JPS62218544A - Stacking bolt for gas turbine - Google Patents
Stacking bolt for gas turbineInfo
- Publication number
- JPS62218544A JPS62218544A JP6054386A JP6054386A JPS62218544A JP S62218544 A JPS62218544 A JP S62218544A JP 6054386 A JP6054386 A JP 6054386A JP 6054386 A JP6054386 A JP 6054386A JP S62218544 A JPS62218544 A JP S62218544A
- Authority
- JP
- Japan
- Prior art keywords
- steel
- creep rupture
- rupture strength
- gas turbine
- less
- 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
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 20
- 239000010959 steel Substances 0.000 claims abstract description 20
- 229910000734 martensite Inorganic materials 0.000 claims abstract description 19
- 229910000851 Alloy steel Inorganic materials 0.000 claims abstract description 5
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 4
- 229910052748 manganese Inorganic materials 0.000 claims abstract description 4
- 229910052758 niobium Inorganic materials 0.000 claims abstract description 4
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 3
- 229910052715 tantalum Inorganic materials 0.000 claims abstract 3
- 239000000203 mixture Substances 0.000 abstract description 5
- 238000005496 tempering Methods 0.000 abstract description 3
- 230000001105 regulatory effect Effects 0.000 abstract 2
- 229910052804 chromium Inorganic materials 0.000 abstract 1
- 229910052742 iron Inorganic materials 0.000 abstract 1
- 229910052750 molybdenum Inorganic materials 0.000 abstract 1
- 229910052720 vanadium Inorganic materials 0.000 abstract 1
- 239000000463 material Substances 0.000 description 23
- 230000000694 effects Effects 0.000 description 12
- 229910000859 α-Fe Inorganic materials 0.000 description 10
- 230000015572 biosynthetic process Effects 0.000 description 6
- 229910045601 alloy Inorganic materials 0.000 description 4
- 239000000956 alloy Substances 0.000 description 4
- 230000000052 comparative effect Effects 0.000 description 3
- 239000003205 fragrance Substances 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 230000007774 longterm Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000010521 absorption reaction Methods 0.000 description 2
- 239000003795 chemical substances by application Substances 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910001566 austenite Inorganic materials 0.000 description 1
- 238000010411 cooking Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003009 desulfurizing effect Effects 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000009863 impact test Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- JEIPFZHSYJVQDO-UHFFFAOYSA-N iron(III) oxide Inorganic materials O=[Fe]O[Fe]=O JEIPFZHSYJVQDO-UHFFFAOYSA-N 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 150000001247 metal acetylides Chemical class 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000000779 smoke Substances 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、温度４００〜４５０℃において高いクリープ
破断強度及び室温において高い靭性を有する新規なマル
テンサイト系合金鋼を用いたガスタービン用スタッキン
グボルトに関する。Detailed Description of the Invention [Industrial Application Field] The present invention provides a stacking bolt for gas turbines using a novel martensitic alloy steel that has high creep rupture strength at temperatures of 400 to 450°C and high toughness at room temperature. Regarding.
現在、ガスタービン用スタッキングボルトには、Ｃｒ
−Ｍ ｏ −Ｖ鋼が使用されている。Currently, stacking bolts for gas turbines contain Cr.
-Mo -V steel is used.
近年、省エネルギーの観点からガスタービンの熱効率の
向上が望まれている。熱効率を向上させてるにはガス温
度及び圧力を上げるのが最も有効な手段である。ガス温
度を１１００℃から１３００℃に高め、圧力比を１０か
ら１５まで高めることにより、相対比で約３％の効率向
上が期待できる。In recent years, it has been desired to improve the thermal efficiency of gas turbines from the viewpoint of energy conservation. The most effective way to improve thermal efficiency is to increase gas temperature and pressure. By increasing the gas temperature from 1100°C to 1300°C and increasing the pressure ratio from 10 to 15, it is possible to expect a relative efficiency improvement of about 3%.
しかし、これらの高温・高圧化に伴ない従来のＣｒ −
Ｍ ｏ −Ｖ ｆＲでは強度不足で、より強度の高い材
料が必要である。強度として高温特性を最も大きく左右
するクリープ破断強度が要求される。However, as these temperatures and pressures increase, conventional Cr −
M o -V fR is insufficient in strength and requires a material with higher strength. Creep rupture strength, which has the greatest influence on high-temperature properties, is required.
