JP2851577B2 - Processing method of cooling air flow path in gas turbine vane shroud - Google Patents
Processing method of cooling air flow path in gas turbine vane shroudInfo
- Publication number
- JP2851577B2 JP2851577B2 JP3788796A JP3788796A JP2851577B2 JP 2851577 B2 JP2851577 B2 JP 2851577B2 JP 3788796 A JP3788796 A JP 3788796A JP 3788796 A JP3788796 A JP 3788796A JP 2851577 B2 JP2851577 B2 JP 2851577B2
- Authority
- JP
- Japan
- Prior art keywords
- cooling air
- air flow
- flow path
- shroud
- gas turbine
- 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.)
- Expired - Lifetime
Links
- 238000001816 cooling Methods 0.000 title claims description 26
- 238000003672 processing method Methods 0.000 title claims 2
- 238000003754 machining Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 6
- 238000005553 drilling Methods 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Description
【０００１】[0001]
【発明の属する技術分野】本発明はガスタービン静翼シ
ュラウドに冷却空気を通す冷却空気流路を加工する方法
に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method for machining a cooling air passage for passing cooling air through a gas turbine vane shroud.
【０００２】[0002]
【従来の技術】ガスタービンの高温化が進むにつれてガ
スタービン静翼のシュラウドも冷却が必要とされてく
る。図２はシュラウドの全貌を示し、図３は同シュラウ
ドに設けた従来の冷却空気流路を図２のＡ−Ａ断面で示
している。2. Description of the Related Art As the temperature of a gas turbine increases, the shroud of a gas turbine stationary blade also needs to be cooled. FIG. 2 shows the whole of the shroud, and FIG. 3 shows a conventional cooling air flow path provided in the shroud in a sectional view taken along line AA of FIG.
【０００３】図３において、冷却空気流路１１はシュラ
ウド１２が隣接して互いに嵌合うシール溝１３の下に軸
方向に貫通して穿設されており、図２のシュラウド平面
図に示すように冷却空気流路１１はその直径に対して非
常に長い。従って冷却空気流路１１の加工には、高度な
加工技術が要求される。In FIG. 3, a cooling air flow passage 11 is formed so as to penetrate axially below a seal groove 13 in which a shroud 12 is adjacently fitted to each other, and as shown in a plan view of the shroud in FIG. The cooling air passage 11 is very long for its diameter. Therefore, processing of the cooling air flow path 11 requires advanced processing techniques.
【０００４】[0004]
【発明が解決しようとする課題】前記したように、その
径に対して長い冷却空気流路１１をドリル加工するに
は、近接して削設されているシール溝１３を避けた機械
加工が必要とされるが、流路の長さが長いので機械加工
の精度上、正確に加工するのには、非常に困難である。As described above, in order to drill the cooling air flow path 11 that is long with respect to its diameter, it is necessary to perform machining that avoids the seal groove 13 that is cut in close proximity. However, since the length of the flow path is long, it is very difficult to perform accurate machining due to the accuracy of machining.
【０００５】またその冷却空気流路にタービュレータ
（冷却フィン）を設けるとなると、精度の出る加工は殆
んど不可能である。If turbulators (cooling fins) are provided in the cooling air flow path, highly accurate machining is almost impossible.
【０００６】本発明はこの問題点を解消し、確実かつ容
易にこの冷却空気流路の加工を行なう方法を提供するこ
とを課題とするものである。An object of the present invention is to solve this problem and to provide a method for processing the cooling air flow path reliably and easily.
