JP3592932B2 - Contact structure between gas turbine vane and blade ring - Google Patents
Contact structure between gas turbine vane and blade ring Download PDFInfo
- Publication number
- JP3592932B2 JP3592932B2 JP14127798A JP14127798A JP3592932B2 JP 3592932 B2 JP3592932 B2 JP 3592932B2 JP 14127798 A JP14127798 A JP 14127798A JP 14127798 A JP14127798 A JP 14127798A JP 3592932 B2 JP3592932 B2 JP 3592932B2
- Authority
- JP
- Japan
- Prior art keywords
- blade ring
- blade
- outer shroud
- gas turbine
- contact
- 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
- 230000002093 peripheral effect Effects 0.000 claims description 8
- 239000007789 gas Substances 0.000 description 14
- 239000002184 metal Substances 0.000 description 5
- 230000007423 decrease Effects 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Description
【０００１】
【発明の属する技術分野】
本発明はガスタービン静翼と翼環の接触構造に関し、翼環に伝えられる熱を少くし、翼環の温度上昇を抑え、これにより翼環の熱膨張のたわみを小さくするようにしたものである。
【０００２】
【従来の技術】
図４は従来のガスタービン静翼の翼環部分を示す断面図である。図において、１は静翼、２はその外側シュラウドであり、３はシール空気用チューブで、翼内部を外側シュラウド２から内側に向って貫通して設けられている。４は翼環であり、５は翼環フランジで、静翼１の外側シュラウド２を翼環４に支持している。この翼環４及び翼環フランジ５は円環状の構造で、翼環フランジ５で外側シュラウド２のフランジ６と係合し、外側シュラウド２を固定し、支持している。
【０００３】
７は接触面（Ａ）であり、翼環フランジ５と外側シュラウド２の円周状の外周面と接触する面である。８は嵌り込み部である。９も反対側（ガス流れ前流側）の外側シュラウド２と翼環４との嵌り込み部であるが、翼環４にボルト１１で取付けられたブロック１０により外側シュラウド２を支持する構造であり、翼環４への静翼１からの熱伝達を減少させる観点からは本発明の対象外の範囲となるのでこれ以上の説明は省略する。
【０００４】
上記構成のガスタービン静翼において、ガスタービンの運転中では高温の燃焼ガスが流れて静翼１は高温に加熱され、その熱は外側シュラウド２にも伝えられる。外側シュラウド２は翼環４に翼環フランジ５とブロック１０とで前後で支持されており、翼環４とは接触面（Ａ）７と接触し、静翼１からの熱が翼環４に伝えられる。
【０００５】
この翼環４で外側シュラウド２を支持する部分のうち、ブロック１０は翼環４とは分割された構造であり、熱伝達の面からすると翼環フランジ５と外側フランジ２とが接触する接触面（Ａ）７の部分が最も問題となる部分であり、これら接触面からの翼環４に伝わる熱を少くし、翼環４の温度上昇をできるだけ少くする対策が望まれていた。
【０００６】
【発明が解決しようとする課題】
前述のように従来のガスタービンの静翼においては、静翼から翼環への熱伝達により翼環のメタル温度が上昇し、翼環が過度の熱膨張により歪む恐れがあり、できるだけ翼環の温度上昇を防ぐ必要がある。特に、この翼環４への熱伝達が大きい部分は翼環フランジ５と外側フランジ２とが直接接触する接触面（Ａ）７であり、この部分は外側フランジ２が周方向全長にわたって所定の幅で翼環４に接しており、接触面積も大きく、かつ外側シュラウド２の肉厚も小さく、高温ガス流の熱伝達の影響を最も受けやすい部分である。このような部分をできるだけ熱伝達を受けにくくし、かつ強度的にも満足するような形状にすることが必要である。
【０００７】
そこで本発明は静翼を支持する翼環との接合部分の熱伝達を少くし、翼環のメタル温度上昇を防ぐことのできるガスタービン静翼と翼環との接触構造を提供し、翼環が過度の熱膨張によりたわむことのないようにすることを課題としてなされたものである。
【０００８】
【課題を解決するための手段】
本発明は前述の課題を解決するために次の手段を提供する。
