JPH04308328A - Stator blade support structure of variable stator blade gas turbine - Google Patents
Stator blade support structure of variable stator blade gas turbineInfo
- Publication number
- JPH04308328A JPH04308328A JP9940491A JP9940491A JPH04308328A JP H04308328 A JPH04308328 A JP H04308328A JP 9940491 A JP9940491 A JP 9940491A JP 9940491 A JP9940491 A JP 9940491A JP H04308328 A JPH04308328 A JP H04308328A
- Authority
- JP
- Japan
- Prior art keywords
- sleeve
- gas turbine
- stator blade
- support structure
- shaft
- 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
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 16
- 239000000956 alloy Substances 0.000 claims abstract description 16
- 229910052581 Si3N4 Inorganic materials 0.000 claims abstract description 10
- HQVNEWCFYHHQES-UHFFFAOYSA-N silicon nitride Chemical compound N12[Si]34N5[Si]62N3[Si]51N64 HQVNEWCFYHHQES-UHFFFAOYSA-N 0.000 claims abstract description 8
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 18
- 229910052759 nickel Inorganic materials 0.000 claims description 9
- 229910002077 partially stabilized zirconia Inorganic materials 0.000 claims description 8
- 229910017052 cobalt Inorganic materials 0.000 claims description 6
- 239000010941 cobalt Substances 0.000 claims description 6
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 5
- 230000003647 oxidation Effects 0.000 claims description 2
- 238000007254 oxidation reaction Methods 0.000 claims description 2
- 230000002093 peripheral effect Effects 0.000 claims 1
- 238000001816 cooling Methods 0.000 abstract description 5
- 229910002076 stabilized zirconia Inorganic materials 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 37
- 239000000567 combustion gas Substances 0.000 description 8
- 239000000463 material Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 3
- 229910001026 inconel Inorganic materials 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000007664 blowing Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】0001
【産業上の利用分野】本発明は可変静翼ガスタービンの
静翼支持構造に関するものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a stator blade support structure for a variable stator blade gas turbine.
【０００２】0002
【従来の技術】従来、ガスタービンの高効率化を図るた
めに、燃焼ガス流通方向に対して、ガスタービンの静翼
の角度を調整できるようにした可変静翼ガスタービンが
ある。2. Description of the Related Art Conventionally, in order to improve the efficiency of gas turbines, there have been variable stator vane gas turbines in which the angle of the stator blades of the gas turbine can be adjusted with respect to the combustion gas flow direction.
【０００３】図３は従来の可変静翼ガスタービンの静翼
支持構造の一例を示すものであり、図中３はガスタービ
ンのケーシング４の外周部に取付けられたスリーブホル
ダ、５はスリーブホルダ３に嵌装されたガスタービンの
径方向に延びるスリーブ、２はガスタービンの静翼１の
基部に形成され且つ前記スリーブ５に回動可能に支持さ
れた軸部を示している。FIG. 3 shows an example of a stator blade support structure of a conventional variable stator blade gas turbine. In the figure, 3 is a sleeve holder attached to the outer periphery of a casing 4 of the gas turbine, and 5 is a sleeve holder 3. A sleeve 2 extending in the radial direction of the gas turbine fitted in the gas turbine 2 indicates a shaft portion formed at the base of the stationary blade 1 of the gas turbine and rotatably supported by the sleeve 5.
【０００４】上述した構成の静翼支持構造を有する可変
静翼ガスタービンでは、軸部２を回動させることにより
、燃焼ガスＧに対する静翼１の角度を調整するようにな
っている。In the variable stator blade gas turbine having the stator blade support structure configured as described above, the angle of the stator blade 1 with respect to the combustion gas G is adjusted by rotating the shaft portion 2.
【０００５】また、軸部２がケーシング４を貫通する部
分には、間隙１３が形成されており、ガスタービンの運
転中においては、ケーシング４に形成された図示されて
いない流路から前記間隙１３へ冷却用の空気を供給して
、軸部２、スリーブ５等の冷却を行い、静翼支持部の焼
付きを防止している。Further, a gap 13 is formed in the portion where the shaft portion 2 passes through the casing 4, and during operation of the gas turbine, the gap 13 is formed from a flow path (not shown) formed in the casing 4. Cooling air is supplied to cool the shaft portion 2, sleeve 5, etc., and prevent seizing of the stationary blade support portion.
