JPH09329001A - Compressor blades - Google Patents
Compressor bladesInfo
- Publication number
- JPH09329001A JPH09329001A JP15089296A JP15089296A JPH09329001A JP H09329001 A JPH09329001 A JP H09329001A JP 15089296 A JP15089296 A JP 15089296A JP 15089296 A JP15089296 A JP 15089296A JP H09329001 A JPH09329001 A JP H09329001A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- platform
- shape
- compressor
- narrowed
- 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
- 239000000463 material Substances 0.000 claims description 4
- 230000001133 acceleration Effects 0.000 abstract description 10
- 230000006866 deterioration Effects 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 8
- 238000009826 distribution Methods 0.000 description 4
- 230000002411 adverse Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
(57)【要約】
【課題】 加減速によって翼の取り付け角に変化がな
く、性能の劣化を生じない圧縮機の動翼とする。
【解決手段】 翼１と、この翼１を固定する平板状のプ
ラットホーム３と、このプラットホーム３の下部に固定
されプラットホーム３と共にロータに埋め込まれる取付
部４とからなり、翼１は付け根部のコード長を絞った翼
形状を有し、プラットホーム３の平面形状はほぼ長方形
であり翼の付け根部はこのほぼ長方形のほぼ対角線上に
固定されている。
(57) [Abstract] [PROBLEMS] To provide a compressor rotor blade in which the blade mounting angle does not change due to acceleration / deceleration and does not cause performance deterioration. SOLUTION: The blade 1 includes a flat plate-shaped platform 3 for fixing the blade 1, and a mounting portion 4 fixed to a lower portion of the platform 3 and embedded in a rotor together with the platform 3, and the blade 1 has a cord at a base portion. It has a wing shape with a narrowed length, and the plane shape of the platform 3 is substantially rectangular, and the base of the wing is fixed substantially on the diagonal line of this substantially rectangular shape.
Description
【０００１】[0001]
【発明の属する技術分野】本発明はジェットエンジンや
ガスタービンなどに用いられる圧縮機の動翼に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a moving blade of a compressor used for jet engines, gas turbines and the like.
【０００２】[0002]
【従来の技術】従来ジェットエンジンやガスタービンで
は、空気を取り入れ圧縮機で圧縮し、燃焼器で圧縮した
空気により燃料を燃焼させ、燃焼ガスによりタービンを
駆動する。圧縮機は静翼と動翼が交互に配置された多段
の翼列から構成されている。2. Description of the Related Art In a conventional jet engine or gas turbine, air is taken in, compressed by a compressor, fuel is burned by the air compressed by a combustor, and the turbine is driven by the combustion gas. The compressor is composed of a multi-stage blade row in which stationary blades and moving blades are alternately arranged.
【０００３】翼列の空力性能は、ソリディティ（＝翼の
コード長／翼列間隔）に影響され、ソリディティが一定
であれば空力性能は変わらない。多段翼列の場合、他の
段の翼列との共振を回避するため、翼枚数を変更する場
合がある。このとき、翼枚数を減らすと翼列間隔が大き
くなるので空力性能（ソリディティ）を保持するため
に、翼のコード長を伸ばす必要がある。The aerodynamic performance of a blade cascade is influenced by the solidity (= the blade cord length / blade spacing), and if the solidity is constant, the aerodynamic performance does not change. In the case of a multi-stage blade row, the number of blades may be changed in order to avoid resonance with blade rows of other stages. At this time, if the number of blades is reduced, the blade spacing becomes large, so it is necessary to extend the cord length of the blades in order to maintain aerodynamic performance (solidity).
【０００４】図５は従来のコード長を伸ばした動翼の構
成を示す図である。図５（ａ）は側面図であり、１は翼
でこの場合コード長を大きくしている。２はダブテイル
（dovetail) と称し、木造建築などで２つの部材をつな
ぐとき、一方を鳩の尾状とし、他方を鳩の尾状の穴を有
する部材とするとき、この鳩の尾状の部材を英語でダブ
テイルといい、このつなぎ方をありつぎてという。ダブ
テイル２は翼１を固定する平面状のプラットホーム３
と、このプラットホーム３の下部に固定され鳩の尾状の
形状を有し、圧縮機のロータに設けられた鳩の尾状の穴
と嵌合する取付部４なる。FIG. 5 is a diagram showing the structure of a conventional moving blade having an extended cord length. FIG. 5 (a) is a side view, and 1 is a wing in which the cord length is increased. 2 is called a dovetail, and when connecting two members in a wooden construction, etc., when one is a dovetail-shaped member and the other is a member having a dovetail-shaped hole, this dovetail-shaped member Is called "Dovetail" in English, and this connection method is said to continue. The dovetail 2 is a flat platform 3 for fixing the wing 1.