【０００９】
静翼の外側シュラウドを支持する翼環フランジと同外側シュラウドの外側周面との接触面において、同接触面の前記翼環フランジ側の面に周方向で互にほぼ平行して配列し、軸方向に伸びる複数の溝を形成したことを特徴とするガスタービン静翼と翼環の接触構造。
【００１０】
本発明の静翼と翼環の接触構造は、外側シュラウド外側周面と翼環フランジとの接合面において、翼環側に複数の溝を設けたので、この溝の幅と長さ、溝の数で決まる面積の分だけ接触面積が減少し、伝熱面積が小さくなる。従って、この接触面において外側シュラウドから翼環に伝達される熱が少くなり、翼環のメタル温度上昇をこの分抑えることができ、翼環の熱膨張によるたわみを防止することができる。
【００１１】
【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に基づいて具体的に説明する。図１は本発明の実施の一形態に係るガスタービン静翼の接触構造の部分断面図である。図において符号１，２，４乃至８は図４に示す従来例と同じ部分であるので同一符号をそのまま引用し、詳しい説明は省略するが、本発明の特徴部分は符号１０で示す溝を設けたところにある。
【００１２】
図１において、接触面（Ａ）７は外側シュラウド２と翼環４とが直接接触する部分であり、熱伝達の影響を最も受ける部分である。
【００１３】
この接触面（Ａ）７には溝１０が周面にほぼ平行に複数列加工されている。図２は図１のＸ−Ｘ断面図、図３はこの翼環フランジ５の接触面（Ａ）７の部分的な斜視図である。両図において、翼環フランジ５の接触面１０にはその全周面に所定間隔ｔで溝１０が加工されている。なお、この溝１０は、かならずしも平行でなくても良く、互に傾斜しても良く、又間隔ｔも一定にしなくても良いものであるが、加工性の面からは平行の方が好ましい。
【００１４】
溝１０を翼環４の接触面（Ａ）７に設けると、外側シュラウド２の面と接する翼環フランジ５の面積が溝１０の長さと幅、数で決まる面積分だけ少なくなり、その分だけ接触面積を少くすることができる。即ち、図２において溝１０の長さをＬ、溝幅をｄとし、溝１０の全数をＮとすれば、接触面積はＬｄＮ分だけ減少することになる。
【００１５】
接触面（Ａ）７における接触面積が減少するとその伝達面積が少くなり、その分、外側シュラウド２から翼環４へ伝わる熱量が少くなり翼環４の熱的影響を小さくできる。なお、この溝１０Ｎの数、間隔ｔ、幅ｄは特に限定するものではなく、外側シュラウド２の形状、高温燃焼ガスのもれ、強度的な影響等を考慮して決定すれば良いものである。又、溝１０の断面形状も半円形、四角形、等どのような形状でも良いが、強度の面からは半円形又はなだらかな曲面が好ましい。
【００１６】
以上説明の実施の形態によれば、静翼１の外側シュラウド２と翼環４との接触面（Ａ）７の翼環フランジ５側に複数の溝１０を周方向に配列したので、外側シュラウド２と翼環フランジ５間の接触面積が減少し、外側シュラウド２から翼環に伝わる熱が少くなり、翼環４のメタル温度の上昇を抑える。これにより翼環が過度の熱膨張のためにたわみ強度的に無理な熱応力の発生を防止できる。
【００１７】
【発明の効果】
本発明のガスタービン静翼と翼環の接触構造は、静翼の外側シュラウドを支持する翼環フランジと同外側シュラウドの外側周面との接触面において、同接触面の前記翼環フランジ側の面に周方向で互にほぼ平行して配列し、軸方向に伸びる複数の溝を形成したことを特徴としている。このような構造により、外側フランジ外側周面と翼環フランジ間の接触面積が減少し、外側シュラウドから翼環に伝わる熱が少くなり、翼環のメタル温度上昇が抑えられ、翼環が過度の熱膨張のためにたわむことがなくなる。
【図面の簡単な説明】
【図１】本発明の実施の一形態に係るガスタービン静翼と翼環の接触構造を示す断面図である。
【図２】図１におけるＸ−Ｘ矢視図である。
【図３】本発明の実施の一形態に係るガスタービン静翼と翼環の接触構造の翼環部の斜視図である。
【図４】従来のガスタービン静翼と翼環の接触構造を示す断面部である。
【符号の説明】
１ 静翼
２ 外側シュラウド
４ 翼環
５ 翼環フランジ
６ 外側シュラウドフランジ
７ 接触面（Ａ）
８ 嵌り込み部
１０ 溝[0001]
TECHNICAL FIELD OF THE INVENTION
The present invention relates to a contact structure between a gas turbine vane and a blade ring, in which heat transferred to the blade ring is reduced, temperature rise of the blade ring is suppressed, and thereby, deflection of thermal expansion of the blade ring is reduced. is there.