クリープ破断強度がＣｒ−ＭｏＶ鋼より高い構造材料と
してオーステナイト鋼、Ｎｉ基合金。Austenitic steel and Ni-based alloys are structural materials with higher creep rupture strength than Cr-MoV steel.
ＣＯ基合金、マルテンサイト鋼等が一般に知られている
が、熱間加工性、切削性及び振動減衰特性等の点でＮｉ
基合金及びＧｏ基合金は望ましくない。また、オーステ
ナイト鋼は４００〜４５０℃付近の高温強度がそれ程高
くないこと更にガスタービン全体システムから望ましく
ない。一方、マルテンサイト鋼は他の構成部品とのマツ
チングが良く、高温強度も十分である。マルテンサイト
鋼として特開昭５８−１１０６６１号公報、同５８−４
５３５９号公報、特公昭４６−２７９号公報等知られて
いる。しかし、これらの材料では４００〜４５０℃で高
いクリープ破断強度で、室温における高い靭性が得られ
る。CO-based alloys, martensitic steels, etc. are generally known, but Ni
Base alloys and Go-based alloys are undesirable. Further, austenitic steel does not have very high high temperature strength around 400 to 450°C, and is also undesirable from the perspective of the entire gas turbine system. On the other hand, martensitic steel matches well with other components and has sufficient high-temperature strength. As martensitic steel, JP-A No. 58-110661, No. 58-4
5359, Japanese Patent Publication No. 46-279, etc. are known. However, these materials have high creep rupture strength at 400-450°C and high toughness at room temperature.
ガスタービンの高温・高圧化に対して単に強度を高める
だけでなく、室温における靭性の高い材料が要求される
ことである。一般に、強度を向上させると靭性が低下す
る。本発明は高温強度と室温における靭性を兼ね備えた
材料を見い出すことにある。Materials that not only have high strength to cope with the high temperatures and pressures of gas turbines, but also have high toughness at room temperature are required. Generally, increasing strength reduces toughness. The object of the present invention is to find a material that has both high temperature strength and room temperature toughness.
本発明の目的は、４００〜４５０℃において高いクリー
プ破断強度を有し、且つ室温において高い靭性を有する
マルテンサイト鋼によって構成したガスタービン用スク
ッキングボルトを提供するにある。An object of the present invention is to provide a gas turbine screw bolt made of martensitic steel that has high creep rupture strength at 400 to 450°C and high toughness at room temperature.
本発明は、４５０℃で１０万時間クリープ破断強度が４
５ｋｇ／ｗｍ”以上、２０℃Ｖノツチシャルピー衝撃値
が５ ｋｇ −ｍ ／ ａ１以上であるマルテンサイト
鋼によって構成されることを特徴とするガスタービン用
スクッキングボルトにある。The present invention has a creep rupture strength of 4 for 100,000 hours at 450°C.
5 kg/wm" or more, and a martensitic steel having a 20°C V Notch Charpy impact value of 5 kg-m/a1 or more.
本発明の目的である４００〜４５０℃で高クリープ破断
強度を得るためには１次に示す組成範囲に成分を調整す
ることにより達成されることが実験的に未明された。It has been experimentally discovered that the objective of the present invention, which is to obtain a high creep rupture strength at 400 to 450°C, can be achieved by adjusting the components within the composition range shown below.
Ｃ０．０５〜０．１５％、Ｖ０．１〜０．３％Ｓｉ
１％以下、 Ｎｂ０．０２〜０．２％Ｍｎ
１．５％以下、 Ｎ ０．０２〜０．
１％Ｎｉ １〜２．５％、 残部がＦｅおよ
び不純物Ｃｒ８〜１３％。C0.05~0.15%, V0.1~0.3%Si
1% or less, Nb0.02-0.2%Mn
1.5% or less, N 0.02-0.
1% Ni 1-2.5%, balance Fe and impurities Cr 8-13%.