【０００７】[0007]
【課題を解決するための手段】本発明は前記課題を解決
するべくなされたもので、シュラウド端面に軸方向に延
びる溝を加工し、同溝の開口部をプラグで塞いで冷却空
気流路を形成したガスタービン静翼シュラウドにおける
冷却空気流路の加工方法を提供し、シュラウドの冷却の
加工が側面開放で、まず溝の形成次いでこの溝の開口部
をプラグで塞ぐという手順で行なわれるため、作業は確
実、容易であり、また、工具の形状等の選択次第でター
ビュレータ通路の形成も可能となるほか、シュラウドを
軸方向にドリル加工する方式に比べて加工精度も格段に
向上する上、シール溝と干渉することもなく容易に所望
の冷却空気流路を得ることができるものである。SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problem, and has a groove formed in an end face of a shroud extending in an axial direction, and an opening of the groove is closed with a plug to form a cooling air flow path. To provide a method of processing the cooling air flow path in the formed gas turbine vane shroud, since the processing of the cooling of the shroud is performed by opening the side surfaces, first forming a groove, and then closing the opening of the groove with a plug, The work is reliable and easy, the turbulator passage can be formed depending on the selection of the tool shape, etc., the machining accuracy is significantly improved compared to the method of drilling the shroud in the axial direction, and the seal is improved. The desired cooling air flow path can be easily obtained without interfering with the grooves.
【０００８】[0008]
【発明の実施の形態】本発明の実施の一形態を図１に基
づいて説明する。図１は静翼シュラウド部の断面図で、
前記した図２のＡ−Ａ断面位置に相当する部分を示して
いる。DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of the present invention will be described with reference to FIG. FIG. 1 is a sectional view of a stationary blade shroud portion.
2 shows a portion corresponding to the cross-sectional position along AA in FIG. 2 described above.
【０００９】静翼シュラウド１の端面には、隣接したシ
ュラウド同志が互いに嵌合うシール溝２が加工されてい
てその下に凸形状の工具を用いて軸方向に冷却空気流路
用の溝３を加工する。On the end face of the vane shroud 1, a seal groove 2 is formed in which adjacent shrouds are fitted to each other, and a groove 3 for a cooling air flow path is formed axially below the convex groove by using a convex tool. Process.
【００１０】次いでこの溝３の開口部に軸方向に板状の
プラグ４を嵌め込み、周囲をロー付などで塞いで軸方向
へ延びる冷却空気流路を完成する。Next, a plate-like plug 4 is fitted in the opening of the groove 3 in the axial direction, and the periphery thereof is closed with a braze or the like to complete a cooling air flow path extending in the axial direction.
【００１１】このように本実施の形態では、冷却空気流
路３はシュラウド側面開放で加工できるので加工が容易
であり、加工精度も格段に向上し、其の上工具の選択等
によってはタービュレータ通路の形成も可能にするもの
である。As described above, in the present embodiment, the cooling air flow path 3 can be processed by opening the side surface of the shroud, so that the processing is easy, the processing accuracy is remarkably improved, and the turbulator passage depends on the selection of the tool. Can also be formed.
【００１２】なお、ここでは凸形状の工具を用いて溝３
を加工するものを説明したが、工具の形状の選択、工具
の移動方向（切削方向等）の選択、また、溝３の開口部
へ嵌め込むプラグの形状の選択、プラグの内面加工、そ
してこれら選択したものの組合せの仕方等によって、冷
却空気流路の形状は方形、円形その他種々の形状としう
ることは容易に理解されよう。Here, the groove 3 is formed by using a convex tool.
However, the selection of the shape of the tool, the selection of the moving direction (cutting direction, etc.) of the tool, the selection of the shape of the plug fitted into the opening of the groove 3, the inner surface processing of the plug, and the like It can be easily understood that the shape of the cooling air flow path can be square, circular or various other shapes depending on the combination of the selected components.
【００１３】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.
【００１４】[0014]
【発明の効果】以上、本発明によれば、冷却空気流路の
加工が著しく容易になるとともに加工精度も格段に向上
することができたものである。又タービュレータ通路の
形成も可能となると共に、冷却穴の形状も種々選択でき
るのでシュラウド端の冷却性能を一段と向上することが
できるなど、ガスタービン性能向上に寄与する効果は大
きいものである。As described above, according to the present invention, the processing of the cooling air flow passage is remarkably facilitated and the processing accuracy can be remarkably improved. Further, the turbulator path can be formed, and the shape of the cooling hole can be variously selected, so that the cooling performance at the shroud end can be further improved.
【図１】本発明の実施の一形態に係る静翼シュラウド部
の要部を示す断面図。FIG. 1 is a sectional view showing a main part of a stationary blade shroud portion according to an embodiment of the present invention.