[0002]
[Prior art]
FIG. 4 is a sectional view showing a blade ring portion of a conventional gas turbine stationary blade. In the drawing, reference numeral 1 denotes a stationary blade, 2 denotes an outer shroud thereof, and 3 denotes a tube for sealing air, which is provided so as to penetrate the inside of the blade from the outer shroud 2 inward. Reference numeral 4 denotes a blade ring, and reference numeral 5 denotes a blade ring flange, which supports the outer shroud 2 of the stationary blade 1 on the blade ring 4. The blade ring 4 and the blade ring flange 5 have an annular structure, and engage with the flange 6 of the outer shroud 2 at the blade ring flange 5 to fix and support the outer shroud 2.
[0003]
Reference numeral 7 denotes a contact surface (A) which is in contact with the blade ring flange 5 and the circumferential outer peripheral surface of the outer shroud 2. 8 is a fitting portion. Reference numeral 9 also denotes a fitting portion between the outer shroud 2 on the opposite side (the upstream side of the gas flow) and the blade ring 4, and has a structure in which the outer shroud 2 is supported by a block 10 attached to the blade ring 4 with bolts 11. From the viewpoint of reducing the heat transfer from the stationary blade 1 to the blade ring 4, the range is out of the scope of the present invention, and further description will be omitted.
[0004]
In the gas turbine stationary blade having the above configuration, high-temperature combustion gas flows during operation of the gas turbine, and the stationary blade 1 is heated to a high temperature, and the heat is also transmitted to the outer shroud 2. The outer shroud 2 is supported by the blade ring 4 at the front and rear by a blade ring flange 5 and a block 10. Reportedly.
[0005]
Among the portions that support the outer shroud 2 with the blade ring 4, the block 10 has a structure separated from the blade ring 4, and from the viewpoint of heat transfer, a contact surface where the blade ring flange 5 contacts the outer flange 2. (A) 7 is the most problematic part, and measures to reduce the heat transmitted from these contact surfaces to the blade ring 4 and minimize the temperature rise of the blade ring 4 have been desired.
[0006]
[Problems to be solved by the invention]
As described above, in the conventional gas turbine stationary blade, the heat transfer from the stationary blade to the blade ring increases the metal temperature of the blade ring, and the blade ring may be distorted due to excessive thermal expansion. It is necessary to prevent temperature rise. In particular, a portion where the heat transfer to the blade ring 4 is large is a contact surface (A) 7 where the blade ring flange 5 and the outer flange 2 come into direct contact with each other. The outer shroud 2 has a small contact area with the blade ring 4 and has a small wall thickness, and is most susceptible to the heat transfer of the high-temperature gas flow. It is necessary to make such a portion less susceptible to heat transfer as much as possible and to have a shape that satisfies the strength.
[0007]
Therefore, the present invention provides a contact structure between a gas turbine stator blade and a blade ring which can reduce heat transfer at a joint portion with a blade ring supporting a stator blade and can prevent a rise in metal temperature of the blade ring. The purpose of the present invention is to prevent the steel from being bent by excessive thermal expansion.
[0008]
[Means for Solving the Problems]
The present invention provides the following means for solving the above-mentioned problems.
[0009]
At the contact surface between the blade ring flange that supports the outer shroud of the stator blade and the outer peripheral surface of the outer shroud, the contact surface is arranged substantially parallel to one another in the circumferential direction on the blade ring flange side surface, A contact structure between a gas turbine vane and a blade ring, wherein a plurality of grooves extending in a direction are formed.
