JPH1122402A - Gas turbine rotor - Google Patents
Gas turbine rotorInfo
- Publication number
- JPH1122402A JPH1122402A JP17409797A JP17409797A JPH1122402A JP H1122402 A JPH1122402 A JP H1122402A JP 17409797 A JP17409797 A JP 17409797A JP 17409797 A JP17409797 A JP 17409797A JP H1122402 A JPH1122402 A JP H1122402A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- cavity
- upstream
- pressure
- rotor
- 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
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 43
- 230000002093 peripheral effect Effects 0.000 claims description 7
- 238000001816 cooling Methods 0.000 abstract description 26
- 239000012530 fluid Substances 0.000 abstract description 5
- 230000003068 static effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明はガスタービン車室か
ら静翼を経て動翼に冷却空気を供給する構造を備えたガ
スタービンロータに関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine rotor having a structure for supplying cooling air from a gas turbine casing to stationary blades via stationary blades.
【０００２】[0002]
【従来の技術】従来のものについて図３および図４に基
づいて説明する。2. Description of the Related Art A conventional device will be described with reference to FIGS.
【０００３】図３に示すものでは、静翼２０を経由した
冷却空気２１は、矢印で示すように静翼２０の内端上流
側に設けた孔２２から流出し、静翼翼頂のラビリンス２
３を通り抜けて動翼２４の翼根部２５に供給され、冷却
に供されるようになっている。In FIG. 3, cooling air 21 passing through a stationary blade 20 flows out of a hole 22 provided on the upstream side of the inner end of the stationary blade 20 as shown by an arrow, and a labyrinth 2 at the top of the stationary blade.
3 and is supplied to the blade root portion 25 of the rotor blade 24 for cooling.
【０００４】すなわち、この形式のものにあっては、前
記翼根部２５に冷却空気を流すのは、同翼根部２５の上
流側と下流側の静圧差に依存することになるので、動翼
２４の前で高くするかもしくは動翼２４の後で低くする
ことが必要である。That is, in this type, the flow of cooling air to the blade root 25 depends on the static pressure difference between the upstream side and the downstream side of the blade root 25. Or lower after the rotor blades 24.
【０００５】また図４に示す他の形式のものは、前記図
３のものの構成に加えて、静翼２０の内周部に後流方向
に向けて開口するノズル２６を設け、同ノズル２６から
も冷却空気を噴出させ、同冷却空気が動翼２４の翼根部
２５へ入り易くなるようにしたものである。In another type shown in FIG. 4, in addition to the configuration shown in FIG. 3, a nozzle 26 is provided on the inner peripheral portion of the stationary blade 20 so as to open in the downstream direction. The cooling air is also blown out so that the cooling air can easily enter the blade root 25 of the moving blade 24.
【０００６】このノズル２６から噴出する冷却空気の流
れは、図４（ａ）のＣ−Ｃ断面をとって図４（ｂ）に示
すように、ノズル２６の噴出角をθ、動翼２４の周速度
をｕ、冷却空気の噴出速度をｃとすると、図４（ｂ）中
に記入した速度三角形ができ、流入速度ｗが求められる
ことになる。As shown in FIG. 4B, the flow of the cooling air ejected from the nozzle 26 is taken along the line C--C in FIG. Assuming that the peripheral velocity is u and the jetting velocity of the cooling air is c, the velocity triangle described in FIG. 4B is formed, and the inflow velocity w is obtained.
【０００７】しかし、この流入速度ｗが加重されるとは
いうものの、この形式のものにあっても翼根部２５へ供
給される冷却空気の流動は、動翼２４の翼根部２５にお
ける上流側と下流側との静圧差によることが基本であ
る。However, although this inflow velocity w is weighted, even in this type, the flow of the cooling air supplied to the blade root portion 25 flows between the upstream side of the blade root portion 25 of the moving blade 24. It is basically based on the static pressure difference with the downstream side.
