JPH0727095A - Stationary blade for axial flow compressor - Google Patents
Stationary blade for axial flow compressorInfo
- Publication number
- JPH0727095A JPH0727095A JP16696893A JP16696893A JPH0727095A JP H0727095 A JPH0727095 A JP H0727095A JP 16696893 A JP16696893 A JP 16696893A JP 16696893 A JP16696893 A JP 16696893A JP H0727095 A JPH0727095 A JP H0727095A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- vicinity
- hub
- side end
- stationary blade
- 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
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は軸流圧縮機の静翼に関す
るものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a stationary blade of an axial compressor.
【０００２】[0002]
【従来の技術】図８は従来の軸流圧縮機の静翼取付部分
の一例を示すもので、１は略筒状のケーシング壁、２は
略環状のハブ壁であり、該ハブ壁２はケーシング壁１の
内径よりも小さい外径を有し且つケーシング壁１の内部
に略同軸に配置されている。2. Description of the Related Art FIG. 8 shows an example of a stationary blade mounting portion of a conventional axial flow compressor, wherein 1 is a substantially cylindrical casing wall, 2 is a substantially annular hub wall, and the hub wall 2 is It has an outer diameter smaller than the inner diameter of the casing wall 1 and is arranged substantially coaxially inside the casing wall 1.
【０００３】３は静翼であり、該静翼３は、ハブ側端部
４が前記のハブ壁２と対峙するようにケーシング壁１と
ハブ壁２とにより囲まれる環状空間に周方向に略等間隔
に配置され且つチップ側端部５がケーシング壁１に支持
されている。Reference numeral 3 is a stationary blade, and the stationary blade 3 is substantially circumferentially formed in an annular space surrounded by the casing wall 1 and the hub wall 2 so that the hub side end portion 4 faces the hub wall 2. The chip-side ends 5 are arranged at equal intervals and are supported by the casing wall 1.
【０００４】前記の静翼３は、図２、図４、図９に示す
ように一側面に前縁６から後縁７に連なる凸面形状の背
面８を有し且つ他側面に前縁６から後縁７に連なる腹面
９を有している。As shown in FIGS. 2, 4 and 9, the vane 3 has a convex back surface 8 extending from the leading edge 6 to the trailing edge 7 on one side and from the leading edge 6 on the other side. It has a ventral surface 9 continuous with the trailing edge 7.
【０００５】図９において、１１は翼弦線を表し、該翼
弦線１１は、前記の前縁６と後縁７とを結ぶ直線であ
り、この翼弦線１１の長さを静翼３の弦長ｃとしてい
る。In FIG. 9, reference numeral 11 denotes a chord line, and the chord line 11 is a straight line connecting the leading edge 6 and the trailing edge 7, and the length of the chord line 11 is the vane 3 The string length c is
【０００６】１２は反り線（翼中心線）を表し、該反り
線１２は、前記の背面８と腹面９とに内接する円群１３
の中心を結ぶ曲線である。Reference numeral 12 denotes a warp line (blade center line), and the warp line 12 is a group of circles 13 inscribed in the back surface 8 and the abdominal surface 9.
Is a curve connecting the centers of.
【０００７】前記の反り線１２の接線に直交する垂線の
背面交差部から腹面交差部までの長さが翼厚であり、前
記の翼弦線１１の延長方向の翼厚の変化が静翼３の翼厚
分布となる。The length from the back intersection to the abdominal intersection of the perpendicular line orthogonal to the tangent of the warp line 12 is the blade thickness, and the change in the blade thickness in the extension direction of the chord line 11 is the vane 3. The wing thickness distribution is.
【０００８】また、Ｔmaxは最大翼厚を表している。Further, Tmax represents the maximum blade thickness.
【０００９】従来の軸流圧縮機に用いられる静翼３で
は、スパン方向（図８においてハブ側端部４からチップ
側端部５へ向う方向）のいずれの翼断面においても、反
り線１２の形状が略同等に形成され、且つ最大翼厚部分
も翼弦線１１の延長方向の略同じ部分に位置するように
形成されている。In the vane 3 used in the conventional axial compressor, the warp line 12 is formed in any blade cross section in the span direction (the direction from the hub side end 4 to the tip side end 5 in FIG. 8). The shapes are formed to be substantially the same, and the maximum blade thickness portion is also formed so as to be located in substantially the same portion in the extension direction of the chord line 11.