Ｍ ｏ １ 、５〜３ 、５％。M o 1, 5-3, 5%.
また次に示す式で計算されるＣｒ当量が、１０以下にな
るように成分調整し、金属組織をδフェライトを含まな
い全焼もどしてマルテンサイト組織にすることにより、
使用中脆化が著しく少なくなることも究明された。In addition, by adjusting the composition so that the Cr equivalent calculated by the following formula is 10 or less, and completely tempering the metal structure to make it a martensitic structure that does not contain δ ferrite,
It has also been found that embrittlement during use is significantly reduced.
Ｃｒ当量＝−４０Ｇ−２Ｍｎ−４Ｎｉ−３ＯＮ＋６８ｉ
＋Ｃｒ＋４Ｍｏ＋１１Ｖ＋５Ｎｂ＋２．５Ｔａさらに上
記組成にＷを添加するとクリープ破断強度が向上するこ
と、ＣＯを添加すると衝撃値が低くなるもののクリープ
破断強度が向上すること、Ｎｂの代わりにＴａを添加し
ても本発明の目的が達成されることも実験的に未明され
た。Cr equivalent = -40G-2Mn-4Ni-3ON+68i
+Cr+4Mo+11V+5Nb+2.5Ta Furthermore, adding W to the above composition improves the creep rupture strength, adding CO lowers the impact value but improves the creep rupture strength, and adding Ta instead of Nb also improves the creep rupture strength. It was also experimentally demonstrated that the objective was achieved.
本発明材の熱処理はまず完全なオーステナイトに変態す
るに十分な温度、最低９００℃、最高１１５０℃に均一
加熱し、マルテンサイト組織が得られる１００℃／ｈ以
上の速度で急冷し、次いで４５０〜６００℃の温度に加
熱保持しく第１火煙もどじ）、次いで５５０〜６５０℃
の温度に加熱保持し第２火煙もどじを行う。In the heat treatment of the material of the present invention, first, it is uniformly heated to a temperature sufficient to transform into complete austenite, a minimum of 900°C and a maximum of 1150°C, and then rapidly cooled at a rate of 100°C/h or more to obtain a martensitic structure. Heat and hold at a temperature of 600℃ (first fire and smoke), then 550-650℃
Heat and maintain at a temperature of
次に本発明の安全評価について述べる。高温回転体で最
も重要なのはクリープ破断強度であり、設計許容応力は
１０万時間クリープ破断強度で決定される。そこで本発
明材の高温強度は４５０″″Ｃ２１０５ｈクリ一プ破断
強度で評価した。１０”ｈクリープ破断強度は、一般に
用いられているラルソンーミラー法で求めた。Next, safety evaluation of the present invention will be described. The most important factor for high-temperature rotating bodies is creep rupture strength, and the design allowable stress is determined by the 100,000-hour creep rupture strength. Therefore, the high temperature strength of the material of the present invention was evaluated using 450''C2105h clip rupture strength. The 10''h creep rupture strength was determined by the commonly used Larson-Miller method.
本発明材の成分範囲限定理由について説明する。 The reason for limiting the range of components of the material of the present invention will be explained.
Ｃは高い引張強さと耐力を得るために最低０．０５％必
要である。しかし、あまりＣを多くすると、高温に長時
間さらされた場合に金属組織が不安定になり、１０δｈ
クリープ破断強度を低下させるので、０．１５％以下
にしなければならない。最も０．０７〜０．１２％が好
ましい。C is required at least 0.05% to obtain high tensile strength and yield strength. However, if too much C is added, the metal structure becomes unstable when exposed to high temperatures for a long time, and 10δh
Since it lowers the creep rupture strength, it must be kept at 0.15% or less. The most preferable range is 0.07 to 0.12%.