【０００６】[0006]
【発明が解決しようとする課題】ところが、上述した静
翼支持構造では下記のような問題が生じる。However, the above stator blade support structure has the following problems.
【０００７】（１）間隙１３の寸法を大きく形成すると
、ガスタービンの運転時に、燃焼ガスＧのガス圧による
空気荷重が静翼１に作用して軸部２が撓み、該軸部２が
スリーブ５内周面に押付けられて軸部２、スリーブ５に
過大摩耗または固着が生じ、最終的には静翼１の円滑な
回動が行えなくなる。(1) If the size of the gap 13 is made large, the air load due to the gas pressure of the combustion gas G acts on the stator vane 1 during operation of the gas turbine, causing the shaft portion 2 to bend, causing the shaft portion 2 to bend. 5 is pressed against the inner circumferential surface of the shaft 2 and the sleeve 5, causing excessive wear or sticking, and eventually the stationary blade 1 cannot rotate smoothly.
【０００８】（２）軸部２、スリーブ５等に冷却用の空
気を吹付けるための流路をケーシング４に形成するので
、ケーシング４構造が複雑化し、且つエンジンの性能低
下を生ずる。(2) Since a flow path for blowing cooling air to the shaft portion 2, sleeve 5, etc. is formed in the casing 4, the structure of the casing 4 becomes complicated and the performance of the engine is lowered.
【０００９】本発明は上述した問題点を解決するもので
、可変静翼タービンの静翼支持部材を強制的に冷却する
ことなく、静翼支持部材の焼付きを防止し、また、摩耗
を抑制することを目的としている。The present invention solves the above-mentioned problems, and prevents seizure of the stator blade support member of a variable stator blade turbine and suppresses wear without forcibly cooling the stator blade support member of a variable stator blade turbine. It is intended to.
【００１０】0010
【課題を解決するための手段】本発明の請求項１に記載
した可変静翼ガスタービンの静翼支持構造は、ガスター
ビンのケーシング外周部に取付けたスリーブホルダと、
該スリーブホルダに嵌装されたガスタービンの径方向に
延びるスリーブと、ガスタービンの静翼の基部に固着さ
れ且つ前記スリーブに回動可能に支持された軸部を備え
た可変静翼ガスタービンの静翼支持構造において、前記
軸部をコバルト系耐熱合金により形成し、また、スリー
ブを窒化硅素、あるいは部分安定化ジルコニアにより形
成したものである。[Means for Solving the Problems] A stator blade support structure for a variable stator blade gas turbine according to claim 1 of the present invention includes a sleeve holder attached to the outer circumference of a casing of a gas turbine;
A variable stator blade gas turbine comprising: a sleeve extending in the radial direction of the gas turbine fitted in the sleeve holder; and a shaft portion fixed to a base of a stator blade of the gas turbine and rotatably supported by the sleeve. In the stationary blade support structure, the shaft portion is formed of a cobalt-based heat-resistant alloy, and the sleeve is formed of silicon nitride or partially stabilized zirconia.
【００１１】本発明の請求項２に記載した可変静翼ガス
タービンの静翼支持構造は、軸部、スリーブを請求項１
に記載した可変静翼ガスタービンの静翼支持構造のもの
に替えて、軸部をニッケル系耐熱合金により形成し、ま
た、スリーブを部分安定化ジルコニアにより形成したも
のである。The stator blade support structure for a variable stator blade gas turbine according to claim 2 of the present invention includes a shaft portion and a sleeve as set forth in claim 1.
In place of the stator blade support structure of the variable stator vane gas turbine described in 1., the shaft portion is formed of a nickel-based heat-resistant alloy, and the sleeve is formed of partially stabilized zirconia.