【００１０】このような静翼３では、腹面９に対して背
面８の曲率が大きいので、静翼３に沿って前縁側Ｌから
後縁側Ｔへ流れる空気の速度は、背面側Ｂのほうが腹面
側Ｆに比べて高くなって腹面側Ｆより背面側Ｂの静圧が
低くなる。In such a vane 3, since the back surface 8 has a larger curvature than the ventral surface 9, the velocity of the air flowing along the vane 3 from the leading edge side L to the trailing edge side T is such that the back side B is the abdominal surface. It becomes higher than that on the side F, and the static pressure on the back side B becomes lower than that on the abdominal side F.
【００１１】[0011]
【発明が解決しようとする課題】ところが、静翼３の背
面側Ｂにおいて前縁側Ｌから後縁側Ｔへ向って流れる空
気の減速の割合が大きく翼面負荷が高い場合には、静翼
３のハブ側端部４並びにチップ側端部５付近において、
ハブ壁２とケーシング壁１との境界層の干渉により、背
面側Ｂにおいて境界層の剥離が生じやすくなり、図７に
一点鎖線で示すように静翼３の背面側Ｂのハブ側端部４
並びにチップ側端部５付近における圧力損失がスパン方
向中心部付近に比べて高くなる傾向を呈する。However, when the deceleration rate of the air flowing from the leading edge side L to the trailing edge side T on the rear surface side B of the stationary blade 3 is large and the blade surface load is high, the stationary blade 3 In the vicinity of the hub side end 4 and the tip side end 5,
Due to the interference of the boundary layer between the hub wall 2 and the casing wall 1, separation of the boundary layer is likely to occur on the back surface side B, and as shown by the alternate long and short dash line in FIG.
In addition, the pressure loss in the vicinity of the tip side end portion 5 tends to be higher than that in the vicinity of the center portion in the span direction.
【００１２】本発明は軸流圧縮機の静翼のハブ側端部並
びにチップ側端部付近における圧力損失を低くすること
を目的としている。An object of the present invention is to reduce the pressure loss in the vicinity of the end on the hub side and the end on the tip side of the stationary blade of the axial flow compressor.
【００１３】[0013]
【課題を解決するための手段】上記目的を達成するた
め、本発明の軸流圧縮機の静翼では、一側面に前縁から
後縁に連なる背面を有し且つ他側面に前縁から後縁に連
なる腹面を有する軸流圧縮機の静翼において、スパン方
向中央部付近の翼断面における反り線の形状を翼弦長前
半部で大きな反りとなるように形成するとともに、スパ
ン方向中央部付近の翼断面における最大翼厚部分を翼弦
長前半部に位置させ、且つハブ側端部並びにチップ側端
部付近の翼断面における反り線の形状を翼弦長後半部で
大きな反りとなるように形成するとともに、ハブ側端部
並びにチップ側端部付近の翼断面における最大翼厚部分
をスパン方向中央部付近における最大翼厚部分よりも後
縁側に位置させている。In order to achieve the above object, in a stator blade of an axial compressor according to the present invention, one side surface has a back surface extending from a leading edge to a trailing edge, and the other side surface has a leading edge to a trailing edge. In a stationary blade of an axial flow compressor having a belly surface continuous to the edge, the shape of the warp line in the blade cross section near the center part in the span direction is formed to have a large warp in the first half of the chord length, and near the center part in the span direction. The maximum blade thickness in the blade cross section of the blade is located in the first half of the chord length, and the shape of the warp line in the blade cross section near the hub end and the tip end is large in the latter half of the chord length. While being formed, the maximum blade thickness portion in the blade cross section near the hub side end portion and the tip side end portion is located on the trailing edge side of the maximum blade thickness portion near the span direction central portion.