Ｓｉは脱酸剤、Ｍｎは脱酸・脱硫剤として錆の溶解の際
に添加するものであり、少量でも効果がある。Ｓｉはδ
フエライト生成元素であり、多量の添加は疲労及び靭性
を低下させるδフエライト生成の原因になるので１％以
下にしなければならない。なお、カーボン真空脱酸法及
びエレクトロスラグ溶解法などによればＳｉ添加の必要
がなく、Ｓｊ低減は使用中脆化の防止効果があり、０．
３％以下、特に０．０１％以下が好ましい。多量のＭｎ
添加は高温強度を低下させるので１．５％以下にしなけ
ればならない、特に０．５〜０．９％が好ましい。Si is added as a deoxidizing agent, and Mn is added as a deoxidizing/desulfurizing agent when dissolving rust, and even a small amount is effective. Si is δ
It is a ferrite-forming element, and addition of a large amount causes the formation of δ ferrite, which reduces fatigue and toughness, so it must be kept at 1% or less. In addition, according to carbon vacuum deoxidation method, electroslag melting method, etc., it is not necessary to add Si, and reducing Sj has the effect of preventing embrittlement during use.
It is preferably 3% or less, particularly 0.01% or less. Large amount of Mn
Since addition reduces high-temperature strength, it must be kept at 1.5% or less, particularly preferably 0.5 to 0.9%.
Ｃｒは耐食性と高温強度を高めるが、１３％以上添加す
るとδフエライト組織生成の原因になる。Cr increases corrosion resistance and high-temperature strength, but when added in an amount of 13% or more, it causes the formation of a δ-ferrite structure.
８％より少ないと耐食性及び高温強度が不十分なので、
Ｃｒは８〜１３％に決定された。特に１１〜１２．５％
が好ましい。If it is less than 8%, corrosion resistance and high temperature strength are insufficient.
Cr was determined to be 8-13%. Especially 11-12.5%
is preferred.
Ｍｏは固溶及び析出強化作用によってクリープ破断強度
を高めると同時に脆化防止効果がある。Mo increases creep rupture strength through solid solution and precipitation strengthening effects, and at the same time has the effect of preventing embrittlement.
１．５％以下ではクリープ破断強度向上効果が不十分で
あり、３．５％以上になるとδフエライト生成原因にな
るので１．５〜３．５％に限定された。If it is less than 1.5%, the effect of improving creep rupture strength will be insufficient, and if it is more than 3.5%, it will cause the formation of δ ferrite, so it was limited to 1.5 to 3.5%.
特に２〜３％が好ましい
■及びＮｂは炭化物を析出し高温強度を高めると同時に
靭性向上効果がある。ｖ０．１％、Ｎｂ０．０２％以下
ではその効果が不十分であり、Ｖ０．３％、Ｎｂ０．２
％以上ではδフエライト生成の原因となると共にクリー
プ破断強度が低下する傾向を示すようになる。特にＶ０
．１５〜０．２０％、Ｎｂ０．０４〜０．０８％が好ま
しい、ＴａもＮｂと同じ効果がある。Particularly preferred is 2 to 3% of (2) and Nb, which precipitate carbides and increase high-temperature strength, while at the same time having the effect of improving toughness. If V0.1% and Nb0.02% or less, the effect is insufficient;
% or more causes the formation of δ ferrite and tends to lower the creep rupture strength. Especially V0
．． 15 to 0.20% and Nb 0.04 to 0.08% are preferred; Ta also has the same effect as Nb.
Ｎｉは靭性を高め、かつδフエライト生成の防止効果が
あるが、１．０％以下ではその効果が十分でなく、２．
５％以上では長時間クリープ破断強度を低下させる。特
に１．５〜１．９％より１．７〜１．９％が好ましい。Ni increases toughness and has the effect of preventing the formation of δ ferrite, but if it is less than 1.0%, the effect is not sufficient;
If it exceeds 5%, the long-term creep rupture strength decreases. In particular, 1.7 to 1.9% is more preferable than 1.5 to 1.9%.
Ｎはクリープ破断強度の改善及びδフェライトの生成防
止に効果があるが０．０２％未満ではその効果が十分で
なく、０．１％ を越えると靭性を低下させる。特に０
．０４〜０．０７％の範囲で優れた特性が得られる。N is effective in improving creep rupture strength and preventing the formation of δ ferrite, but if it is less than 0.02%, the effect is not sufficient, and if it exceeds 0.1%, it reduces toughness. Especially 0
．． Excellent properties can be obtained within the range of 0.04 to 0.07%.
