JPH0660701U - Integrated wing wheel - Google Patents
Integrated wing wheelInfo
- Publication number
- JPH0660701U JPH0660701U JP700893U JP700893U JPH0660701U JP H0660701 U JPH0660701 U JP H0660701U JP 700893 U JP700893 U JP 700893U JP 700893 U JP700893 U JP 700893U JP H0660701 U JPH0660701 U JP H0660701U
- Authority
- JP
- Japan
- Prior art keywords
- disk
- outer peripheral
- peripheral surface
- blade
- blade root
- 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
Abstract
(57)【要約】
【構成】 ディスク9と該ディスク9の外周面に略等間
隔に設けた動翼10とを一体的に形成した一体形翼車に
おいて、ディスク外周面前縁12を各動翼10の翼根部
前端13に且つディスク外周面後縁14を各動翼10の
翼根部後端15に位置させ、ディスク外周面前縁12か
らディスク前端面16になだらかに連なりディスク径方
向の断面が凹曲線形状を有する前部環状湾曲面17並び
に前記のディスク外周面後縁14からディスク後端面1
8になだらかに連なりディスク径方向の断面が凹曲線形
状を有する後部環状湾曲面19を設ける。
【効果】 前部環状湾曲面並びに後部環状湾曲面を設け
ることによって、動翼の翼根部前端並びに翼根部後端に
生じる応力集中が抑制される。
(57) [Summary] [Construction] In an integrated vane wheel in which a disk 9 and moving blades 10 provided at substantially equal intervals on the outer peripheral surface of the disk 9 are integrally formed, a disk outer peripheral surface leading edge 12 is provided for each moving blade. 10 is located at the blade root front end 13 and the disk outer peripheral surface trailing edge 14 is located at the blade root rear end 15 of each moving blade 10, and the disk outer diameter concave section is gently connected from the disk outer peripheral surface front edge 12 to the disk front end surface 16. From the front annular curved surface 17 having a curved shape and the disk outer peripheral surface rear edge 14 to the disk rear end surface 1
8 is provided with a rear annular curved surface 19 which is gently continuous and has a concave curved shape in the cross section in the disk radial direction. [Effect] By providing the front annular curved surface and the rear annular curved surface, stress concentration occurring at the blade root front end and the blade root rear end of the moving blade is suppressed.
Description
【0001】[0001]
本考案は一体型翼車に関するものである。 The present invention relates to an integrated impeller.
【0002】[0002]
ジェットエンジンなどの軸流圧縮機や軸流タービンに用いられている翼車には 、環状のディスクのディスクの外周部に削設した動翼植え込み溝に、動翼の基端 部に形成したダブテイルを嵌め込む組立型翼車の他に、動翼とディスクとを一体 的に形成した一体型翼車がある。 For impellers used in axial compressors and turbines of jet engines and the like, dovetails formed at the base end of the rotor blade are installed in the rotor blade embedding groove cut in the outer peripheral portion of the disk of the annular disc. In addition to the assembly type impeller in which the blades are fitted, there is an integral type impeller in which the rotor blade and the disk are integrally formed.
【0003】 一体型翼車を製作する手段としては、特公平1−222820号公報等に開示 されている電解加工法がある。As a means for manufacturing an integral type impeller, there is an electrolytic processing method disclosed in Japanese Patent Publication No. 1-222820.
【0004】 電解加工法による一体型翼車の製作においては、図4に示すように、形成すべ き動翼の腹面並びに背面に合致する翼成形面を有する工具1を陰極とし、また、 一体型翼車となるべき環状の金属素材2を陽極として、工具1より電解液aを噴 出させながら工具1を金属素材2に接近させるともに、前記の両電極間に電流を 導通させ、工具1と金属素材2との間において大電流密度で放電加工を行うこと よって図4から図6に示すように動翼3を形成させている。In the production of the integral impeller by the electrolytic processing method, as shown in FIG. 4, the tool 1 having a blade forming surface that matches the ventral surface and the back surface of the moving blade to be formed is used as the cathode, and the integral type impeller is used. Using the annular metal material 2 to be an impeller as an anode, the tool 1 is made to approach the metal material 2 while ejecting the electrolyte a from the tool 1, and a current is conducted between both electrodes to make the tool 1 By performing electric discharge machining with a large current density with the metal material 2, the moving blade 3 is formed as shown in FIGS. 4 to 6.