【００１４】[0014]
【作用】静翼の背面側のハブ側端部並びにチップ側端部
付近の翼断面において、反り線の形状を翼弦長後半部で
大きな反りとなるように形成し、更に最大翼厚部分をス
パン方向中央部付近における最大翼厚部分よりも後縁側
に位置させているので、スパン方向中央部付近に比べて
前縁近傍における空気の流速が低くなり、静翼の翼弦長
前半部での翼面負荷も軽減される傾向を呈する。[Function] In the blade cross section near the end on the hub side and the end on the tip side of the back surface of the stationary blade, the shape of the warp line is formed so as to have a large warp in the latter half of the chord length, and the maximum blade thickness portion is further increased. Since it is located on the trailing edge side of the maximum blade thickness near the center of the span direction, the air flow velocity near the leading edge is lower than that near the center of the span direction. The wing load also tends to be reduced.
【００１５】このため、背面側の前縁近傍における静圧
は、ハブ側端部並びにチップ側端部付近に比べてスパン
方向中央部付近の方が低くなり、翼面境界層が背面側の
ハブ側端部並びにチップ側端部付近からスパン方向中央
部付近に移動する。Therefore, the static pressure in the vicinity of the front edge on the rear surface side is lower in the vicinity of the central portion in the span direction than in the vicinity of the end portion on the hub side and the end portion on the tip side, and the blade boundary layer is the hub on the rear surface side. It moves from the side edge and near the chip side edge to near the center in the span direction.
【００１６】よって、静翼の背面側のハブ側端部並びに
チップ側端部付近において、翼面並びに壁面境界層の剥
離が抑えられ、静翼の背面側のハブ側端部並びにチップ
側端部付近における圧力損失が低減される。Therefore, in the vicinity of the hub-side end and the tip-side end on the back side of the vane, separation of the blade surface and the wall boundary layer is suppressed, and the hub-side end and tip-side end of the vane on the back side. The pressure loss in the vicinity is reduced.
【００１７】[0017]
【実施例】以下本発明の実施例を図面を参照しつつ説明
する。Embodiments of the present invention will be described below with reference to the drawings.
【００１８】図１は本発明の軸流圧縮機の静翼の一実施
例を示すもので、図２、図４、図９と同一の符号を付し
た部分は同一物を表している。FIG. 1 shows an embodiment of a stationary blade of an axial flow compressor according to the present invention, and the parts designated by the same reference numerals as those in FIGS. 2, 4 and 9 represent the same parts.
【００１９】本実施例では、一側面に前縁６から後縁７
に連なる背面８を有し且つ他側面に前縁６から後縁７に
連なる腹面９を有する静翼１０において、スパン方向中
央部付近の翼断面における反り線１２の形状を翼弦長前
半部で大きな反りとなるように形成するとともに、スパ
ン方向中央部付近の翼断面における最大翼厚Ｔmaxを翼
弦長前半部に位置させ、且つハブ側端部並びにチップ側
端部付近の翼断面における反り線１２の形状を翼弦長後
半部で大きな反りとなるように形成するとともに、ハブ
側端部並びにチップ側端部付近の翼断面における最大翼
厚Ｔmaxをスパン方向中央部付近における最大翼厚部分
よりも後縁側Ｔに位置させている。In this embodiment, the leading edge 6 to the trailing edge 7 are provided on one side surface.
In a stationary blade 10 having a back surface 8 continuous with the front edge 6 and a ventral surface 9 continuous with the trailing edge 7 on the other side, the shape of the warp line 12 in the blade cross section near the central portion in the span direction is measured in the first half of the chord length. In addition to forming a large warp, the maximum blade thickness Tmax in the blade cross section near the center in the span direction is located in the first half of the chord length, and the warp line in the blade cross section near the hub side end and the tip side end. The shape of No. 12 is formed so as to have a large warp in the latter half of the chord length, and the maximum blade thickness Tmax in the blade cross section near the hub side end and the tip side end is calculated from the maximum blade thickness part near the center in the span direction. Is also located on the trailing edge side T.
【００２０】上記構成を有する静翼１０に沿って前縁側
Ｌから後縁側Ｔへ向う空気の流れる空気の速度は、背面
側Ｂのスパン方向中央部付近の翼断面では、図２に示す
ように前縁６近傍において空気の速度が最大となり静翼
１０の翼弦長前半部での翼面負荷が高くなる傾向を呈す
る。The velocity of the air flowing from the leading edge side L to the trailing edge side T along the vane 10 having the above-described structure is as shown in FIG. 2 in the blade cross section near the center of the back side B in the span direction. The velocity of the air becomes maximum near the leading edge 6, and the blade surface load in the first half of the chord length of the stationary blade 10 tends to increase.