【００１２】本発明の請求項３に記載した可変静翼ガス
タービンの静翼支持構造は、軸部、スリーブを請求項１
に記載した可変静翼ガスタービンの静翼支持構造のもの
に替えて、軸部をニッケル系耐熱合金により形成したう
え、軸部の表面にクロマイズド処理及び酸化処理を施し
、また、スリーブを窒化硅素により形成したものである
。The stator blade support structure for a variable stator blade gas turbine according to claim 3 of the present invention includes a shaft portion and a sleeve as defined in claim 1.
In place of the stator blade support structure of the variable stator vane gas turbine described in 1., the shaft part is made of a nickel-based heat-resistant alloy, the surface of the shaft part is subjected to chromized treatment and oxidation treatment, and the sleeve is made of silicon nitride. It was formed by
【００１３】本発明の請求項４に記載した可変静翼ガス
タービンの静翼支持構造は、軸部、スリーブを請求項１
に記載した可変静翼ガスタービンの静翼支持構造のもの
に替えて、軸部をニッケル系耐熱合金により形成したう
え、軸部にコバルト系耐熱合金により形成した筒状の部
材を外嵌固着せしめ、また、スリーブを窒化硅素、ある
いは部分安定化ジルコニアにより形成したものである。The stator blade support structure for a variable stator blade gas turbine according to claim 4 of the present invention includes a shaft portion and a sleeve as defined in claim 1.
Instead of the stator blade support structure of the variable stator vane gas turbine described in , the shaft portion is formed of a nickel-based heat-resistant alloy, and a cylindrical member formed of a cobalt-based heat-resistant alloy is externally fitted and fixed to the shaft portion. In addition, the sleeve is made of silicon nitride or partially stabilized zirconia.
【００１４】[0014]
【作用】本発明の請求項１，２，３，４に記載したいず
れの可変静翼ガスタービンの静翼支持構造においても、
ガスタービンの運転時に軸部、スリーブ等の温度が約９
００℃前後の高温になっても焼付きが発生せず、また、
軸部、スリーブに摩耗がほとんど発生しない。[Operation] In any of the stator blade support structures for variable stator blade gas turbines described in claims 1, 2, 3, and 4 of the present invention,
When the gas turbine is operating, the temperature of the shaft, sleeve, etc. is approximately 9.
No seizure occurs even at high temperatures around 00℃, and
Almost no wear occurs on the shaft and sleeve.
【００１５】[0015]
【実施例】以下、本発明の実施例を図面を参照しつつ説
明する。Embodiments Hereinafter, embodiments of the present invention will be described with reference to the drawings.
【００１６】図１は本発明の請求項１，２，３に記載し
た可変静翼ガスタービンの静翼支持構造を示すものであ
り、図中、図３と同一の符号を付した部分は同一物を表
わしている。FIG. 1 shows a stator blade support structure for a variable stator blade gas turbine according to claims 1, 2, and 3 of the present invention. represents something.
【００１７】なお、図１において、スリーブ５は図３に
示すものより静翼１側へ延びており、軸部２、スリーブ
５は、耐熱性、耐摩耗性を有する材質によって形成され
ている。In FIG. 1, the sleeve 5 extends closer to the stationary blade 1 than the sleeve 5 shown in FIG. 3, and the shaft portion 2 and sleeve 5 are made of a material having heat resistance and wear resistance.
【００１８】図１において、６は略水平方向に延び一端
が前記軸部２の反静翼１側端部に固着された作動腕、７
はケーシング４の外周面に沿って延び且つ該ケーシング
４に固着された環状のガイド部材、８はガイド部材７に
周方向へ摺動し得るように外嵌された作動リング、９は
作動リング８に設けたガスタービンの径方向に延びる作
動軸であり、該作動軸９の反ガイド部材７側端部に形成
された球状部１０には、前記作動腕６の他端に形成した
環状の球面座１１が外嵌されている。In FIG. 1, reference numeral 6 denotes an actuating arm extending substantially horizontally and having one end fixed to the end portion of the shaft portion 2 on the side opposite to the stationary blade 1;
8 is an annular guide member extending along the outer circumferential surface of the casing 4 and fixed to the casing 4; 8 is an actuation ring fitted onto the guide member 7 so as to be able to slide in the circumferential direction; 9 is an actuation ring 8; The spherical portion 10 formed at the end of the operating shaft 9 on the side opposite to the guide member 7 has an annular spherical surface formed at the other end of the operating arm 6. A seat 11 is fitted onto the outside.