【0005】 このようにして、金属素材2に動翼3を逐次形成させてゆくと、金属素材2の 電解加工が行われなかった中心部寄りの部分が環状のディスク4となる。When the blades 3 are successively formed on the metal material 2 in this manner, the portion of the metal material 2 near the center where the electrolytic processing is not performed becomes the annular disk 4.
【0006】[0006]
従来、電解加工により製作される一体型翼車では、工具1の形状が電極加工が 容易なように加工本位に設計されているので、動翼3の翼根部の前後長さLに対 して、ディスク外周面の厚さ(ディスク外周面における前後方向の寸法)Tが大 きく、ディスク外周面前縁5が動翼3の翼根部前端6よりも前方A側に位置し、 ディスク外周面後縁7が動翼3の翼根部後端8よりも後方B側に位置している。 一方、動翼3は高温の燃焼ガスに流通によって昇温されやすいのに対し、ディ スク4は動翼3に比較して昇温されにくく、また、動翼3の翼根部前端6に比べ て翼根部後端8の方が温度が低い。 Conventionally, in the integrated impeller manufactured by electrolytic machining, the shape of the tool 1 is designed for machining so that electrode machining is easy, so that the front-back length L of the blade root of the rotor blade 3 is The thickness of the disc outer peripheral surface (the dimension in the front-rear direction on the disc outer peripheral surface) T is large, and the disc outer peripheral surface front edge 5 is located on the front side A side of the blade root front end 6 of the rotor blade 3, and the disc outer peripheral surface rear edge is 7 is located on the rear B side of the blade root rear end 8 of the moving blade 3. On the other hand, the rotor blade 3 is likely to be heated by the flow of high-temperature combustion gas, whereas the disc 4 is less likely to be heated than the rotor blade 3, and compared to the blade root front end 6 of the rotor blade 3. The temperature at the rear end 8 of the blade root is lower.
【0007】 このため、燃焼ガスの温度を上昇させてエンジンの高出力化を図ろうとすると 、動翼3とディスク4並びに翼根部前端6と翼根部後端8の熱膨張差がより大き くなるとともに、タービンディスクの回転数の向上に起因する遠心力の増大によ り動翼3の翼根部前端6と翼根部後端部8に過大な応力集中が生じることが予想 される。Therefore, when the temperature of the combustion gas is raised to increase the output of the engine, the difference in thermal expansion between the moving blade 3, the disk 4, the blade root front end 6 and the blade root rear end 8 becomes larger. At the same time, it is expected that an excessive stress concentration will occur at the blade root front end 6 and the blade root rear end 8 of the rotor blade 3 due to the increase in centrifugal force resulting from the improvement in the rotational speed of the turbine disk.
【0008】 本考案は前述した実情に鑑みなしたもので、動翼の翼根部前端並びに翼根部後 端における応力集中を抑制することが可能な一体型翼車を提供することを目的と している。The present invention has been made in view of the above-mentioned circumstances, and an object thereof is to provide an integrated impeller capable of suppressing stress concentration at the blade root front end and the blade root rear end of a moving blade. There is.
【0009】[0009]
上記目的を達成するため、本考案の一体型翼車においては、環状のディスクと 該ディスクの外周面に略等間隔に設けた動翼とを一体的に形成した一体形翼車に おいて、ディスク外周面前縁を各動翼の翼根部前端にディスク外周面後縁を各動 翼の翼根部後端にそれぞれ位置させ、前記のディスク外周面前縁からディスク前 端面になだらかに連なりディスク径方向の断面が凹曲線形状を有する前部環状湾 曲面並びに前記のディスク外周面後縁からディスク後端面になだらかに連なり且 つディスク径方向の断面が凹曲線形状を有する後部環状湾曲面を設けている。 In order to achieve the above object, in the integrated impeller of the present invention, an integrated impeller in which an annular disc and rotor blades provided at substantially equal intervals on the outer peripheral surface of the disc are integrally formed, The front edge of the disk outer peripheral surface is located at the front end of the blade root of each blade, and the rear edge of the disk outer peripheral surface is located at the rear end of the blade root of each blade. A front annular curved surface having a concave curve shape and a rear annular curved surface having a concave curve shape in the disk radial direction are provided which are smoothly connected from the trailing edge of the disk outer peripheral surface to the disk rear end surface.