[0010]
In the contact structure of the stator vane and the blade ring of the present invention, since a plurality of grooves are provided on the blade ring side at the joint surface between the outer peripheral surface of the outer shroud and the blade ring flange, the width and length of the grooves, The contact area is reduced by the area determined by the number, and the heat transfer area is reduced. Therefore, the heat transferred from the outer shroud to the blade ring at this contact surface is reduced, the rise in metal temperature of the blade ring can be suppressed by this amount, and the deflection due to the thermal expansion of the blade ring can be prevented.
[0011]
BEST MODE FOR CARRYING OUT THE INVENTION
Hereinafter, embodiments of the present invention will be specifically described with reference to the drawings. FIG. 1 is a partial sectional view of a contact structure of a gas turbine stationary blade according to an embodiment of the present invention. In the figure, reference numerals 1, 2, 4 to 8 are the same as those in the conventional example shown in FIG. 4, and therefore the same reference numerals are used as they are, and detailed description is omitted. There.
[0012]
In FIG. 1, the contact surface (A) 7 is a portion where the outer shroud 2 and the blade ring 4 are in direct contact, and is a portion that is most affected by heat transfer.
[0013]
The contact surface (A) 7 is formed with a plurality of rows of grooves 10 substantially parallel to the peripheral surface. FIG. 2 is a sectional view taken along line XX of FIG. 1, and FIG. 3 is a partial perspective view of a contact surface (A) 7 of the blade ring flange 5. In both figures, grooves 10 are formed on the contact surface 10 of the blade ring flange 5 at a predetermined interval t on the entire peripheral surface. The grooves 10 are not necessarily parallel to each other, may be inclined with respect to each other, and the interval t does not need to be constant, but is preferably parallel from the viewpoint of workability.
[0014]
When the groove 10 is provided on the contact surface (A) 7 of the blade ring 4, the area of the blade ring flange 5 in contact with the surface of the outer shroud 2 is reduced by an area determined by the length, width, and number of the groove 10. The contact area can be reduced. That is, in FIG. 2, if the length of the groove 10 is L, the groove width is d, and the total number of the grooves 10 is N, the contact area is reduced by LdN.
[0015]
When the contact area on the contact surface (A) 7 decreases, the transmission area decreases, and accordingly, the amount of heat transmitted from the outer shroud 2 to the blade ring 4 decreases, so that the thermal influence of the blade ring 4 can be reduced. The number, interval t, and width d of the grooves 10N are not particularly limited, and may be determined in consideration of the shape of the outer shroud 2, leakage of high-temperature combustion gas, influence of strength, and the like. . Further, the cross-sectional shape of the groove 10 may be any shape such as a semicircle, a square, etc., but a semicircle or a gentle curved surface is preferable from the viewpoint of strength.
[0016]
According to the embodiment described above, the plurality of grooves 10 are arranged in the circumferential direction on the blade ring flange 5 side of the contact surface (A) 7 between the outer shroud 2 of the stator blade 1 and the blade ring 4, so that the outer shroud is formed. The contact area between the outer ring 2 and the blade ring flange 5 is reduced, the heat transmitted from the outer shroud 2 to the blade ring is reduced, and an increase in the metal temperature of the blade ring 4 is suppressed. As a result, it is possible to prevent the blade ring from flexing due to excessive thermal expansion and to prevent generation of thermal stress that is unreasonable in terms of strength.
[0017]
【The invention's effect】
The contact structure between the gas turbine stator blade and the blade ring of the present invention is a contact surface between the blade ring flange that supports the outer shroud of the stator blade and the outer peripheral surface of the outer shroud. It is characterized in that a plurality of grooves are formed on the surface so as to be arranged substantially parallel to each other in the circumferential direction and to extend in the axial direction. With such a structure, the contact area between the outer peripheral surface of the outer flange and the blade ring flange is reduced, the heat transmitted from the outer shroud to the blade ring is reduced, the rise in metal temperature of the blade ring is suppressed, and the blade ring becomes excessive. No deflection due to thermal expansion.
[Brief description of the drawings]
FIG. 1 is a cross-sectional view illustrating a contact structure between a gas turbine stationary blade and a blade ring according to an embodiment of the present invention.
FIG. 2 is a view taken along the line XX in FIG.