【００１９】また、前記作動リング８は図示されていな
いアクチュエータを駆動すると、周方向へ回動するよう
になっている。Further, the actuating ring 8 is configured to rotate in the circumferential direction when an actuator (not shown) is driven.
【００２０】次に、各部材の材質について説明する。Next, the materials of each member will be explained.
【００２１】静翼１、軸部２には、耐熱性、耐摩耗性に
優れたＸ４０、ＭＡＲ−Ｍ５０９等のコバルト系耐熱合
金、インコネル７１３ＬＣ等のニッケル系耐熱合金、あ
るいは該ニッケル系耐熱合金にクロマイズ表面処理及び
酸化処理を行ったものを、また、スリーブ５には、耐熱
性、耐摩耗性に優れたＳｉ３Ｎ４（窒化硅素）あるいは
ＰＳＺ（部分安定化ジルコニア）を下記表１に示すよう
な組合せで使用する。The stator blade 1 and the shaft portion 2 are made of cobalt-based heat-resistant alloys such as X40 and MAR-M509, which have excellent heat resistance and wear resistance, nickel-based heat-resistant alloys such as Inconel 713LC, or the nickel-based heat-resistant alloys. The sleeve 5 is made of Si3N4 (silicon nitride) or PSZ (partially stabilized zirconia), which has excellent heat resistance and wear resistance, as shown in Table 1 below. Use with.
【００２２】[0022]
【表１】[Table 1]
【００２３】なお、上記表１において、組合せ番号１〜
４は本発明の請求項１に、組合せ番号５は本発明の請求
項３に、組合せ番号６は本発明の請求項２に対応してい
る。[0023] In Table 1 above, combination numbers 1-
4 corresponds to claim 1 of the present invention, combination number 5 corresponds to claim 3 of the present invention, and combination number 6 corresponds to claim 2 of the present invention.
【００２４】上述した構成において、ガスタービンの運
転中に、燃焼ガス流通方向上流側から燃焼ガス流通方向
下流側へ流れる燃焼ガスＧに対して静翼１の角度を調整
するときには、図示されていないアクチュエータによっ
て作動リング８を周方向に回動させる。In the above-described configuration, when adjusting the angle of the stationary blade 1 with respect to the combustion gas G flowing from the upstream side in the combustion gas distribution direction to the downstream side in the combustion gas distribution direction during operation of the gas turbine, the The actuator rotates the actuation ring 8 in the circumferential direction.
【００２５】作動リング８の回動にともない、作動軸９
がケーシング４に対して回動すると、作動腕６を介して
軸部２が回動し、燃焼ガスＧの流通方向に対する静翼１
の角度が変化する。As the operating ring 8 rotates, the operating shaft 9
When rotates with respect to the casing 4, the shaft portion 2 rotates via the operating arm 6, and the stator blade 1 rotates in the direction of flow of the combustion gas G.
The angle of changes.
【００２６】一方、ガスタービンを運転することにより
、軸部２、スリーブホルダ３、スリーブ５の温度が約９
００℃前後の高温になっても、軸部２、スリーブ５に前
掲した表１に示すような材質の組合せを適用しているの
で、軸部２、スリーブ５に焼付きが生じることがなく、
また、静翼１に作用する燃焼ガスＧのガス圧により軸部
２がスリーブ５に押付けられても、軸部２、スリーブ５
に偏摩耗が生じることが少なく、静翼１を円滑に回動さ
せることができ、更に軸部２、スリーブ５に冷却用の空
気を吹付けなくてもよいので、ケーシング４の構造を簡
略化することができる。On the other hand, by operating the gas turbine, the temperature of the shaft portion 2, sleeve holder 3, and sleeve 5 decreases to about 9
Even at high temperatures of around 00°C, since the combination of materials shown in Table 1 above is used for the shaft 2 and sleeve 5, the shaft 2 and sleeve 5 will not seize.