The mounting portion 4 is fixed to the lower portion of the platform 3 and has a dovetail-like shape, and is fitted into a dovetail-like hole provided in the rotor of the compressor.
【０００５】図５（ｂ）は（ａ）のＸ−Ｘ矢視図で、翼
１とプラットホーム３の関係を示す。翼１のコード長が
長くないときは、プラットホーム３は図１（ｂ）に示す
ように長方形であるが、長くなるとプラットホーム３を
平行四辺形にして長さを吸収する形状としていた。な
お、ダブテイル２と取り合うロータの穴はプラットホー
ム３まで埋め込む構造となっている。FIG. 5B is a view taken along the line XX in FIG. 5A and shows the relationship between the wing 1 and the platform 3. When the cord length of the blade 1 is not long, the platform 3 is rectangular as shown in FIG. 1B, but when it becomes longer, the platform 3 is formed into a parallelogram to absorb the length. It should be noted that the hole of the rotor to be fitted with the dovetail 2 is structured to be embedded up to the platform 3.
【０００６】[0006]
【発明が解決しようとする課題】プラットホーム３が平
行四辺形の場合、圧縮機が定速度運転の場合はよいが、
加速や減速運転を行うと、プラットホーム３の平行四辺
形の斜面に沿ってプラットホーム３が歪み、これに伴い
翼１の取り付け角度が変わり、空力性能に悪影響が出て
くるという問題点があった。図６は圧縮機の加減速によ
る翼取り付け角の変化を示し、実線は変化前を示し、破
線は変化後を示す。５はプラットホーム３と嵌合する圧
縮機のロータの翼取付部を示す。なお、矢印はロータの
回転方向を示す。When the platform 3 is a parallelogram and the compressor operates at a constant speed, it is preferable.
When the acceleration or deceleration operation is performed, the platform 3 is distorted along the slope of the parallelogram of the platform 3, and the mounting angle of the blade 1 is changed accordingly, which adversely affects the aerodynamic performance. FIG. 6 shows a change in blade attachment angle due to acceleration / deceleration of the compressor, a solid line shows before change, and a broken line shows after change. Reference numeral 5 denotes a blade mounting portion of the rotor of the compressor that fits with the platform 3. The arrow indicates the rotation direction of the rotor.
【０００７】図７は平行四辺形プラットホームの歪みを
改良するプラットホームの図で、斜辺部に垂直部３ａ，
３ｂを設けたものである。これにより歪みはある程度少
なくなるが、プラットホーム３の形状が複雑になり製造
コストが高くなる。FIG. 7 is a diagram of a platform for improving the distortion of the parallelogram platform, in which the vertical portion 3a,
3b is provided. As a result, distortion is reduced to some extent, but the shape of the platform 3 is complicated and the manufacturing cost is increased.
【０００８】本発明は、上述の問題点に鑑みてなされた
もので、加減速によって翼の取り付け角に変化がなく、
性能の劣化を生じない圧縮機の動翼を提供することを目
的とする。The present invention has been made in view of the above problems, and there is no change in the mounting angle of the blade due to acceleration / deceleration,
It is an object of the present invention to provide a compressor blade that does not cause performance deterioration.
【０００９】[0009]
【課題を解決するための手段】上記目的を達成するため
請求項１の発明では、翼と、この翼を固定する平板状の
プラットホームと、このプラットホームの下部に固定さ
れプラットホームと共にロータに埋め込まれる取付部と
からなり、前記翼は付け根部のコード長を絞った翼形状
を有し、前記プラットホームの平面形状はほぼ長方形で
あり翼の付け根部はこのほぼ長方形のほぼ対角線上に固
定されている。In order to achieve the above object, according to the invention of claim 1, a blade, a plate-shaped platform for fixing the blade, and an attachment fixed to the lower part of the platform and embedded in the rotor together with the platform. The blade has a blade shape in which the cord length of the root portion is narrowed, the planar shape of the platform is substantially rectangular, and the blade root portion is fixed substantially diagonally of the substantially rectangular shape.