FIG. 3 is a perspective view of a blade ring portion of a gas turbine stator blade and blade ring contact structure according to an embodiment of the present invention.
FIG. 4 is a sectional view showing a conventional contact structure between a gas turbine stationary blade and a blade ring.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 Stator blade 2 Outer shroud 4 Blade ring 5 Blade ring flange 6 Outer shroud flange 7 Contact surface (A)
8 Fitting part 10 Groove
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14127798A JP3592932B2 (en) | 1998-05-22 | 1998-05-22 | Contact structure between gas turbine vane and blade ring |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14127798A JP3592932B2 (en) | 1998-05-22 | 1998-05-22 | Contact structure between gas turbine vane and blade ring |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH11336505A JPH11336505A (en) | 1999-12-07 |
| JP3592932B2 true JP3592932B2 (en) | 2004-11-24 |
Family
ID=15288159
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP14127798A Expired - Lifetime JP3592932B2 (en) | 1998-05-22 | 1998-05-22 | Contact structure between gas turbine vane and blade ring |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3592932B2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2952965B1 (en) * | 2009-11-25 | 2012-03-09 | Snecma | INSULATING A CIRCONFERENTIAL SIDE OF AN EXTERNAL TURBOMACHINE CASTER WITH RESPECT TO A CORRESPONDING RING SECTOR |
-
1998
- 1998-05-22 JP JP14127798A patent/JP3592932B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPH11336505A (en) | 1999-12-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP3912935B2 (en) | High-pressure turbine stator ring for turbine engines | |
| JP3600912B2 (en) | Combustor liner seal structure | |
| JP3947227B2 (en) | Gas turbine engine shroud seal | |
| JP4008212B2 (en) | Hollow structure with flange | |
| US11009039B2 (en) | Intermittent spigot joint for gas turbine engine casing connection | |
| US20090191053A1 (en) | Diaphragm and blades for turbomachinery | |
| JP2003003863A (en) | Exhaust frame, gas turbine engine and manufacturing method thereof | |
| JP4660051B2 (en) | Turbine | |
| JP2004530832A (en) | Segmented turbine vane support structure | |
| JP2005534890A (en) | Heat-free rear frame for transition ducts | |
| JPH08246806A (en) | Stator for turbomachinery | |
| CA2601934A1 (en) | Gas turbine combustor exit duct and hp vane interface | |
| JP2007513281A (en) | Peristaltic joint between combustor wall and nozzle platform | |
| US10662795B2 (en) | Rotary assembly for a turbomachine | |
| JP2000054804A (en) | Low distortion shroud for turbine | |
| KR20160064018A (en) | First stage turbine vane arrangement | |
| JP4812553B2 (en) | Thermal alignment clip | |
| JP4890145B2 (en) | Thermally compliant turbine shroud assembly | |
| JP4912786B2 (en) | Thermally matched turbine shroud mounting assembly | |
| EP1040256B1 (en) | Support for a turbine stator assembly | |
| JP4293419B2 (en) | Auxiliary seal for string hinge seal in gas turbine | |
| JP4953725B2 (en) | Thermally compliant turbine shroud mount | |
| JP2003525381A (en) | Turbine equipment | |
| JP3592932B2 (en) | Contact structure between gas turbine vane and blade ring | |
| KR20190143350A (en) | Curved seal for adjacent gas turbine components |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A977 | Report on retrieval |
Free format text: JAPANESE INTERMEDIATE CODE: A971007 Effective date: 20040315 |
|
| A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20040518 |
|
| TRDD | Decision of grant or rejection written | ||
| A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20040727 |
|
| A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20040826 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20080903 Year of fee payment: 4 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20080903 Year of fee payment: 4 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20090903 Year of fee payment: 5 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20090903 Year of fee payment: 5 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20100903 Year of fee payment: 6 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110903 Year of fee payment: 7 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110903 Year of fee payment: 7 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120903 Year of fee payment: 8 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120903 Year of fee payment: 8 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20130903 Year of fee payment: 9 |
|
| S111 | Request for change of ownership or part of ownership |
Free format text: JAPANESE INTERMEDIATE CODE: R313111 |
|
| R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| EXPY | Cancellation because of completion of term |