高温回転体では、クリープ破断強度が高いことと、高温
で長時間使用中に脆化し難いことも重要である。この使
用中脆化にはδフエライト組織が有害であり、組織は全
焼もどしてマルテンサイト組織でなければならないこと
が実験的に究明された。It is also important for high-temperature rotating bodies to have high creep rupture strength and to be resistant to embrittlement during long-term use at high temperatures. It has been experimentally determined that the δ-ferrite structure is harmful to this embrittlement during use, and that the structure must be completely tempered to become a martensitic structure.
４５０℃、 １０Ｉｓｈ ’） ＩＪ −フ破断強度
Ｌｔ、４５ｋｇ／＋ｍ”以上で、２０℃Ｖノツチシャル
ピー衝撃値が５ ｋｇ −ｍ ／ ａ１以上が必要であ
る。特に前者が５０ ｋｇ／ ｍ”以上後者が９ ｋｇ
−ｍ ／ ａＪ以上が好ましい。ＦＡＴＴは２０℃以
下、特に１５℃以下が好ましい。特に、高温脆化も大事
な要因であり、５００℃で３，０ＯＯｂ 加熱後の室温
のＶノツチシャルピー衝撃値が３ ｋｇ −ｍ ／ ｃ
Ｊ以上、特に７ｋｇ″″”／ｄ以上とすることが好まし
い。450℃, 10Ish') IJ-F breaking strength Lt, 45kg/+m'' or more, and 20℃ V notch Charpy impact value of 5kg-m/a1 or more.Especially if the former is 50kg/m'' or more and the latter is 50kg/m'' or more. is 9 kg
-m/aJ or more is preferable. FATT is preferably 20°C or lower, particularly 15°C or lower. In particular, high-temperature embrittlement is also an important factor, and the V-notch Charpy impact value at room temperature after heating is 3,0OOb at 500℃, 3 kg-m/c.
J or more, especially 7 kg''''/d or more is preferable.
第１表に示す組成（重量％）の試料をそれぞれ２０ｋｇ
溶解し、１１５０℃に加熱し鍛造して実験素材とした。20 kg of each sample with the composition (wt%) shown in Table 1
It was melted, heated to 1150°C, and forged to obtain an experimental material.
この素材に表に示すような焼入れ後、焼戻しの熱処理を
施した。熱処理後の素材からクリープ破断試験片、引張
試験片及びＶノツチシャルピー衝撃試験片を採取し実験
した。This material was quenched and then subjected to tempering heat treatment as shown in the table. A creep rupture test piece, a tensile test piece, and a V-notch Charpy impact test piece were taken from the heat-treated material and tested.
表において、賦香１，２及び５は本発明材であり、賦香
３及び４は比較材である。ＮＱ２はＣｒ当量が高くδフ
エライト組織を５％含み９５％焼もどしマルテンサイト
組織である。他試料は全焼もどしマルテンサイト組織で
あった。比較鋼３はガスタービンホイール及び蒸気ター
ビンブレードに使用されている材料（Ｍ１５２鋼）であ
り、比較鋼４はｌ Ｚ Ｃｒ系耐熱鋼の中で、高温部材
として最も広く用いられているＣｒｕｃｊ、ｂｌｅ４２
２鋼である。In the table, fragrances 1, 2, and 5 are materials of the present invention, and fragrances 3 and 4 are comparative materials. NQ2 has a high Cr equivalent and has a 95% tempered martensitic structure containing 5% δ-ferrite structure. The other samples had a completely tempered martensitic structure. Comparative steel 3 is a material (M152 steel) used for gas turbine wheels and steam turbine blades, and comparative steel 4 is Crucj, ble42, which is the most widely used material for high-temperature parts among l Z Cr-based heat-resistant steels.
2 steel.
第２表はこれら試料の機械的性質の試験結果を示す。賦
香３及び４の結果を見ると、賦香３は衝撃値が９ 、８
ｋｇ −ｍ ／ ｒｙｌ と高いがクリープ破断強度
が４１．９ｋｇ／ｍ”と低い。賦香４は衝撃値及びクリ
ープ破断強度がちとに低い。Table 2 shows the results of testing the mechanical properties of these samples. Looking at the results of incense 3 and 4, incense 3 has a shock value of 9 and 8.
kg-m/ryl, but the creep rupture strength is low at 41.9 kg/m''.The impact value and creep rupture strength of Fragrance 4 are quite low.
