JP3241241B2 - Hollow gas turbine blades - Google Patents
Hollow gas turbine bladesInfo
- Publication number
- JP3241241B2 JP3241241B2 JP20324495A JP20324495A JP3241241B2 JP 3241241 B2 JP3241241 B2 JP 3241241B2 JP 20324495 A JP20324495 A JP 20324495A JP 20324495 A JP20324495 A JP 20324495A JP 3241241 B2 JP3241241 B2 JP 3241241B2
- Authority
- JP
- Japan
- Prior art keywords
- blade
- trailing edge
- gas turbine
- pedestal
- hollow gas
- 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
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、翼後縁端における
熱応力を緩和することができるようにした中空のガスタ
ービン翼に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a hollow gas turbine blade capable of reducing thermal stress at a trailing edge of the blade.
【０００２】[0002]
【従来の技術】図２に、従来の中空ガスタービン動翼の
一例を示す。翼根１１の底部から流入した冷却空気は、
矢印の方向に流れて動翼を冷却する。即ち、前縁側１２
Ａから流入した冷却空気は、タービュレンスプロモータ
を形成する冷却フィン１３を有する冷却空気通路を流れ
て翼を冷却し翼頭部（シャワーヘッド）及び翼側（フィ
ルム冷却）を冷却して主ガス流れに合流する。また、後
縁部１２Ｂから流入した冷却空気は、冷却空気通路を矢
印の方向に流れピンフィン１４で翼後縁を冷却したの
ち、翼後縁の出口スロット部において、ペデスタル１６
とペデスタル１６との間に形成される穴（スロット）１
５から流出して主ガス流れに合流する。2. Description of the Related Art FIG. 2 shows an example of a conventional hollow gas turbine blade. The cooling air flowing from the bottom of the blade root 11 is
It flows in the direction of the arrow to cool the blade. That is, the leading edge 12
The cooling air flowing in from A flows through the cooling air passage having the cooling fins 13 forming the turbulence promoter, cools the blades, cools the blade head (shower head) and the blade side (film cooling), and forms a main gas flow. Join. The cooling air flowing in from the trailing edge portion 12B flows through the cooling air passage in the direction of the arrow to cool the trailing edge of the blade with the pin fins 14, and then, at the outlet slot portion of the trailing edge of the blade, the pedestal 16
(Slot) 1 formed between the pedestal 16 and the pedestal 16
5 and merges with the main gas stream.
【０００３】図３は翼後縁端部の前記出口スロット部の
部分図であり、図３に示すように、翼後縁端にペデスタ
ル１６の端面が面一に設けられていて、ペデスタル１６
とペデスタル１６との間の隙間で形成される穴１５を、
矢印に示すように、冷却空気が流出して主ガス流れに合
流する。FIG. 3 is a partial view of the outlet slot portion at the trailing edge of the wing. As shown in FIG. 3, the end surface of the pedestal 16 is provided flush with the trailing edge of the wing.
Hole 15 formed in the gap between the pedestal 16 and
As indicated by the arrows, the cooling air flows out and merges with the main gas flow.
【０００４】[0004]
【発明が解決しようとする課題】前記の従来の中空ター
ビンの翼の後縁端面においては、ペデスタルとペデスタ
ル間の隙間に形成される穴によって、厚肉部と薄肉部が
交互に形成されている。そのため温度変化が生じた場
合、放熱又は加熱速度に差異が生じ、翼後縁端面の薄肉
部に局所的な応力集中が生じ、翼の後縁端にクラック等
の発生するおそれがある。At the trailing edge of the blade of the above-mentioned conventional hollow turbine, thick portions and thin portions are alternately formed by holes formed in the gap between the pedestals. . Therefore, when a temperature change occurs, a difference occurs in heat radiation or heating rate, local stress concentration occurs in a thin portion of the trailing edge of the blade, and cracks or the like may occur at the trailing edge of the blade.
【０００５】本発明はこの問題点を解消するためになさ
れたものである。The present invention has been made to solve this problem.