【０００８】[0008]
【発明が解決しようとする課題】タービン後方段の長い
動翼では、流体の速度の周方向成分は遠心力を発生さ
せ、流れが外周へ片寄る傾向があるので、通路面積内を
できるだけ一様流れにし、流体が軸方向に滑らかに流れ
るように、動翼へ入る時の圧力を外周寄りで高く、内周
で低くなるように動翼の通路面積と出入口角度を調整し
た設計とするのが普通である。In a long rotor blade at the rear stage of the turbine, the circumferential component of the velocity of the fluid generates a centrifugal force, and the flow tends to be shifted to the outer periphery. In general, the design is such that the passage area and the entrance / exit angle of the moving blade are adjusted so that the pressure entering the moving blade is high near the outer circumference and lower at the inner circumference so that the fluid flows smoothly in the axial direction. It is.
【０００９】その結果、このような長い動翼の根本近く
ではその段の圧力降下の大部分が静翼中で発生し、動翼
前後の圧力差は極くわずかなものとなってしまう。従っ
て前記した図３の形式のものでは、翼根部へ冷却空気を
導入して所定の冷却空気量を確保することがむづかしく
なってしまうものである。As a result, near the root of such a long moving blade, most of the pressure drop at that stage occurs in the stationary blade, and the pressure difference between before and after the moving blade becomes very small. Therefore, in the case of the type shown in FIG. 3, it is difficult to secure a predetermined amount of cooling air by introducing cooling air to the blade root.
【００１０】同様に図４のものでも、ラビリンス２３を
通った冷却空気による動翼前後の圧力差での冷却空気の
導入は期待できず、ノズル２６の噴出に多くを依存する
こととなり、冷却空気量の確保は大巾に低下せざるをえ
ないものである。Similarly, in FIG. 4 as well, the introduction of cooling air due to the pressure difference between the front and rear blades due to the cooling air passing through the labyrinth 23 cannot be expected, and the cooling air largely depends on the ejection of the nozzle 26. Securing the quantity has to be drastically reduced.
【００１１】本発明はこのような従来のものにおける不
具合を解消し、動翼の翼根部に対して確実に冷却空気を
供給しうるようにしたものを提供することを課題とする
ものである。SUMMARY OF THE INVENTION It is an object of the present invention to solve the above-mentioned disadvantages of the prior art and to provide a cooling blade capable of reliably supplying cooling air to a blade root portion of a moving blade.
【００１２】[0012]
【課題を解決するための手段】本発明は前記した課題を
解決すべくなされたもので、相隣接するディスクの翼根
位置で互いに軸方向に対向して張り出して当接する一対
のディスク腕と、同腕の外側で動翼の上流側端部底位置
に形成した動翼翼溝キャビティと、静翼の内周端上流側
に対向して形成した静翼上流側キャビティを有し、前記
一対のディスク腕を軸方向に貫通して前記静翼上流側キ
ャビティと動翼翼溝キャビティとを連通する連通孔を設
けたガスタービンロータを提供するものである。DISCLOSURE OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and comprises a pair of disk arms which project and abut against each other at the blade root positions of adjacent disks in the axial direction. A rotor blade groove cavity formed outside the arm at the upstream end of the rotor blade at a bottom position, and a stator blade upstream cavity formed facing the inner peripheral end upstream of the stator blade; An object of the present invention is to provide a gas turbine rotor provided with a communication hole which penetrates an arm in an axial direction and communicates the stator blade upstream side cavity and the rotor blade groove cavity.
【００１３】すなわち、動翼の上流側端部底位置の動翼
翼溝キャビティと、静翼の内周端上流側の静翼上流側キ
ャビティとは、ディスク腕を貫通した連通孔で連通され
ているので、動翼翼溝キャビティの圧力は静翼上流側キ
ャビティの圧力をほぼ確保することとなり、この動翼翼
溝キャビティに続く動翼翼根部へ確実に冷却空気の供給
を行うことができるものである。That is, the rotor blade groove cavity at the bottom position on the upstream end of the rotor blade and the stator blade upstream cavity on the inner peripheral end upstream of the stator blade are communicated with each other through a communication hole penetrating the disk arm. Therefore, the pressure in the moving blade blade groove cavity substantially secures the pressure in the stationary blade upstream cavity, so that the cooling air can be reliably supplied to the moving blade blade root following the moving blade blade groove cavity.
【００１４】[0014]
【発明の実施の形態】図１及び図２に基づいて本発明の
実施の一形態を説明する。図１は（ａ），（ｂ）図に区
分して本実施の形態の要部構成を示し、また図２は図１
の要部構成をタービン中に組み入れる位置関係を示すも
のである。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described with reference to FIGS. FIG. 1 shows the main configuration of this embodiment divided into FIGS. 1 (a) and 1 (b), and FIG.