これに対し、本発明材賦香１，２及び３は４５０’Ｃ，
１０”ｈ クリープ破断強度、引張特性及び衝撃値が
優れており、高温ガスタービン用デスタントピース材と
して必要な強度、靭性を十分満足することが確認された
。On the other hand, the present invention materials 1, 2 and 3 were 450'C,
It was confirmed that the material had excellent creep rupture strength, tensile properties, and impact value, and sufficiently satisfied the strength and toughness required as a distant piece material for high-temperature gas turbines.
高温部材としては、長時間使用中に脆化し難いことも重
要なので、脆化材の衝撃値も調べた。As a high-temperature member, it is important that the material does not easily become brittle during long-term use, so the impact value of the brittle material was also investigated.
５００℃で３０００ ｈ加熱脆化処理を施した後の衝撃
吸収エネルギーは賦香１が８ 、６ ｋｇ −ｍ ／
ａｌ試賦香が８ 、９ ｋｇ −ｍ ／ ａＪ 、賦香
３が３ 、８ ｋｇ −ｍ ／ ａｄであった。発明材
（全焼もどしマルテンサイト組織）は脆化処理後でも３
）ｃｇ −ｍ ／ ｃｘ１以上、特に、Ｎａｌ及び５
は８ ｋｇ −ｍ ／ ａ１以上の衝撃吸収エネルギを
有し優れている。これに対し、５％のδフエライト組織
を含む賦香３は若干脆化する。The impact absorption energy after heat embrittlement treatment at 500°C for 3000 hours was 8.6 kg-m/
The al trial incense was 8.9 kg-m/aJ, and the incense 3 was 3.8 kg-m/ad. The invented material (completely tempered martensitic structure) has 3
)cg-m/cx1 or more, especially Nal and 5
has an excellent impact absorption energy of 8 kg-m/a1 or more. On the other hand, the flavoring material 3 containing 5% δ ferrite structure is slightly brittle.
図面は本発明に係るガスタービンの回転部分の断面図で
ある。１はタービンスタブシャフト、２はタービンパケ
ット、３はタービンスクッキングボルト、４はタービン
スペーサ、５はデスタントピース、６はコンプレッサデ
ィスク、７はコンプレッサブレード、８はコンプレッサ
スタッキングボルト、９はコンプレッサスタブシャフト
、１０はタービンディスクである。The drawing is a sectional view of a rotating part of a gas turbine according to the present invention. 1 is a turbine stub shaft, 2 is a turbine packet, 3 is a turbine cooking bolt, 4 is a turbine spacer, 5 is a dead piece, 6 is a compressor disk, 7 is a compressor blade, 8 is a compressor stacking bolt, 9 is a compressor stub shaft , 10 is a turbine disk.
本発明に係るガスタービン用スタッキングボルト３及び
８を第１表に示すＨａ ５の材料を用いて構成すること
によりガスタービンの高温・高圧化が可能であり、効率
向上が図れる９本発明に係るは前述の本発明に係る合金
鋼と同様に鍛造し、熱処理を施し、全焼戻しマルテンサ
イト組織を有するように調整される。By constructing the stacking bolts 3 and 8 for a gas turbine according to the present invention using Ha5 materials shown in Table 1, it is possible to increase the temperature and pressure of the gas turbine and improve efficiency.9 According to the present invention is forged and heat treated in the same manner as the alloy steel according to the present invention described above, and is adjusted to have a fully tempered martensitic structure.
本発明のガスタービン用スタッキングボルトは、４００
〜４５０℃クリープ破断強度が著しく優れており、高温
破壊に対する信頼性が高い。The stacking bolt for gas turbine of the present invention has 400
It has extremely high creep rupture strength at ~450°C and is highly reliable against high-temperature fracture.
第１図は本発明の一実施例のガスタービンの断面図であ
る。FIG. 1 is a sectional view of a gas turbine according to an embodiment of the present invention.
