可能なものである。As described above, by inclining the inner wall surface 20H of the side wall from a predetermined position downstream of the throat to reduce the thickness of the passage, fluid separation near the rear end of the pressure surface 21A of the guide blade 21 is suppressed. Thus, the efficiency can be improved by preventing an increase in the total pressure loss of the diffuser. Further, since the throat area is not reduced, there is no need to consider changes in the flow rate characteristics of the compressor, and the guide blade shape can be set in the same manner as in the conventional case.
【００２１】尚、上記構成例は、通路厚さを縮小させる
ためにハブ側の側壁内面２０Ｈを傾斜させたものである
が、傾斜させる側壁内面はハブ側に限るものではなく、
シュラウド側であっても良く、ハブ側及びシュラウド側
の両側とも傾斜させても良いものである。In the above configuration example, the inner wall surface 20H on the hub side is inclined to reduce the thickness of the passage, but the inner wall surface to be inclined is not limited to the hub side.
The shroud side may be provided, and both sides of the hub side and the shroud side may be inclined.
【００２２】[0022]
【発明の効果】以上述べたように、本発明による遠心圧
縮機のディフューザーによれば、拡大通路を形成する回
転軸方向の少なくとも一方の側壁面が、スロート位置よ
り下流側の位置から通路厚さを縮小する側に所定角度で
傾斜形成されていることにより、案内羽根の圧力面後端
近傍での流体剥離を抑制することができ、ディフューザ
ーの全圧損失の増加を防いで効率を向上させることがで
きる。更に、スロート面積が縮小されることはないため
に圧縮機の流量特性の変化を考慮する必要がなく、従来
と同様にして案内羽根形状を設定可能なものである。As described above, according to the diffuser of the centrifugal compressor of the present invention, at least one side wall surface in the direction of the rotation axis forming the enlarged passage has a passage thickness from the position downstream of the throat position. Is formed at a predetermined angle on the side to reduce the pressure, so that fluid separation near the rear end of the pressure surface of the guide vanes can be suppressed, and the efficiency of the diffuser can be improved by preventing an increase in the total pressure loss of the diffuser. Can be. Further, since the throat area is not reduced, there is no need to consider changes in the flow rate characteristics of the compressor, and the shape of the guide vanes can be set as in the conventional case.
【図１】本発明に係る遠心圧縮機のディフューザーの一
構成例を適用した圧縮機のディフューザー部位の部分概
略断面図である。FIG. 1 is a partial schematic cross-sectional view of a diffuser part of a compressor to which a configuration example of a diffuser of a centrifugal compressor according to the present invention is applied.
【図２】図１のＡ−Ａ断面図である。FIG. 2 is a sectional view taken along line AA of FIG.
【図３】図２のＢ−Ｂ断面図である。FIG. 3 is a sectional view taken along line BB of FIG. 2;
【図４】図２のＣ矢視図に相当する通路出口の低速領域
を示し、（Ａ）は縮小率：０．０５，（Ｂ）は縮小率：
０．１，（Ｃ）は縮小率：０．２の例である。FIGS. 4A and 4B show a low speed region at the passage exit corresponding to a view taken in the direction of arrow C in FIG. 2, wherein FIG. 4A shows a reduction ratio: 0.05, and FIG.
0.1 and (C) are examples of a reduction ratio of 0.2.
【図５】従来例としての圧縮機のディフューザー部位の
部分概略断面図である。FIG. 5 is a partial schematic sectional view of a diffuser portion of a compressor as a conventional example.
【図６】図５のＤ−Ｄ断面図である。FIG. 6 is a sectional view taken along line DD of FIG. 5;
【図７】図６のＥ矢視図に相当する通路出口の低速領域
を示す図である。FIG. 7 is a view showing a low speed region at a passage exit corresponding to a view as seen from an arrow E in FIG. 6;
【図８】通路の厚さ方向における流出角分布を示す図で
ある。FIG. 8 is a diagram showing an outflow angle distribution in a thickness direction of a passage.
１ 圧縮機（遠心圧縮機） １０Ｈ ハブ側側壁 １０Ｓ シュラウド側側壁 ２０ ディフューザー ２０Ｈ ハブ側側壁内面（羽根車のハブ側と対応する側
壁面） ２０Ｓ シュラウド側側壁内面（側壁面） ２１ 案内羽根DESCRIPTION OF SYMBOLS 1 Compressor (centrifugal compressor) 10H Hub side wall 10S Shroud side wall 20 Diffuser 20H Hub side wall inner surface (side wall surface corresponding to the hub side of the impeller) 20S Shroud side wall inner surface (sidewall surface) 21 Guide blade
Claims (1)
大通路によって流体の運動エネルギーを圧力エネルギー
に変換するディフューザーであって、 拡大通路を形成する回転軸方向の少なくとも一方の側壁
面が、スロートより下流側の位置から通路厚さを縮小す
る側に傾斜形成されていることを特徴とする遠心圧縮機
のディフューザー。1. A centrifugal compressor, comprising: a diffuser for converting kinetic energy of a fluid into pressure energy by an enlarged passage formed by a guide blade, wherein at least one side wall surface in the direction of a rotation axis forming the enlarged passage is located downstream of the throat. A diffuser for a centrifugal compressor, characterized in that the diffuser is inclined from the side position to the side that reduces the thickness of the passage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP08298898A JP4174693B2 (en) | 1998-03-13 | 1998-03-13 | Centrifugal compressor diffuser |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP08298898A JP4174693B2 (en) | 1998-03-13 | 1998-03-13 | Centrifugal compressor diffuser |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH11257291A true JPH11257291A (en) | 1999-09-21 |
| JP4174693B2 JP4174693B2 (en) | 2008-11-05 |
Family
ID=13789610
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP08298898A Expired - Fee Related JP4174693B2 (en) | 1998-03-13 | 1998-03-13 | Centrifugal compressor diffuser |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP4174693B2 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008035465A1 (en) * | 2006-09-21 | 2008-03-27 | Mitsubishi Heavy Industries, Ltd. | Centrifugal compressor |
| KR101271090B1 (en) * | 2005-09-21 | 2013-06-04 | 삼성테크윈 주식회사 | Diffuser for turbo compressor |
| CN104214138A (en) * | 2013-06-04 | 2014-12-17 | 哈米尔顿森德斯特兰德公司 | Air compressor backing plate |
| CN104937219A (en) * | 2013-02-01 | 2015-09-23 | 博格华纳公司 | Elliptical compressor cover for turbocharger |
| WO2017090713A1 (en) * | 2015-11-26 | 2017-06-01 | 三菱重工業株式会社 | Stationary vane and centrifugal compressor provided with stationary vane |
-
1998
- 1998-03-13 JP JP08298898A patent/JP4174693B2/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101271090B1 (en) * | 2005-09-21 | 2013-06-04 | 삼성테크윈 주식회사 | Diffuser for turbo compressor |
| WO2008035465A1 (en) * | 2006-09-21 | 2008-03-27 | Mitsubishi Heavy Industries, Ltd. | Centrifugal compressor |
| CN104937219A (en) * | 2013-02-01 | 2015-09-23 | 博格华纳公司 | Elliptical compressor cover for turbocharger |
| CN104214138A (en) * | 2013-06-04 | 2014-12-17 | 哈米尔顿森德斯特兰德公司 | Air compressor backing plate |
| WO2017090713A1 (en) * | 2015-11-26 | 2017-06-01 | 三菱重工業株式会社 | Stationary vane and centrifugal compressor provided with stationary vane |
Also Published As
| Publication number | Publication date |
|---|---|
| JP4174693B2 (en) | 2008-11-05 |
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