3 shows a positional relationship in which the main configuration of the above is incorporated into a turbine.
【００１５】ガスタービンのロータは図２に示すように
ディスク１を複数個軸方向に積重ね、これを締結ボルト
８で締付けて一本のロータを形成している。As shown in FIG. 2, the rotor of the gas turbine is formed by stacking a plurality of disks 1 in the axial direction and tightening the disks 1 with fastening bolts 8 to form one rotor.
【００１６】ここで隣接する一対のディスク１，１につ
いてみれば、各ディスク１，１にそれぞれ固定された動
翼２４の翼根部に相当する位置において、隣接する一方
のディスク１から他方のディスク１に向かって軸方向に
張り出したディスク腕２を設け、互に隣接するディスク
１，１のディスク腕２，２同志を当接させて相互の位置
決めを行っている。Here, regarding the pair of disks 1 and 1 adjacent to each other, at a position corresponding to the blade root portion of the moving blade 24 fixed to each disk 1 and 1, each of the disks 1 and 1 adjacent to each other is located. The disk arms 2 are provided so as to protrude in the axial direction toward each other, and the disk arms 2, 2 of the disks 1, 1 adjacent to each other are brought into contact with each other to perform mutual positioning.
【００１７】このディスク腕２，２の当接部位Ｂを拡大
して図１に示している。なお、この部位には、動翼２
４，２４の間に当る動翼翼間部３が含まれており、本来
ここには静翼が動翼と対向方向に延びて配置されている
が、ここでは図示を省略している。FIG. 1 is an enlarged view of the contact portion B between the disk arms 2 and 2. In addition, the rotor blade 2
4 and 24, the moving blade inter-blade portion 3 is included. Originally, the stationary blade extends in the direction facing the moving blade, but is not shown here.
【００１８】図１及び図２共に左側が作動流体の上流側
であり、この上流側でディスク腕２の張り出し部に当る
位置（この位置は図示省略した静翼の上流側内周端が対
向する位置に相当する）に静翼上流側キャビティ４が形
成されている。The left side of both FIGS. 1 and 2 is the upstream side of the working fluid, and a position corresponding to the overhang of the disk arm 2 on this upstream side (this position is opposite to the upstream inner peripheral end of the stationary blade not shown). (Corresponding to the position), a stationary blade upstream cavity 4 is formed.
【００１９】また、図１の右側の作動流体下流側では、
前記静翼上流側キャビティ４に対向して、動翼の上流側
端部底位置に動翼翼溝キャビティ５が形成されている。On the downstream side of the working fluid on the right side of FIG.
A rotor blade groove cavity 5 is formed at the bottom of the upstream end of the rotor blade so as to face the upstream blade cavity 4.
【００２０】そして軸方向で対向方向に張り出して延
び、その先端を当接した前記１対のディスク腕２，２に
は、同ディスク腕２，２中を軸方向に貫通する連通孔６
が設けられ、同連通孔６により前記静翼上流側キャビテ
ィ４と動翼翼溝キャビティ５とが連通されている。The pair of disk arms 2, 2 extending in the opposite direction in the axial direction and having their ends abutting are provided with communication holes 6 passing through the disk arms 2, 2 in the axial direction.
The stationary blade upstream cavity 4 and the rotor blade groove cavity 5 communicate with each other through the communication hole 6.
【００２１】なお、前記１対のディスク腕２，２の当接
部は弾性的当接を狙って図示のように一部空間９を持っ
て当接する形態としているので、同空間９を通って前記
連通孔６が開放されないようにここには円周方向に亘っ
てシール板７が配設されている。Since the contact portions of the pair of disk arms 2 and 2 have a space 9 as shown in the drawing for the purpose of elastic contact, they pass through the space 9. A seal plate 7 is provided here in the circumferential direction so that the communication hole 6 is not opened.
【００２２】本実施の形態は前記のように構成されてい
るので、図示省略の静翼を経由して静翼上流側キャビテ
ィ４に運ばれた冷却空気は、連通孔６を経て動翼翼溝キ
ャビティ５に送られる。Since the present embodiment is configured as described above, the cooling air carried to the stationary blade upstream side cavity 4 via the stationary blade (not shown) passes through the communication hole 6 and the rotor blade groove cavity. Sent to 5.