Further, even if the shaft portion 2 is pressed against the sleeve 5 due to the gas pressure of the combustion gas G acting on the stator vane 1, the shaft portion 2 and the sleeve 5
The structure of the casing 4 is simplified because uneven wear is less likely to occur, the stator blade 1 can be rotated smoothly, and there is no need to blow cooling air onto the shaft 2 and sleeve 5. can do.
【００２７】図２は本発明の請求項４に記載した可変静
翼ガスタービンの静翼支持構造を示すものである。FIG. 2 shows a stator blade support structure for a variable stator blade gas turbine according to claim 4 of the present invention.
【００２８】なお、図２において、図１と同一の符号を
付した部分は同一物を表わしている。Note that in FIG. 2, parts given the same reference numerals as in FIG. 1 represent the same parts.
【００２９】図２に示す実施例では、軸部２に筒状の外
嵌部材１２を外嵌固着し、該外嵌部材１２を介して軸部
２がスリーブ５に対して周方向に回動し得るように、軸
部２をスリーブ５に挿入した構造になっている。In the embodiment shown in FIG. 2, a cylindrical external fitting member 12 is externally fitted and fixed to the shaft portion 2, and the shaft portion 2 is rotated in the circumferential direction with respect to the sleeve 5 via the external fitting member 12. The structure is such that the shaft portion 2 is inserted into the sleeve 5 so that the shaft portion 2 can be inserted into the sleeve 5.
【００３０】次に各部材の材質について説明する。静翼
１、軸部２には、耐熱性、対摩耗性に優れたインコネル
７１３ＬＣ等のニッケル基耐熱合金を使用し、外嵌部材
１２には、耐熱性、耐摩耗性に優れたＸ４０、ＭＡＲ−
Ｍ５０９等のコバルト系耐熱合金を、また、スリーブ５
には、耐熱性、耐摩耗性に優れたＳｉ３Ｎ４あるいはＰ
ＳＺを下記表２に示すような組合せで使用する。Next, the materials of each member will be explained. The stationary blade 1 and shaft part 2 are made of nickel-based heat-resistant alloy such as Inconel 713LC, which has excellent heat resistance and wear resistance, and the outer fitting member 12 is made of X40, MAR, which has excellent heat resistance and wear resistance. −
Cobalt-based heat-resistant alloy such as M509 is also used for sleeve 5.
Si3N4 or P, which has excellent heat resistance and wear resistance, is used for
SZ is used in combinations as shown in Table 2 below.
【００３１】[0031]
【表２】[Table 2]
【００３２】上述した材質の軸部２、外嵌部材１２にお
いて、軸部２に外嵌部材１２を外嵌固着する手順を説明
すると、まず、軸部２に外嵌部材１２を常温で圧入し、
次いで、軸部２及び外嵌部材１２を約９００℃の温度で
２４時間程度熱拡散処理を施して軸部２の外周面と外嵌
部材１２の内周面を接合した後、外嵌部材１２の外径を
機械加工により所定の寸法に仕上げる。In the shaft portion 2 and external fitting member 12 made of the above-mentioned materials, the procedure for externally fitting and fixing the external fitting member 12 onto the shaft portion 2 will be explained. First, the external fitting member 12 is press-fitted into the shaft portion 2 at room temperature. ,
Next, the shaft portion 2 and the outer fitting member 12 are subjected to heat diffusion treatment at a temperature of about 900° C. for about 24 hours to join the outer circumferential surface of the shaft portion 2 and the inner circumferential surface of the outer fitting member 12. Finish the outer diameter to the specified dimensions by machining.