【図２】静翼シュラウド部における冷却空気流路の位置
関係を示す同静翼シュラウド部の断面図。FIG. 2 is a sectional view of the stationary blade shroud showing a positional relationship of a cooling air flow path in the stationary blade shroud.
【図３】従来の静翼シュラウド部の要部を示す断面図。FIG. 3 is a sectional view showing a main part of a conventional stationary blade shroud portion.
１ 静翼シュラウド ２ シール溝 ３ 冷却空気流路用の溝 ４ プラグ DESCRIPTION OF SYMBOLS 1 Stator blade shroud 2 Seal groove 3 Cooling air passage groove 4 Plug
フロントページの続き (72)発明者 川合 渉 兵庫県高砂市荒井町新浜二丁目１番１号 三菱重工業株式会社高砂製作所内 (72)発明者 福良 孝 兵庫県高砂市荒井町新浜二丁目１番１号 三菱重工業株式会社高砂製作所内 (72)発明者 浅野 弘 兵庫県高砂市荒井町新浜二丁目１番１号 三菱重工業株式会社高砂製作所内 (56)参考文献 特開 平３−194101（ＪＰ，Ａ) 特開 平８−200002（ＪＰ，Ａ) (58)調査した分野(Int.Cl.6，ＤＢ名) F01D 9/02,5/18Continued on the front page (72) Inventor Wataru Kawai 2-1-1 Shinhama, Arai-machi, Takasago City, Hyogo Prefecture Inside the Takasago Works, Mitsubishi Heavy Industries, Ltd. (72) Inventor Hiroshi Asano 2-1-1, Aramachi-cho, Niihama, Arai-machi, Takasago-shi, Hyogo Prefecture, Japan Inside Takasago Works, Mitsubishi Heavy Industries, Ltd. (56) References JP-A-3-194101 (JP, A) Hei 8-200002 (JP, A) (58) Field surveyed (Int. Cl. 6 , DB name) F01D 9/02, 5/18
Claims (1)
工し、同溝の開口部をプラグで塞いで冷却空気流路を形
成したことを特徴とするガスタービン静翼シュラウドに
おける冷却空気流路の加工方法。1. A cooling air flow path in a gas turbine vane shroud, wherein a groove extending in an axial direction is formed on an end face of the shroud, and an opening of the groove is closed with a plug to form a cooling air flow path. Processing method.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3788796A JP2851577B2 (en) | 1996-02-26 | 1996-02-26 | Processing method of cooling air flow path in gas turbine vane shroud |
| US09/145,237 US5957657A (en) | 1996-02-26 | 1998-09-01 | Method of forming a cooling air passage in a gas turbine stationary blade shroud |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3788796A JP2851577B2 (en) | 1996-02-26 | 1996-02-26 | Processing method of cooling air flow path in gas turbine vane shroud |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH09228803A JPH09228803A (en) | 1997-09-02 |
| JP2851577B2 true JP2851577B2 (en) | 1999-01-27 |
Family
ID=12510058
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP3788796A Expired - Lifetime JP2851577B2 (en) | 1996-02-26 | 1996-02-26 | Processing method of cooling air flow path in gas turbine vane shroud |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2851577B2 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6173491B1 (en) * | 1999-08-12 | 2001-01-16 | Chromalloy Gas Turbine Corporation | Method for replacing a turbine vane airfoil |
| JP5679246B1 (en) | 2014-08-04 | 2015-03-04 | 三菱日立パワーシステムズ株式会社 | High-temperature component of gas turbine, gas turbine including the same, and method for manufacturing high-temperature component of gas turbine |
| JP6587251B2 (en) | 2015-11-27 | 2019-10-09 | 三菱日立パワーシステムズ株式会社 | Flow path forming plate, flow path forming assembly member and vane including the same, gas turbine, flow path forming plate manufacturing method, and flow path forming plate remodeling method |
| JP6725273B2 (en) | 2016-03-11 | 2020-07-15 | 三菱日立パワーシステムズ株式会社 | Wing, gas turbine equipped with this |
-
1996
- 1996-02-26 JP JP3788796A patent/JP2851577B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPH09228803A (en) | 1997-09-02 |
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