【0010】[0010]
ディスク外周面前縁とディスク前端面との間に前部環状湾曲面を、また、ディ スク外周面後縁とディスク後端面との間に後部環状湾曲面を形成しているので、 動翼の温度上昇やディスクの高回転化により増大する遠心力により動翼の翼根部 前端並びに翼根部後端に生じる応力集中が抑制される。 Since a front annular curved surface is formed between the disk outer peripheral surface front edge and the disk front end surface, and a rear annular curved surface is formed between the disk outer peripheral surface rear edge and the disk rear end surface, the rotor blade temperature The concentration of stress generated at the blade root front end and blade root rear end of the rotor blade due to the centrifugal force that increases due to the rise and higher disk rotation is suppressed.
【0011】[0011]
以下、本考案の実施例を図面を参照しつつ説明する。 Hereinafter, embodiments of the present invention will be described with reference to the drawings.
【0012】 図1から図3は本考案の一体型翼車の一実施例を示すもので、9は環状のディ スク、10は動翼である。1 to 3 show an embodiment of an integrated impeller of the present invention, in which 9 is an annular disk and 10 is a moving blade.
【0013】 動翼10はディスク9の外周面11にディスク周方向に略等間隔に設けられお り、各動翼10はディスク9と一体的に形成されている。The moving blades 10 are provided on the outer peripheral surface 11 of the disk 9 at substantially equal intervals in the disk circumferential direction, and each moving blade 10 is formed integrally with the disk 9.
【0014】 ディスク外周面前縁12は各動翼10の翼根部前端13に位置し、また、ディ スク外周面後縁14は各動翼10の翼根部後端15に位置している。The disk outer peripheral surface leading edge 12 is located at the blade root front end 13 of each rotor blade 10, and the disk outer peripheral surface trailing edge 14 is located at the blade root rear end 15 of each rotor blade 10.
【0015】 更に、前記のディスク外周面前縁12とディスク前端面16との間には、なだ らかに連なりディスク径方向の断面が凹曲線形状を有する前部環状湾曲面17が 形成され、また、前記のディスク外周面後縁14とディスク後端面18との間に は、なだらかに連なりディスク径方向の断面が凹曲線形状を有する後部環状湾曲 面19が形成されている。Further, between the disc outer peripheral surface front edge 12 and the disc front end face 16, there is formed a front annular curved surface 17 which is smoothly continuous and has a concave curved shape in a disc radial direction cross section. A rear annular curved surface 19 is formed between the trailing edge 14 of the outer peripheral surface of the disk and the trailing end surface 18 of the disk, which is smoothly continuous and has a concave curved cross section in the disk radial direction.
【0016】 上述した形状を有する一体型翼車を製造する際には、金属素材2に電解加工を 施して図3等に示すような一体型翼車を形成された後、該一体型翼車のディスク 9に放電加工等の手段により前部環状湾曲面17並びに後部環状湾曲面19を形 成させるようにするか、あるいは、金属素材2に対して機械加工等の手段により 予め前部環状湾曲面17並びに後部環状湾曲面19を形成させておく。In manufacturing the integrated impeller having the above-described shape, the metal material 2 is subjected to electrolytic processing to form the integrated impeller as shown in FIG. The front annular curved surface 17 and the rear annular curved surface 19 are formed on the disk 9 by means of electric discharge machining or the like, or the front annular curved surface is previously formed on the metal material 2 by means such as machining. The surface 17 and the rear annular curved surface 19 are formed.