Claims (1)
ｇ／ｍｍ＾２以上２０℃Ｖノッチシャルピー衝撃値が５
ｋｇ−ｍ／ｃｍ＾２以上であるマルテンサイト系合金鋼
によって構成されることを特徴とするガスタービン用ス
タッキングボルト。 ２、前記マルテンサイト系合金鋼は、重量比で、Ｃ０．
０５〜０．２％、Ｓｉ１％以下、Ｍｎ１．５％以下、Ｎ
ｉ１〜２．５％、Ｃｒ８〜１５％、Ｍｏ１．０〜３．５
％、Ｖ０．０５〜０．３０％、Ｎｂ及びＴａの少なくと
も一方で単独又は複合で０．０５〜０．２０％、Ｎ０．
１％以下を含有し、７５％以上のＦｅからなる特許請求
の範囲第１項記載のガスタービン用スタッキングボルト
。 ３、前記鋼は、重量でＣ０．０５〜０．２０％、Ｓｉ０
．３％以下、Ｍｎ１．５％以下、Ｎｉ１〜２．５％、Ｃ
ｒ１１〜１２．５％、Ｍｏ１．５〜３．５％、Ｖ０．０
５〜０．３％、Ｎｂ及びＴａの少なくとも一方で単独又
は複合で０．０５〜０．２０％、Ｎ０．０４〜０．０７
％を含有し、残部が実質的にＦｅからなり、４５０℃、
１０万時間クリープ破断強度が５０ｋｇ／ｍｍ＾２以上
である特許請求の範囲第１項に記載のガスタービン用ス
タッキングボルト。 ４、前記鋼は次式で計算されるＣｒ当量が１０以下であ
り、全焼まどしマルテンサイト組織を有する特許請求の
範囲第１項〜第３項のいずれかに記載のガスタービン用
スタッキングボルト。[Claims] Creep rupture strength of 45k at 1,450°C for 100,000 hours
g/mm^2 or more 20℃ V-notch Charpy impact value 5
A stacking bolt for a gas turbine, characterized in that it is made of martensitic alloy steel having a tensile strength of at least kg-m/cm^2. 2. The martensitic alloy steel has a weight ratio of C0.
05-0.2%, Si 1% or less, Mn 1.5% or less, N
i1~2.5%, Cr8~15%, Mo1.0~3.5
%, V0.05-0.30%, at least one of Nb and Ta alone or in combination 0.05-0.20%, N0.
The stacking bolt for a gas turbine according to claim 1, comprising 1% or less of Fe and 75% or more of Fe. 3. The steel contains 0.05-0.20% C and Si0 by weight.
．． 3% or less, Mn 1.5% or less, Ni 1-2.5%, C
r11~12.5%, Mo1.5~3.5%, V0.0
5-0.3%, at least one of Nb and Ta alone or in combination 0.05-0.20%, N0.04-0.07
%, the remainder substantially consists of Fe, 450°C,
The stacking bolt for a gas turbine according to claim 1, having a creep rupture strength of 50 kg/mm^2 or more for 100,000 hours. 4. The stacking bolt for a gas turbine according to any one of claims 1 to 3, wherein the steel has a Cr equivalent calculated by the following formula of 10 or less and has a fully sintered martensitic structure. .
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP6054386A JPS62218544A (en) | 1986-03-20 | 1986-03-20 | Stacking bolt for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP6054386A JPS62218544A (en) | 1986-03-20 | 1986-03-20 | Stacking bolt for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS62218544A true JPS62218544A (en) | 1987-09-25 |
Family
ID=13145307
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP6054386A Pending JPS62218544A (en) | 1986-03-20 | 1986-03-20 | Stacking bolt for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS62218544A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1681359A1 (en) * | 2003-08-29 | 2006-07-19 | National Institute for Materials Science | High temperature bolt material |
-
1986
- 1986-03-20 JP JP6054386A patent/JPS62218544A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1681359A1 (en) * | 2003-08-29 | 2006-07-19 | National Institute for Materials Science | High temperature bolt material |
| EP1681359A4 (en) * | 2003-08-29 | 2009-03-11 | Nat Inst For Materials Science | High temperature bolt material |
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