【００１０】翼のコード長が長くなっても付け根部のコ
ード長を絞って短くするので、プラットホームをほぼ長
方形とすることができる。これにより圧縮機の加減速時
プラットホームは歪まず翼の取り付け角も変わらない。
また翼の付け根部のみ絞るので、空力性能の劣化は殆ど
生じない。翼の付け根部は応力が大きくなるので、ここ
を絞ると応力は増大するが、解析の結果大きな増大はな
く応力上も問題はない。Even if the cord length of the blade becomes long, the cord length of the root portion is narrowed and shortened, so that the platform can be made substantially rectangular. As a result, the platform does not distort during acceleration / deceleration of the compressor, and the blade mounting angle does not change.
Further, since only the base of the blade is narrowed down, the aerodynamic performance is hardly deteriorated. Since the stress at the root of the blade becomes large, the stress will increase if this is narrowed down, but there is no significant increase as a result of the analysis, and there is no problem in terms of stress.
【００１１】請求項２の発明では、前記翼付け根部は前
縁および後縁を共に絞った形状となっている。In the invention of claim 2, the blade root portion has a shape in which both the leading edge and the trailing edge are narrowed.
【００１２】翼付け根部のコード長を絞る場合、前縁ま
たは後縁のいずれかを絞るよりも、前縁と後縁の両方を
絞った方が、空力性能および応力上から悪影響が少な
い。When the chord length of the blade root portion is narrowed, it is less adverse in terms of aerodynamic performance and stress when both the leading edge and the trailing edge are narrowed than when either the leading edge or the trailing edge is narrowed.
【００１３】請求項３の発明では、前記長方形は前記プ
ラットホームの材料固有の摩擦角以内の角度で平行四辺
形となっている。According to a third aspect of the present invention, the rectangle is a parallelogram at an angle within a friction angle peculiar to the material of the platform.
【００１４】平行四辺形は図２に示す角度θがプラット
ホームの材料固有の摩擦角以内であれば、加減速により
プラットホームが歪み翼の取付け角度が変化することは
ない。In the parallelogram, as long as the angle θ shown in FIG. 2 is within the friction angle peculiar to the material of the platform, the platform is distorted by acceleration and deceleration and the mounting angle of the blade is not changed.
【００１５】[0015]
【発明の実施の形態】以下、本発明の実施の形態につい
て図面を参照して説明する。図１は本発明の実施の形態
を説明する図で、（ａ）は動翼の側面図、（ｂ）は
（ａ）のＸ−Ｘ矢視図である。翼１は付け根のコード長
が前縁（Ｕ）および後縁（Ｖ）に示すように絞られてい
る。ダブテイル２は翼の付け根を固定する平板状のプラ
ットホーム３と、この下部に結合され鳩の尾状の形状を
有する取付部４からなる。なお、動翼を固定する圧縮機
のロータにはプラットホーム３と取付部４の形状の穴が
設けられ嵌合するようになっている。BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of the present invention will be described below with reference to the drawings. 1A and 1B are views for explaining an embodiment of the present invention, in which FIG. 1A is a side view of a moving blade, and FIG. 1B is a view taken along line XX of FIG. The blade 1 has the chord length of the root narrowed as shown in the leading edge (U) and the trailing edge (V). The dovetail 2 is composed of a flat plate-shaped platform 3 for fixing the base of the wing, and a mounting portion 4 connected to the lower part thereof and having a dovetail-like shape. In addition, the rotor of the compressor for fixing the moving blades is provided with a hole having the shape of the platform 3 and the mounting portion 4 for fitting.