【００３３】上述した構成において、ガスタービンを運
転することにより、軸部２、外嵌部材１２、スリーブホ
ルダ３、スリーブ５の温度が約９００℃前後の高温にな
っても、外嵌部材１２、スリーブ５に前掲した表２に示
すような材質の組合せを適用しているので、前述した図
１に示す可変静翼ガスタービンの静翼支持構造と同様な
作用効果を奏し得る。In the above-described configuration, even if the temperature of the shaft portion 2, external fitting member 12, sleeve holder 3, and sleeve 5 reaches a high temperature of about 900° C. by operating the gas turbine, the external fitting member 12, Since the combination of materials shown in Table 2 listed above is applied to the sleeve 5, the same effects as those of the stator blade support structure of the variable stator blade gas turbine shown in FIG. 1 described above can be achieved.
【００３４】なお、本発明は上述した実施例のみに限定
されるものではなく、本発明の要旨を逸脱しない範囲内
で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 changes can be made without departing from the gist of the present invention.
【００３５】[0035]
【発明の効果】以上述べたように、本発明の請求項１、
２、３、４に記載したいずれの可変静翼ガスタービンの
静翼支持構造においても、軸部、スリーブ、あるいは外
嵌部材、スリーブが約９００℃前後の温度になっても焼
付きが生じることがなく、軸部、外嵌部材、スリーブが
摩耗しにくいので、静翼を円滑に回動させることができ
、また、軸部、スリーブ等を強制的に冷却する必要がな
くなるので、ケーシングの構造を簡略化することができ
るという優れた効果を奏し得る。[Effects of the Invention] As stated above, claim 1 of the present invention,
In any of the stator blade support structures of variable stator vane gas turbines described in 2, 3, and 4, seizure may occur even if the shaft portion, sleeve, external fitting member, or sleeve reaches a temperature of approximately 900°C. There is no need to forcibly cool the shaft, external fitting member, sleeve, etc., so the stator vane can rotate smoothly. This has the excellent effect of simplifying the process.
【図１】本発明の請求項１、２、３に記載した可変静翼
ガスタービンの静翼支持構造を示す断面図である。FIG. 1 is a sectional view showing a stator blade support structure of a variable stator blade gas turbine according to claims 1, 2, and 3 of the present invention.
【図２】本発明の請求項４に記載した可変静翼ガスター
ビンの静翼支持構造を示す断面図である。FIG. 2 is a sectional view showing a stator blade support structure of a variable stator blade gas turbine according to a fourth aspect of the present invention.
【図３】従来の可変静翼ガスタービンの静翼支持構造を
示す断面図である。FIG. 3 is a sectional view showing a stator blade support structure of a conventional variable stator blade gas turbine.
１ 静翼 ２ 軸部 ３ スリーブホルダ ４ ケーシング ５ スリーブ １２ 外嵌部材 1 Static wing 2 Shaft part 3 Sleeve holder 4 Casing 5 Sleeve 12 External fitting member
Claims (4)
付けたスリーブホルダと、該スリーブホルダに嵌装され
たガスタービンの径方向に延びるスリーブと、ガスター
ビンの静翼の基部に固着され且つ前記スリーブに回動可
能に支持された軸部を備えた可変静翼ガスタービンの静
翼支持構造において、前記軸部をコバルト系耐熱合金に
より形成し、また、スリーブを窒化硅素、あるいは部分
安定化ジルコニアにより形成したことを特徴とする可変
静翼ガスタービンの静翼支持構造。1. A sleeve holder attached to the outer circumference of a casing of a gas turbine, a sleeve fitted into the sleeve holder and extending in the radial direction of the gas turbine, and a sleeve fixed to the base of a stationary blade of the gas turbine and attached to the sleeve. In a stator blade support structure for a variable stator vane gas turbine having a rotatably supported shaft, the shaft is formed of a cobalt-based heat-resistant alloy, and the sleeve is formed of silicon nitride or partially stabilized zirconia. A stator blade support structure for a variable stator blade gas turbine.