【０００６】[0006]
【課題を解決するための手段】本発明の中空ガスタービ
ン翼は、翼後縁の出口スロット部にあるペデスタルの出
口端を１〜数ｍｍだけ翼の後縁端面から翼側に離して設
け、前記ペデスタルの周囲をフレキシブルに作用する薄
肉部で囲み、翼後縁端面をすべてフレキシブルに作用す
る薄肉部で形成している。According to the hollow gas turbine blade of the present invention, the outlet end of the pedestal at the outlet slot portion of the blade trailing edge is provided at a distance of 1 mm to several mm from the trailing edge end face of the blade to the blade side. The periphery of the pedestal is surrounded by a thin wall that acts flexibly, and the entire trailing edge of the wing is flexibly actuated.
That it is formed by thin-walled portion.
【０００７】本発明においては、以上のように、ペデス
タルが翼後縁端面から翼側に１〜数ｍｍ移され、前記ペ
デスタルの周囲をフレキシブルに作用する薄肉部で囲ん
でいるので、翼後縁端面はすべてフレキシブルに作用す
る薄肉部で形成され、これにより翼後縁端面はすべて薄
肉部の構造となる。従って、薄肉部がフレキシブルに作
用して翼後縁部に発生する応力集中が緩和され、翼後縁
端面におけるクラック等の発生を防止することができ
る。In the present invention, as described above, the pedestal is moved from the trailing edge end face to the wing side by one to several mm and the pedestal is surrounded by the thin portion which acts flexibly, so that the trailing edge face is All work flexibly
That it is formed by the thin wall portion, comprising all trailing edge end face structure of the thin portion thereby. Accordingly, the concentration of stress generated at the trailing edge of the blade due to the thin portion acting flexibly is reduced, and the occurrence of cracks and the like at the trailing edge of the blade can be prevented.
【０００８】[0008]
【発明の実施の形態】本発明の実施の一形態を図１によ
って説明する。本実施の形態は、図２及び図３に示され
る従来の中空ガスタービン動翼を次のように改良したも
のである。即ち、出口スロット部にあるペデスタル１６
の出口端は所定の長さｌだけ翼の後縁端面２０から翼側
に離されている。DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of the present invention will be described with reference to FIG. This embodiment is an improvement of the conventional hollow gas turbine blade shown in FIGS. 2 and 3 as follows. That is, the pedestal 16 in the exit slot portion
Is separated from the trailing edge end face 20 of the blade by a predetermined length l toward the blade.
【０００９】このようにすることによって、ペデスタル
の周囲に薄肉部によって囲まれ、かつ翼後縁端面２０は
薄肉部で形成されることになる。この薄肉部はフレキシ
ブルに作用して翼後縁端面２０における局所的な応力集
中の発生が緩和され、翼後縁端面２０にクラック等が発
生することを防止することができる。In this manner, the pedestal is surrounded by the thin portion and the blade trailing edge end face 20 is formed by the thin portion. The thin portion acts flexibly to reduce local stress concentration on the wing trailing edge end face 20 and to prevent cracks and the like from occurring on the wing trailing edge end face 20.
【００１０】前記長さｌは実際は１〜数mm程度とするこ
とが望ましい。本実施の形態は、前記のように、翼後縁
端面で高い応力を発生させないこと、つまり、翼後縁端
面より内側で高い応力を発生させることにより、翼後縁
端面からのクラック発生を防止するようにしたものであ
り、この作用を発揮することができるように長さｌが選
択される。In practice, it is desirable that the length 1 is about 1 to several mm. As described above, this embodiment does not generate high stress on the wing trailing edge end face, that is, generates high stress inside the wing trailing edge end face, thereby preventing cracks from occurring from the wing trailing edge end face. The length l is selected so that this action can be exerted.
【００１１】なお、前記の本発明の実施の形態は、中空
ガスタービン動翼に係るものであるが、本発明は中空ガ
スタービン静翼に適用することもできる。The above embodiment of the present invention relates to a hollow gas turbine blade, but the present invention can also be applied to a hollow gas turbine stationary blade.