【００１６】プラットホーム３は長方形であり、矢印で
示す圧縮機の回転方向に左右の辺は直交しているため、
回転の加減速によりプラットホーム３は歪まず、翼１の
取り付け角度も変化しない。また、翼１の付け根部のみ
コード長を絞っており、かつ、前縁と後縁の両方に絞り
を分散しているので、空力性能の劣化は少ない。Since the platform 3 is rectangular and the left and right sides are orthogonal to the rotation direction of the compressor indicated by the arrow,
The platform 3 does not distort due to the acceleration and deceleration of the rotation, and the mounting angle of the blade 1 does not change. Further, since the chord length is narrowed only at the root portion of the blade 1 and the throttling is distributed to both the leading edge and the trailing edge, deterioration of aerodynamic performance is small.
【００１７】プラットホーム３の形状は長方形である
が、この形状は図２に示すように、プラットホーム３の
材料によって決まる摩擦角以下の角度θであれば平行四
辺形となってもよい。これは摩擦角以内であれば、加減
速によりプラットホーム３が歪み翼の取付角が変化する
ことはないからである。また機械部品に一般的に行われ
る程度の角の鋭角部の切り落とし処理をした平行四辺形
も含まれる。The platform 3 has a rectangular shape, but as shown in FIG. 2, the shape may be a parallelogram as long as the angle θ is less than the friction angle determined by the material of the platform 3. This is because if the friction angle is within the range, the platform 3 is distorted due to acceleration / deceleration and the mounting angle of the blades does not change. It also includes a parallelogram obtained by cutting off the acute-angled portion of the degree that is generally used for mechanical parts.
【００１８】次に、翼１の付け根部の応力について説明
する。図３、図４は圧縮機の定格回転時の翼１の表面に
発生する応力を最大応力に対する比で表した相対応力分
布の計算値を示し、図３は翼上面の相対応力、図４は翼
下面の相対応力を示す。図中Ａ〜Ｉは相対応力の分布を
示し、各値は右のＡ〜Ｉの値で示される。単位はパーセ
ントである。また、Ｕ，Ｖは図１（ａ）に示す前縁、後
縁の絞り部を示す。絞り部Ｕ，Ｖにおける応力は小さ
く、加速、減速時この値が数倍となっても何ら問題とな
る値ではない。これにより、応力的には翼付け根部を絞
っても問題はない。Next, the stress at the base of the blade 1 will be described. 3 and 4 show calculated values of the relative stress distribution in which the stress generated on the surface of the blade 1 at the time of rated rotation of the compressor is expressed as a ratio to the maximum stress. FIG. 3 shows the relative stress on the blade upper surface, and FIG. The relative stress on the lower surface of the blade is shown. In the figure, A to I indicate the distribution of relative stress, and the respective values are indicated by the values on the right A to I. The unit is percentage. Further, U and V indicate the narrowed portions at the front edge and the rear edge shown in FIG. The stress in the narrowed portions U and V is small, and this value does not cause any problem even if this value becomes several times during acceleration and deceleration. Therefore, there is no problem in terms of stress even if the root portion of the blade is narrowed.
【００１９】[0019]
【発明の効果】以上の説明より明らかなように、本発明
は、翼のコード長を長くする場合、付け根部のみ絞り、
翼を固定するプラットホームをほぼ長方形にするので、
加減速時にプラットホームに歪みが発生せず、翼の取り
付け角の変化はない。また、空力性能の劣化や大きな応
力の発生もない。As is apparent from the above description, according to the present invention, when the cord length of the blade is increased, only the root portion is narrowed,
Since the platform for fixing the wings is almost rectangular,
No distortion occurs on the platform during acceleration / deceleration, and there is no change in the blade mounting angle. Further, there is no deterioration of aerodynamic performance or generation of large stress.
【図１】本発明の実施の形態を説明する図で、（ａ）は
動翼の側面図、（ｂ）は（ａ）のＸ−Ｘ矢視図である。1A and 1B are diagrams illustrating an embodiment of the present invention, in which FIG. 1A is a side view of a moving blade, and FIG. 1B is a view taken along line XX of FIG.
【図２】プラットホームの形状と摩擦角の関係を示す図
である。FIG. 2 is a diagram showing a relationship between a platform shape and a friction angle.
【図３】動翼の上面の定格回転時の相対応力分布を示す
図である。FIG. 3 is a diagram showing a relative stress distribution at the time of rated rotation of the upper surface of the moving blade.