付けたスリーブホルダと、該スリーブホルダに嵌装され
たガスタービンの径方向に延びるスリーブと、ガスター
ビンの静翼の基部に固着され且つ前記スリーブに回動可
能に支持された軸部を備えた可変静翼ガスタービンの静
翼支持構造において、前記軸部をニッケル系耐熱合金に
より形成し、また、スリーブを部分安定化ジルコニアに
より形成したことを特徴とする可変静翼ガスタービンの
静翼支持構造。2. A sleeve holder attached to the outer circumference of a casing of a gas turbine, a sleeve fitted into the sleeve holder and extending in the radial direction of the gas turbine, and a sleeve fixed to a base of a stationary blade of the gas turbine and attached to the sleeve. A stator blade support structure for a variable stator vane gas turbine including a rotatably supported shaft portion, characterized in that the shaft portion is formed of a nickel-based heat-resistant alloy, and the sleeve is formed of partially stabilized zirconia. A stator blade support structure for a variable stator blade gas turbine.
付けたスリーブホルダと、該スリーブホルダに嵌装され
たガスタービンの径方向に延びるスリーブと、ガスター
ビンの静翼の基部に固着され且つ前記スリーブに回動可
能に支持された軸部を備えた可変静翼ガスタービンの静
翼支持構造において、前記軸部をニッケル系耐熱合金に
より形成したうえ、軸部の表面にクロマイズド処理及び
酸化処理を施し、また、スリーブを窒化硅素により形成
したことを特徴とする可変静翼ガスタービンの静翼支持
構造。3. A sleeve holder attached to the outer peripheral part of the casing of the gas turbine, a sleeve fitted into the sleeve holder and extending in the radial direction of the gas turbine, and a sleeve fixed to the base of the stationary blade of the gas turbine and attached to the sleeve. In a stator blade support structure for a variable stator vane gas turbine having a rotatably supported shaft, the shaft is formed of a nickel-based heat-resistant alloy, and the surface of the shaft is subjected to chromized treatment and oxidation treatment, Also, a stator blade support structure for a variable stator blade gas turbine, characterized in that the sleeve is formed of silicon nitride.
付けたスリーブホルダと、該スリーブホルダに嵌装され
たガスタービンの径方向に延びるスリーブと、ガスター
ビンの静翼の基部に固着され且つ前記スリーブに回動可
能に支持された軸部を備えた可変静翼ガスタービンの静
翼支持構造において、前記軸部をニッケル系耐熱合金に
より形成したうえ、軸部にコバルト系耐熱合金により形
成した筒状の部材を外嵌固着せしめ、また、スリーブを
窒化硅素、あるいは部分安定化ジルコニアにより形成し
たことを特徴とする可変静翼ガスタービンの静翼支持構
造。4. A sleeve holder attached to the outer periphery of a casing of a gas turbine, a sleeve fitted into the sleeve holder and extending in the radial direction of the gas turbine, and a sleeve fixed to a base of a stationary blade of the gas turbine and attached to the sleeve. In a stator blade support structure for a variable stator vane gas turbine equipped with a rotatably supported shaft, the shaft is made of a nickel-based heat-resistant alloy, and the shaft is provided with a cylindrical shaft made of a cobalt-based heat-resistant alloy. A stator blade support structure for a variable stator blade gas turbine, characterized in that members are externally fitted and fixed, and the sleeve is formed of silicon nitride or partially stabilized zirconia.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9940491A JPH04308328A (en) | 1991-04-04 | 1991-04-04 | Stator blade support structure of variable stator blade gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9940491A JPH04308328A (en) | 1991-04-04 | 1991-04-04 | Stator blade support structure of variable stator blade gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH04308328A true JPH04308328A (en) | 1992-10-30 |
Family
ID=14246555
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP9940491A Pending JPH04308328A (en) | 1991-04-04 | 1991-04-04 | Stator blade support structure of variable stator blade gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH04308328A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010168660A (en) * | 2003-06-11 | 2010-08-05 | Ihi Corp | Variable blade and surface treatment method |
-
1991
- 1991-04-04 JP JP9940491A patent/JPH04308328A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010168660A (en) * | 2003-06-11 | 2010-08-05 | Ihi Corp | Variable blade and surface treatment method |
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