【００２１】一方、静翼１０のハブ側端部並びにチップ
側端部付近の付近の翼断面では、反り線１２の形状を翼
弦長後半部で大きな反りとなるように形成し、更に最大
翼厚Ｔmaxをスパン方向中央部付近における最大翼厚Ｔm
axよりも後縁側Ｔに位置させているので、スパン方向中
央部付近に比べて前縁近傍における空気の流速が低くな
り、静翼１０の翼弦長前半部での翼面負荷も軽減される
傾向を呈する。On the other hand, in the blade cross section near the end on the hub side and the end on the tip side of the stationary blade 10, the shape of the warp line 12 is formed so as to have a large warp in the latter half of the chord length, and further, the maximum blade. The thickness Tmax is the maximum blade thickness Tm near the center in the span direction
Since it is located on the trailing edge side T with respect to ax, the flow velocity of air in the vicinity of the leading edge is lower than in the vicinity of the central portion in the span direction, and the blade surface load in the first half of the chord length of the stationary blade 10 is also reduced. Exhibit a tendency.
【００２２】このため、背面側Ｂの前縁６近傍における
静圧は、図４、図５に示すようにハブ側端部並びにチッ
プ側端部付近に比べてスパン方向中央部付近の方が低く
なり、静翼１０の背面側Ｂにおいては、図６に示すよう
なスパン方向中央部付近に向って低くなる静圧分布が形
成され、翼面境界層が背面側Ｂのハブ側端部並びにチッ
プ側端部付近からスパン方向中央部付近に移動する。Therefore, the static pressure in the vicinity of the front edge 6 on the back side B is lower near the central portion in the span direction than in the vicinity of the hub-side end portion and the tip-side end portion as shown in FIGS. Therefore, on the back surface side B of the stationary blade 10, a static pressure distribution that decreases toward the central portion in the span direction as shown in FIG. 6 is formed, and the blade surface boundary layer has the hub side end portion of the back surface side B and the tip. It moves from near the side edge to near the center in the span direction.
【００２３】よって、静翼１０の背面側Ｂのハブ側端部
並びにチップ側端部付近において境界層の剥離が抑えら
れ、図７に実線で示すように静翼１０の背面側Ｂのハブ
側端部並びにチップ側端部付近における圧力損失が低減
される。Therefore, separation of the boundary layer is suppressed in the vicinity of the end on the hub side and the end on the tip side on the back surface side B of the stationary blade 10, and as shown by the solid line in FIG. The pressure loss near the end portion and the tip side end portion is reduced.
【００２４】このように、本実施例においては静翼１０
の背面側Ｂのハブ側端部並びにチップ側端部付近におけ
る圧力損失が低くなるので、軸流圧縮機の圧縮効率を向
上させることが可能となる。As described above, in the present embodiment, the stationary blade 10
Since the pressure loss near the end on the hub side and the end on the tip side on the back side B becomes low, it is possible to improve the compression efficiency of the axial flow compressor.
【００２５】なお、本発明の軸流圧縮機の静翼は、上述
した実施例のみに限定されるものではなく、本発明の要
旨を逸脱しない範囲内において種々変更を加え得ること
は勿論である。The stator vane of the axial flow compressor of the present invention is not limited to the above-mentioned embodiments, and it goes without saying that various modifications can be made without departing from the gist of the present invention. .
【００２６】[0026]
【発明の効果】以上述べたように、本発明の軸流圧縮機
の静翼によれば、下記のような種々の優れた効果を奏し
得る。As described above, according to the stationary blade of the axial flow compressor of the present invention, various excellent effects as described below can be obtained.