【0017】 上述した構成を有する一体型翼車においては、ディスク外周面前縁12とディ スク前端面16との間に凹曲線形状を有する前部環状湾曲面17を設け、また、 ディスク外周面後縁14とディスク後端面18との間に凹曲線形状を有する後部 環状湾曲面19を形成しているので、動翼10の温度上昇やタービンディスクの 高回転化により増大する遠心力により動翼10の翼根部前端13並びに翼根部後 端15に生じる応力集中を抑制することができる。In the integrated impeller having the above-mentioned configuration, the front annular curved surface 17 having a concave curved shape is provided between the disk outer peripheral surface front edge 12 and the disk front end surface 16, and the disk outer peripheral surface rear Since the rear annular curved surface 19 having a concave curve shape is formed between the edge 14 and the disk rear end surface 18, the rotor blade 10 is increased by the centrifugal force increased by the temperature rise of the rotor blade 10 and the rotation speed of the turbine disc. It is possible to suppress stress concentration occurring at the blade root front end 13 and the blade root rear end 15.
【0018】 なお、本考案は上述した実施例のみに限定されるものではなく、本考案の要旨 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。It should be noted that the present invention is not limited to the above-described embodiments, and it goes without saying that various modifications can be made without departing from the gist of the present invention.
【0019】[0019]
以上述べたように本考案の一体型翼車によれば、下記のような種々の優れた効 果を奏し得る。 As described above, the integrated impeller of the present invention can exert various excellent effects as described below.
【0020】 (1)ディスク外周面前縁を各動翼の翼根部前端に且つディスク外周面後縁を 各動翼の翼根部後端にそれぞれ位置させ、ディスク外周面前端とディスク前端と の間に前部環状湾曲面を形成し、ディスク外周面後縁とディスク後端面との間に 後部環状湾曲面を形成しているので、動翼の温度上昇やタービンディスクの高回 転化により増大する遠心力により動翼の翼根部前端並びに翼根部後端に生じる応 力集中が抑制される。(1) The front edge of the disk outer peripheral surface is located at the blade root front end of each blade, and the disk outer peripheral surface trailing edge is located at the blade root rear end of each blade, and between the disk outer peripheral surface front end and the disk front end. The front annular curved surface is formed, and the rear annular curved surface is formed between the trailing edge of the outer peripheral surface of the disk and the rear end surface of the disk.Therefore, centrifugal force increases due to the temperature rise of the rotor blade and the high rotation of the turbine disk. As a result, the concentration of force generated at the blade root front end and blade root rear end is suppressed.
【0021】 (2)動翼の温度上昇に起因する翼根部前端並びに翼根部後端の応力集中が抑 制されるので、燃焼ガスの温度を上昇させることが可能となり、エンジンの高出 力化を図ることができる。(2) Since the stress concentration at the blade root front end and the blade root rear end due to the temperature rise of the moving blade is suppressed, it becomes possible to raise the temperature of the combustion gas and increase the engine output. Can be achieved.
【図1】本考案の一体型翼車の一実施例を示す部分切断
斜視図である。FIG. 1 is a partially cutaway perspective view showing an embodiment of the integrated impeller of the present invention.
【図2】本考案の一体型翼車の一実施例を示す部分縦断
面図である。FIG. 2 is a partial vertical cross-sectional view showing an embodiment of the integrated impeller of the present invention.
【図3】図2のIII−III矢視図である。FIG. 3 is a view taken along the line III-III in FIG.
【図4】従来の一体型翼車の一例を示す部分切断斜視図
である。FIG. 4 is a partially cutaway perspective view showing an example of a conventional integrated impeller.
【図5】従来の一体型翼車の一例を示す部分縦断面図で
ある。FIG. 5 is a partial vertical cross-sectional view showing an example of a conventional integrated impeller.
【図6】図5のVI−VI矢視図である。6 is a VI-VI arrow view of FIG.