【００１２】[0012]
【発明の効果】本発明になる中空タービン翼によれば、
翼後縁端面における局所的な応力集中が緩和され、熱応
力を低減して、翼後縁端面におけるクラックの発生等を
防止することができる。従って、翼の信頼性の向上に寄
与する効果は大きい。According to the hollow turbine blade of the present invention,
The local stress concentration on the trailing edge of the blade is alleviated, the thermal stress is reduced, and the occurrence of cracks on the trailing edge of the blade can be prevented. Therefore, the effect of improving the reliability of the blade is great.
【図１】図１（ａ）は本発明の実施の一形態の出口スロ
ット部の部分図、図１（ｂ）は図１（ａ）のＡ−Ａ矢視
断面図である。FIG. 1A is a partial view of an outlet slot according to an embodiment of the present invention, and FIG. 1B is a cross-sectional view taken along the line AA of FIG. 1A.
【図２】従来の中空ガスタービン動翼の断面図である。FIG. 2 is a sectional view of a conventional hollow gas turbine blade.
【図３】図３（ａ）は従来の中空ガスタービン動翼の出
口スロット部の部分図、図３（ｂ）は図３（ａ）のＢ−
Ｂ矢視断面図である。3 (a) is a partial view of an outlet slot portion of a conventional hollow gas turbine blade, and FIG. 3 (b) is a sectional view taken along line B-B of FIG. 3 (a).
FIG.
１４ ピンフィン １５ 穴 １６ ペデスタル ２０ 翼後縁端面 14 Pin Fin 15 Hole 16 Pedestal 20 Wing Trailing Edge
───────────────────────────────────────────────────── フロントページの続き (56)参考文献 特開 昭55−107004（ＪＰ，Ａ) 特開 昭55−107005（ＪＰ，Ａ) 特開 昭62−258103（ＪＰ，Ａ) ──────────────────────────────────────────────────続 き Continuation of the front page (56) References JP-A-55-107004 (JP, A) JP-A-55-107005 (JP, A) JP-A-62-258103 (JP, A)
Claims (1)
ルの出口端を１〜数ｍｍだけ翼の後縁端面から翼側に離
して設け、前記ペデスタルの周囲をフレキシブルに作用
する薄肉部で囲み、翼後縁端面をすべてフレキシブルに
作用する薄肉部で形成したことを特徴とする中空ガスタ
ービン翼。1. An outlet end of a pedestal in an outlet slot portion of a trailing edge of a blade is provided at a distance of 1 mm to several mm from a trailing edge end surface of the blade to a side of the blade to flexibly act around the pedestal.
To make the entire trailing edge of the wing flexible.
A hollow gas turbine blade formed of a working thin wall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP20324495A JP3241241B2 (en) | 1995-08-09 | 1995-08-09 | Hollow gas turbine blades |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP20324495A JP3241241B2 (en) | 1995-08-09 | 1995-08-09 | Hollow gas turbine blades |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0953405A JPH0953405A (en) | 1997-02-25 |
| JP3241241B2 true JP3241241B2 (en) | 2001-12-25 |
Family
ID=16470827
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP20324495A Expired - Lifetime JP3241241B2 (en) | 1995-08-09 | 1995-08-09 | Hollow gas turbine blades |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3241241B2 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6132169A (en) * | 1998-12-18 | 2000-10-17 | General Electric Company | Turbine airfoil and methods for airfoil cooling |
| FR2852877B1 (en) * | 2003-03-27 | 2005-05-06 | Essilor Int | METHOD FOR DETOURING A GLASS OF A GLASSES |
| US7175386B2 (en) † | 2003-12-17 | 2007-02-13 | United Technologies Corporation | Airfoil with shaped trailing edge pedestals |
| JP6671149B2 (en) * | 2015-11-05 | 2020-03-25 | 三菱日立パワーシステムズ株式会社 | Turbine blade and gas turbine, intermediate product of turbine blade, and method of manufacturing turbine blade |
-
1995
- 1995-08-09 JP JP20324495A patent/JP3241241B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0953405A (en) | 1997-02-25 |
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