【００２７】（１）静翼のハブ側端部並びにチップ側端
部付近の翼断面において、反り線の形状を翼弦長後半部
で大きな反りとなるように形成し、更に最大翼厚部分を
スパン方向中央部付近における最大翼厚部分よりも後縁
側に位置させているので、翼面境界層が背面側のハブ側
端部並びにチップ側端部付近からスパン方向中央部付近
に移動し、静翼の背面側のハブ側端部並びにチップ側端
部付近における圧力損失が低減される。(1) In the blade cross section near the hub side end and the tip side end of the stationary blade, the shape of the warp line is formed so as to have a large warp in the latter half of the chord length, and the maximum blade thickness part is further formed. Since it is located on the trailing edge side of the maximum blade thickness near the center in the span direction, the blade boundary layer moves from the hub side end on the back side and near the tip side end to the center in the span direction, Pressure loss in the vicinity of the end on the hub side and the end on the tip side on the back side of the blade is reduced.
【００２８】（２）ハブ側端部並びにチップ側端部付近
における圧力損失が低減されるので、軸流圧縮機の圧縮
効率を向上させることが可能となる。(2) Since the pressure loss near the end on the hub side and the end on the tip side is reduced, the compression efficiency of the axial flow compressor can be improved.
【図１】本発明の軸流圧縮機の静翼の一実施例のスパン
方向の各断面の形状を示す翼体線図である。FIG. 1 is a blade body diagram showing the shape of each cross section in the span direction of an embodiment of a stationary blade of an axial flow compressor of the present invention.
【図２】反り線の形状を翼弦長前半部で大きな反りとな
るように形成するとともに最大翼厚部分を翼弦長前半部
に位置させた翼体線形を有する静翼断面の速度分布図で
ある。FIG. 2 is a velocity distribution diagram of a stator blade cross section having a blade line shape in which the shape of the warp line is formed so as to have a large warp in the first half of the chord length and the maximum blade thickness portion is located in the first half of the chord length. Is.
【図３】反り線の形状を翼弦長後半部で大きな反りとな
るように形成するとともに最大翼厚部分を後縁側へ移動
させた翼体線形を有する静翼断面の速度分布図である。FIG. 3 is a velocity distribution diagram of a stator blade cross section having a blade line shape in which the shape of the warp line is formed to have a large warp in the latter half of the chord length and the maximum blade thickness portion is moved to the trailing edge side.
【図４】反り線の形状を翼弦長前半部で大きな反りとな
るように形成するとともに最大翼厚部分を翼弦長前半部
に位置させた翼体線形を有する静翼断面の静圧分布図で
ある。[Fig. 4] Static pressure distribution in a static blade cross section having a blade line shape in which the shape of the warp line is formed to have a large warp in the first half of the chord length and the maximum blade thickness portion is located in the first half of the chord length. It is a figure.
【図５】反り線の形状を翼弦長後半部で大きな反りとな
るように形成するとともに最大翼厚部分を後縁側へ移動
させた翼体線形を有する静翼断面の静圧分布図である。FIG. 5 is a static pressure distribution diagram of a cross section of a stationary blade having a blade line shape in which the shape of the warp line is formed to have a large warp in the latter half of the chord length and the maximum blade thickness portion is moved to the trailing edge side. .
【図６】本発明の軸流圧縮機の静翼の一実施例における
背面側の静圧分布図である。FIG. 6 is a static pressure distribution diagram on the back side in one embodiment of the stationary blade of the axial compressor of the present invention.
【図７】本発明の軸流圧縮機の静翼の一実施例と従来の
静翼の一例のスパン方向の圧力損失分布図である。FIG. 7 is a spanwise pressure loss distribution chart of an example of a stationary blade of an axial flow compressor according to the present invention and an example of a conventional stationary blade.
【図８】従来の軸流圧縮機の静翼取付部分の一例を示す
概略図である。FIG. 8 is a schematic view showing an example of a stationary blade mounting portion of a conventional axial flow compressor.
【図９】従来の軸流圧縮機の静翼の一例における断面形
状を示す概略図である。FIG. 9 is a schematic view showing a cross-sectional shape of an example of a stationary blade of a conventional axial flow compressor.