9 ディスク 10 動翼 12 ディスク外周面前縁 13 翼根部前端 14 ディスク外周面後縁 15 翼根部後端 16 ディスク前端面 17 前部環状湾曲面 18 ディスク後端面 19 後部環状湾曲面 9 disk 10 moving blade 12 disk outer peripheral surface front edge 13 blade root front end 14 disk outer peripheral surface trailing edge 15 blade root rear end 16 disk front end surface 17 front annular curved surface 18 disk rear end surface 19 rear annular curved surface
Claims (1)
略等間隔に設けた動翼とを一体的に形成した一体形翼車
において、ディスク外周面前縁を各動翼の翼根部前端に
且つディスク外周面後縁を各動翼の翼根部後端にそれぞ
れ位置させ、前記のディスク外周面前縁からディスク前
端面になだらかに連なりディスク径方向の断面が凹曲線
形状を有する前部環状湾曲面並びに前記のディスク外周
面後縁からディスク後端面になだらかに連なりディスク
径方向の断面が凹曲線形状を有する後部環状湾曲面を設
けたことを特徴とする一体型翼車。1. An integrated vane wheel in which an annular disk and moving blades provided at substantially equal intervals on the outer peripheral surface of the disk are integrally formed, and a front edge of the outer peripheral surface of the disk is provided at a blade root front end of each blade. A disk outer peripheral surface trailing edge is positioned at each blade root rear end of each blade, and the front annular curved surface having a concave curved shape in a disk radial section which is smoothly connected from the disk outer peripheral surface leading edge to the disk front end surface. An integral type impeller, characterized in that a rear annular curved surface is provided which is smoothly continuous from the trailing edge of the outer peripheral surface of the disc to the trailing end face of the disc and has a concave curved cross-section in the disc radial direction.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP700893U JPH0660701U (en) | 1993-02-01 | 1993-02-01 | Integrated wing wheel |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP700893U JPH0660701U (en) | 1993-02-01 | 1993-02-01 | Integrated wing wheel |
Publications (1)
Publication Number | Publication Date |
---|---|
JPH0660701U true JPH0660701U (en) | 1994-08-23 |
Family
ID=11654037
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP700893U Pending JPH0660701U (en) | 1993-02-01 | 1993-02-01 | Integrated wing wheel |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPH0660701U (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1998057042A1 (en) * | 1997-06-12 | 1998-12-17 | Mitsubishi Heavy Industries, Ltd. | Cooled moving blade for gas turbines |
-
1993
- 1993-02-01 JP JP700893U patent/JPH0660701U/en active Pending
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1998057042A1 (en) * | 1997-06-12 | 1998-12-17 | Mitsubishi Heavy Industries, Ltd. | Cooled moving blade for gas turbines |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP4636746B2 (en) | Method and apparatus for reducing circumferential rim stress in a rotor assembly | |
JP4138363B2 (en) | Gas turbine engine, airfoil portion thereof, and manufacturing method thereof | |
JP5671479B2 (en) | Curved platform turbine blade | |
JP4856302B2 (en) | Compressor blisk flow path with reduced stress | |
US7445433B2 (en) | Fan or compressor blisk | |
JP3948926B2 (en) | Method and apparatus for reducing circumferential rim stress in a rotor assembly | |
US7290986B2 (en) | Turbine airfoil with curved squealer tip | |
US8834129B2 (en) | Turbofan flow path trenches | |
US6790005B2 (en) | Compound tip notched blade | |
US5261789A (en) | Tip cooled blade | |
JP2002161702A5 (en) | ||
EP1895100B1 (en) | Conformal tip baffle airfoil | |
JP2007064221A (en) | Optimization for stator vane profile | |
JP4771672B2 (en) | Method and apparatus for reducing vibrations occurring in compressor airfoils | |
JP4304263B2 (en) | Non-parallel dovetail surface fabrication method and dovetail assembly | |
JP2005054798A (en) | Blade profile part of counter stagger type compressor | |
JPH04262002A (en) | Stationary blade structure for steam turbine | |
US20060280610A1 (en) | Turbine blade and method of fabricating same | |
JP2008540921A (en) | Rotor blade / disc dovetail backcut to reduce stress on rotor blade / disk (7FA + e, 2nd stage) | |
JP2003227301A (en) | Step-down turbine platform | |
JP2008291846A (en) | Method for centrally installing cutter tooth on turbine blade with shroud | |
JPH04228804A (en) | Turbine blade and its crack reducing method | |
US10941671B2 (en) | Gas turbine engine component incorporating a seal slot | |
JP2008106778A (en) | Blade/disk dovetail backcut for blade/disk stress reduction (7fa, stage 1) | |
EP4130430A1 (en) | Integrated bladed rotor |