【図４】動翼の下面の定格回転時の相対応力分布を示す
図である。FIG. 4 is a diagram showing a relative stress distribution of the lower surface of the moving blade during rated rotation.
【図５】従来の動翼の構成を説明する図で、（ａ）は動
翼の側面図、（ｂ）は（ａ）のＸ−Ｘ矢視図である。5A and 5B are diagrams illustrating a configuration of a conventional moving blade, in which FIG. 5A is a side view of the moving blade, and FIG. 5B is a view taken along line XX of FIG.
【図６】平行四辺形プラットホームを用いた場合の翼の
取り付け角の変化を示す図である。FIG. 6 is a diagram showing a change in a mounting angle of a wing when a parallelogram platform is used.
【図７】平行四辺形プラットホームを改良した形状を示
す図である。FIG. 7 is a view showing an improved shape of the parallelogram platform.
１ 翼 ２ ダブテイル ３ ブラットホーム ４ 取付部 ５ ロータの翼取付部 1 wing 2 dovetail 3 platform 4 mounting part 5 rotor wing mounting part
Claims (3)
トホームと、このプラットホームの下部に固定されプラ
ットホームと共にロータに埋め込まれる取付部とからな
り、前記翼は付け根部のコード長を絞った翼形状を有
し、前記プラットホームの平面形状はほぼ長方形であり
翼の付け根部はこのほぼ長方形のほぼ対角線上に固定さ
れていることを特徴とする圧縮機の動翼。1. A blade comprising a blade, a plate-shaped platform for fixing the blade, and a mounting portion fixed to a lower portion of the platform and embedded in a rotor together with the platform, the blade having a reduced cord length at a root portion. A moving blade of a compressor, which has a shape, and a planar shape of the platform is substantially rectangular, and a root portion of the blade is fixed substantially diagonally of the substantially rectangular shape.
絞った形状となっていることを特徴とする請求項１記載
の圧縮機の動翼。2. The moving blade of a compressor according to claim 1, wherein the blade root has a shape in which both the leading edge and the trailing edge are narrowed.
固有の摩擦角以内の角度で平行四辺形となっていること
を特徴とする請求項１記載の圧縮機の動翼。3. The moving blade of a compressor according to claim 1, wherein the rectangle is a parallelogram at an angle within a friction angle peculiar to a material of the platform.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP15089296A JPH09329001A (en) | 1996-06-12 | 1996-06-12 | Compressor blades |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP15089296A JPH09329001A (en) | 1996-06-12 | 1996-06-12 | Compressor blades |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH09329001A true JPH09329001A (en) | 1997-12-22 |
Family
ID=15506667
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP15089296A Pending JPH09329001A (en) | 1996-06-12 | 1996-06-12 | Compressor blades |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH09329001A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011127441A (en) * | 2009-12-15 | 2011-06-30 | Ihi Corp | Blade structure and blade ring |
| CN102562665A (en) * | 2010-12-28 | 2012-07-11 | 株式会社日立制作所 | Axial compressor |
| CN106917775A (en) * | 2017-05-11 | 2017-07-04 | 江苏斯别特制泵有限公司 | A kind of high-power submerged axial-flow pump impeller |
| WO2025091319A1 (en) * | 2023-11-01 | 2025-05-08 | 温岭正峰数字机电科技有限公司 | Axial flow pump and guide vane structure of impeller of axial flow pump |
-
1996
- 1996-06-12 JP JP15089296A patent/JPH09329001A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011127441A (en) * | 2009-12-15 | 2011-06-30 | Ihi Corp | Blade structure and blade ring |
| CN102562665A (en) * | 2010-12-28 | 2012-07-11 | 株式会社日立制作所 | Axial compressor |
| JP2012137072A (en) * | 2010-12-28 | 2012-07-19 | Hitachi Ltd | Axial compressor |
| CN106917775A (en) * | 2017-05-11 | 2017-07-04 | 江苏斯别特制泵有限公司 | A kind of high-power submerged axial-flow pump impeller |
| WO2025091319A1 (en) * | 2023-11-01 | 2025-05-08 | 温岭正峰数字机电科技有限公司 | Axial flow pump and guide vane structure of impeller of axial flow pump |
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