６ 前縁 ７ 後縁 ８ 背面 ９ 腹面 １０ 静翼 １２ 反り線 Ｔ 後縁側 Ｔmax 最大翼厚 6 Leading edge 7 Trailing edge 8 Back surface 9 Ventral surface 10 Stator blade 12 Warp line T Trailing edge side Tmax Maximum blade thickness
Claims (1)
し且つ他側面に前縁から後縁に連なる腹面を有する軸流
圧縮機の静翼において、スパン方向中央部付近の翼断面
における反り線の形状を翼弦長前半部で大きな反りとな
るように形成するとともに、スパン方向中央部付近の翼
断面における最大翼厚部分を翼弦長前半部に位置させ、
且つハブ側端部並びにチップ側端部付近の翼断面におけ
る反り線の形状を翼弦長後半部で大きな反りとなるよう
に形成するとともに、ハブ側端部並びにチップ側端部付
近の翼断面における最大翼厚部分をスパン方向中央部付
近における最大翼厚部分よりも後縁側に位置させたこと
を特徴とする軸流圧縮機の静翼。1. A vane section of an axial compressor having a back surface extending from a leading edge to a trailing edge on one side surface and a ventral surface extending from a leading edge to a trailing edge on the other side surface, in the vicinity of a central portion in the span direction. In addition to forming the shape of the warp line in the first half of the chord length to have a large warp, the maximum blade thickness part in the blade cross section near the center part in the span direction is located in the first half of the chord length.
In addition, the shape of the warp line in the blade cross section near the hub side end and the tip side end is formed so as to have a large warp in the latter half of the chord length, and in the blade cross section near the hub side end and the tip side end. A stator blade for an axial flow compressor, characterized in that the maximum blade thickness portion is located closer to the trailing edge than the maximum blade thickness portion near the center in the span direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP16696893A JP3186349B2 (en) | 1993-07-06 | 1993-07-06 | Axial compressor vane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP16696893A JP3186349B2 (en) | 1993-07-06 | 1993-07-06 | Axial compressor vane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0727095A true JPH0727095A (en) | 1995-01-27 |
| JP3186349B2 JP3186349B2 (en) | 2001-07-11 |
Family
ID=15840962
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP16696893A Expired - Fee Related JP3186349B2 (en) | 1993-07-06 | 1993-07-06 | Axial compressor vane |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3186349B2 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002520993A (en) * | 1998-07-20 | 2002-07-09 | エヌエムビー（ユーエスエイ）・インコーポレイテッド | Axial fan |
| DE19909748C2 (en) * | 1999-03-05 | 2003-03-27 | Valeo Klimasysteme Gmbh | fan |
| CN103758791A (en) * | 2014-02-17 | 2014-04-30 | 南通大通宝富风机有限公司 | Circling kinetic energy recovery guide vane of cooling fan of control rod drive mechanism |
| CN106287959A (en) * | 2016-08-17 | 2017-01-04 | 芜湖美智空调设备有限公司 | Stator blade wind wheel, cabinet air-conditioner and air-conditioner |
| CN106704265A (en) * | 2016-11-11 | 2017-05-24 | 珠海格力电器股份有限公司 | Diffuser, diffuser mounting structure, mechanical device and refrigeration equipment |
-
1993
- 1993-07-06 JP JP16696893A patent/JP3186349B2/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002520993A (en) * | 1998-07-20 | 2002-07-09 | エヌエムビー（ユーエスエイ）・インコーポレイテッド | Axial fan |
| JP4796691B2 (en) * | 1998-07-20 | 2011-10-19 | ミネベア株式会社 | Axial fan |
| DE19909748C2 (en) * | 1999-03-05 | 2003-03-27 | Valeo Klimasysteme Gmbh | fan |
| CN103758791A (en) * | 2014-02-17 | 2014-04-30 | 南通大通宝富风机有限公司 | Circling kinetic energy recovery guide vane of cooling fan of control rod drive mechanism |
| CN106287959A (en) * | 2016-08-17 | 2017-01-04 | 芜湖美智空调设备有限公司 | Stator blade wind wheel, cabinet air-conditioner and air-conditioner |
| CN106287959B (en) * | 2016-08-17 | 2022-03-22 | 芜湖美智空调设备有限公司 | Quiet leaf wind wheel, cabinet air conditioner and air conditioner |
| CN106704265A (en) * | 2016-11-11 | 2017-05-24 | 珠海格力电器股份有限公司 | Diffuser, diffuser mounting structure, mechanical device and refrigeration equipment |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3186349B2 (en) | 2001-07-11 |
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