【００２３】連通孔６は、格別の障害物もなく冷却空気
はさしたる圧力損失もなく流れるので、動翼翼溝キャビ
ティ５内には静翼上流側キャビティ４内とほぼ等圧の冷
却空気が供給されることになる。Since the cooling air flows through the communication hole 6 without any particular obstacle and without any significant pressure loss, cooling air having substantially the same pressure as the inside of the stationary blade upstream side cavity 4 is supplied into the rotor blade groove cavity 5. Will be.
【００２４】換言すれば図示省略の静翼の上流側と下流
側で圧力損失はなく、静翼上流側の圧力が次位に配置さ
れた動翼上流側の圧力としてほぼそのまま持ち越される
ことになる。In other words, there is no pressure loss between the upstream side and the downstream side of the stationary blade (not shown), and the pressure on the upstream side of the stationary blade is almost carried over as the pressure on the upstream side of the moving blade arranged next. .
【００２５】従って前記動翼翼溝キャビティ５から図示
省略の動翼翼根部への冷却空気の供給に際しては、静翼
上流側キャビティの圧力にほぼ相当する圧力を以って動
翼翼根部入口圧力とするので、冷却空気の送給は、確実
に行うことができるものである。Therefore, when supplying cooling air from the rotor blade groove cavity 5 to the rotor blade root (not shown), the pressure at the rotor blade root inlet is substantially equal to the pressure of the stator blade upstream cavity. The supply of the cooling air can be reliably performed.
【００２６】以上、本発明を図示の実施の形態について
説明したが、本発明はかかる実施の形態に限定されず、
本発明の範囲内でその具体的構造に種々の変更を加えて
よいことはいうまでもない。Although the present invention has been described with reference to the illustrated embodiment, the present invention is not limited to such an embodiment.
It goes without saying that various changes may be made to the specific structure within the scope of the present invention.
【００２７】[0027]
【発明の効果】以上本発明によれば、相隣接するディス
クの翼根位置で互いに軸方向に対向して張り出して当接
する一対のディスク腕と、同腕の外側で動翼の上流側端
部底位置に形成した動翼翼溝キャビティと、静翼の内周
端上流側に対向して形成した静翼上流側キャビティを有
し、前記一対のディスク腕を軸方向に貫通して前記静翼
上流側キャビティと動翼翼溝キャビティとを連通する連
通孔を設けてガスタービンロータを構成しているので、
動翼翼溝キャビティに前記静翼上流側キャビティの圧力
に相当する圧力を確保し、これを動翼上流側の圧力とし
て動翼翼溝キャビティに続く翼根部への冷却空気を流す
力として用いることができ、冷却空気の供給を確実に、
かつ、安定的に行い得、以ってガスタービンの高温化対
応を大巾に前進させることができたものである。As described above, according to the present invention, a pair of disk arms projecting and abutting against each other in the axial direction at the blade root positions of adjacent disks, and the upstream end of the rotor blade outside the arms. A rotor blade groove cavity formed at the bottom position, and a stator blade upstream cavity formed facing the inner peripheral end upstream side of the stator blade, wherein the pair of disk arms penetrates in the axial direction and the stator blade upstream Since the gas turbine rotor is configured by providing a communication hole that communicates the side cavity and the rotor blade groove cavity,
A pressure equivalent to the pressure of the above-mentioned stationary blade upstream cavity can be secured in the bucket blade groove cavity, and this can be used as a force of flowing cooling air to the blade root following the bucket blade groove cavity as a pressure of the bucket blade upstream side. , Ensure the supply of cooling air,
In addition, the gas turbine can be performed stably, and accordingly, the response to the high temperature of the gas turbine can be greatly advanced.
【図１】本発明の実施の一形態に係るガスタービンロー
タの要部を示し、（ａ）は図２のＢ部拡大図、（ｂ）は
（ａ）のＡ−Ａ断面図である。FIGS. 1A and 1B show a main part of a gas turbine rotor according to an embodiment of the present invention, wherein FIG. 1A is an enlarged view of a portion B in FIG. 2 and FIG.
【図２】本実施の形態の要部を組み入れ、全体の位置付
けを示す説明図である。FIG. 2 is an explanatory diagram showing the overall positioning of a main part of the present embodiment.
【図３】従来のガスタービンロータの要部の一例を示す
説明図である。FIG. 3 is an explanatory view showing an example of a main part of a conventional gas turbine rotor.
【図４】従来のガスタービンロータの要部の他の例を示
し、（ａ）は同要部の説明図、（ｂ）は（ａ）のＣ−Ｃ
断面図である。4A and 4B show another example of a main part of a conventional gas turbine rotor, wherein FIG. 4A is an explanatory view of the main part, and FIG.
It is sectional drawing.
１ ディスク ２ ディスク腕 ３ 動翼翼間部 ４ 静翼上流側キャビティ ５ 動翼翼溝キャビティ ６ 連通孔 ７ シール板 ８ 締結ボルト ９ 空間 DESCRIPTION OF SYMBOLS 1 Disc 2 Disk arm 3 Rotor blade inter-blade 4 Stator vane upstream cavity 5 Rotor blade groove cavity 6 Communication hole 7 Seal plate 8 Fastening bolt 9 Space
Claims (1)
軸方向に対向して張り出して当接する一対のディスク腕
と、同腕の外側で動翼の上流側端部底位置に形成した動
翼翼溝キャビティと、静翼の内周端上流側に対向して形
成した静翼上流側キャビティを有し、前記一対のディス
ク腕を軸方向に貫通して前記静翼上流側キャビティと動
翼翼溝キャビティとを連通する連通孔を設けたことを特
徴とするガスタービンロータ。1. A pair of disk arms projecting axially opposite to each other at the blade root position of adjacent disks and abutting against each other, and a rotor blade formed outside the arm and at a bottom position on the upstream end of the rotor blade. A grooved cavity, and a stationary blade upstream cavity formed facing the inner peripheral end upstream side of the stationary blade, wherein the stationary blade upstream cavity and the moving blade groove cavity penetrate the pair of disk arms in the axial direction. A communication hole for communicating with the gas turbine rotor.
Priority Applications (6)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17409797A JP3285793B2 (en) | 1997-06-30 | 1997-06-30 | Gas turbine rotor |
| US09/242,108 US6089827A (en) | 1997-06-11 | 1998-06-10 | Rotor for gas turbines |
| CA002262539A CA2262539C (en) | 1997-06-11 | 1998-06-10 | Gas turbine rotor |
| DE69820207T DE69820207T2 (en) | 1997-06-11 | 1998-06-10 | ROTOR FOR GAS TURBINES |
| PCT/JP1998/002564 WO1998057040A1 (en) | 1997-06-11 | 1998-06-10 | Rotor for gas turbines |
| EP98924565A EP0921273B1 (en) | 1997-06-11 | 1998-06-10 | Rotor for gas turbines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17409797A JP3285793B2 (en) | 1997-06-30 | 1997-06-30 | Gas turbine rotor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH1122402A true JPH1122402A (en) | 1999-01-26 |
| JP3285793B2 JP3285793B2 (en) | 2002-05-27 |
Family
ID=15972606
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP17409797A Expired - Fee Related JP3285793B2 (en) | 1997-06-11 | 1997-06-30 | Gas turbine rotor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3285793B2 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010242750A (en) * | 2009-03-31 | 2010-10-28 | General Electric Co <Ge> | Supply of film cooling hole from seal slot |
| KR102582763B1 (en) * | 2023-06-07 | 2023-09-26 | 터보파워텍(주) | Method for manufacturing turbine labyrinth seal by wire arc additive manufacturing |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105756719B (en) * | 2016-01-08 | 2018-02-06 | 北京航空航天大学 | A kind of Profile For Compressor Stator blade root grooving method based on optimized algorithm |
-
1997
- 1997-06-30 JP JP17409797A patent/JP3285793B2/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010242750A (en) * | 2009-03-31 | 2010-10-28 | General Electric Co <Ge> | Supply of film cooling hole from seal slot |
| KR102582763B1 (en) * | 2023-06-07 | 2023-09-26 | 터보파워텍(주) | Method for manufacturing turbine labyrinth seal by wire arc additive manufacturing |
| US12209500B2 (en) | 2023-06-07 | 2025-01-28 | Turbo Powertech Co., Ltd. | Method for manufacturing turbine labyrinth seal using wire arc additive manufacturing |
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| JP3285793B2 (en) | 2002-05-27 |
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