JPS62182254A - Spacer for gas turbine - Google Patents
Spacer for gas turbineInfo
- Publication number
- JPS62182254A JPS62182254A JP2382986A JP2382986A JPS62182254A JP S62182254 A JPS62182254 A JP S62182254A JP 2382986 A JP2382986 A JP 2382986A JP 2382986 A JP2382986 A JP 2382986A JP S62182254 A JPS62182254 A JP S62182254A
- Authority
- JP
- Japan
- Prior art keywords
- spacer
- gas turbine
- creep rupture
- less
- rupture strength
- 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
- 125000006850 spacer group Chemical group 0.000 title claims abstract description 16
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 16
- 229910000734 martensite Inorganic materials 0.000 claims abstract description 16
- 239000010959 steel Substances 0.000 claims abstract description 16
- 229910000851 Alloy steel Inorganic materials 0.000 claims abstract description 5
- 229910052758 niobium 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
- 229910052759 nickel Inorganic materials 0.000 claims abstract 3
- 229910052715 tantalum Inorganic materials 0.000 claims 2
- 239000000463 material Substances 0.000 abstract description 23
- 239000000203 mixture Substances 0.000 abstract description 6
- 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
- 230000000694 effects Effects 0.000 description 12
- 229910000859 α-Fe Inorganic materials 0.000 description 10
- 230000015572 biosynthetic process Effects 0.000 description 6
- 239000003205 fragrance Substances 0.000 description 5
- 229910045601 alloy Inorganic materials 0.000 description 4
- 239000000956 alloy Substances 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000000052 comparative effect Effects 0.000 description 3
- 230000007774 longterm Effects 0.000 description 3
- 238000010521 absorption reaction Methods 0.000 description 2
- 239000003795 chemical substances by application Substances 0.000 description 2
- 238000011156 evaluation Methods 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 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
- 241000282342 Martes americana Species 0.000 description 1
- 229910001566 austenite Inorganic materials 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000010411 cooking Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion 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
- 238000009863 impact test Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 150000001247 metal acetylides Chemical class 0.000 description 1
- 239000002304 perfume Substances 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 238000005496 tempering 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フル
テンサイ１−系合金鋼を用いたガスタービン用スペーサ
に関する。Detailed Description of the Invention [Industrial Application Field] The present invention provides a spacer for gas turbines using a novel full tensile strength 1-based alloy steel that has high creep rupture strength at a temperature of 400 to 450°C and high toughness at room temperature. Regarding.
現在、ガスタービン用スペーサにはＣｒ −Ｍ 。 Currently, Cr-M is used for gas turbine spacers.
−Ｖ鋼が使用されている。-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。熱効率を向上させるにはガス温度
及び圧力をＬげろのが最も有効な手段である。ガス温度
を１１００°Ｃ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−
にが期待できる。In recent years, it has been desired to improve the thermal efficiency of gas turbines from the viewpoint of energy conservation. The most effective means for improving thermal efficiency is to lower the gas temperature and pressure. By increasing the gas temperature from 1100°C to 1300°C and increasing the pressure ratio from 10 to 15, a relative efficiency increase of approximately 3% was achieved.
You can expect it.
しかし、これらの高温、ｌｌ’ＪＨ圧化に伴ない従来の
Ｃｒ −Ｍ ｏ −Ｖ鋼では強度不足で、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, due to these high temperatures and ll'JH pressures, the strength of conventional Cr-Mo-V steel is insufficient, and a material with higher strength is required. Creep rupture strength, which has the greatest influence on high-temperature properties, is required.
クリープ破断強度がＣｒ −Ｍ ｏ −Ｖ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-Mo-V 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Ｃｏ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５８−１１０６６］什公報、同５８−４
５３５！’１号公報、特公昭４６−２７９号公報等知ら
れている。Co-based alloys, martensitic steels, etc. are generally known, but Ni
Base alloys and Co-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. JP 58-11066 as martensitic steel] Publication No. 58-4
535! '1 Publication, Japanese Patent Publication No. 46-279, etc. are known.
しかし、これらの材料では４００〜４５０’Ｃで晶いク
リープ破断強度で、室温における高い靭性が得られない
。However, these materials have creep rupture strength that crystallizes at 400 to 450'C, and high toughness at room temperature cannot be obtained.
ガスタービンの高温、高圧化に対して貼に強度を高める
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 withstand 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”Ｃ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＋−ｍによって構成したガスタービン用
スペーサを提供するにある。An object of the present invention is to provide a spacer for a gas turbine made of marten thi+-m, which 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
５ ｋｇ／ｍｍ２−以上、２０℃ｖノツチシャルピー衝
撃値が５ ｋｇ−ｍ／ｃｍ”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
スペーサにある。The present invention has a creep rupture strength of 4 for 100,000 hours at 450°C.
5 kg/mm2- or more and a notch Charpy impact value at 20° C. of 5 kg-m/cm 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、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水門された。It has been experimentally determined that high creep rupture strength at 400 to 450° C., which is the objective of the present invention, can be achieved by adjusting the components within the following composition range.
Ｇ ０．０５〜０．１５％、Ｖ０．Ｌ 〜０．３％
Ｓｉ １％以下、Ｎｂ０．０２〜０．２％Ｍｎ １
．５％以下、Ｎ０．０２〜０．１％Ｎｊ １〜２．５％
、残部がＦａおよび不純物Ｃｒ ８〜１３％。G 0.05-0.15%, V0. L ~0.3%
Si 1% or less, Nb 0.02-0.2% Mn 1
．． 5% or less, N0.02~0.1%Nj 1~2.5%
, the remainder being Fa and impurities Cr 8-13%.
Ｍｏ １．５〜３．５％。Mo 1.5-3.5%.
また次に示す式で計算されるＣｒ当鰍が、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 content calculated by the following formula is 10 or less and making the metal structure a fully tempered martensitic structure that does not contain δ ferrite, embrittlement during use is significantly reduced. It was also determined that
Ｃｒ当量＝−４０Ｃ−２Ｍｎ−４Ｎｉ−３ＯＮ＋６Ｓｉ
＋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の代わりに一部又は全
部についてＴａを添加しても本発明の目的が達成される
ことも実験的に水門された。Cr equivalent = -40C-2Mn-4Ni-3ON+6Si
+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 in part or all in place of Nb. It has also been experimentally demonstrated that the objectives of the present invention can be 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次焼もどじ）、次いで５５０〜６５０℃
の温度に加熱保持し第２次焼もどじを行なう。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. Heating and holding at a temperature of 600℃ (first baking process), then 550-650℃
Heat and maintain the temperature at
次に本発明材の安全評価について述べる。高温回転体で
最も重量なのはクリープ破断強度であり。Next, safety evaluation of the present invention material will be described. The heaviest factor in high-temperature rotating bodies is creep rupture strength.
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４５０ｔ。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 is 450t.
１０５ｈクリー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。Evaluation was made based on 105h creep 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、Ｃは高
い引張強さと耐力を得るために最底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、１０’ｈ ク
リープ破断強度を低下させるので０．１５γ、以下にし
なければならない。最も０．０７〜０．１２％が好まし
い。Explaining the reason for limiting the range of components of the material of the present invention, C is required at a minimum content of 0.05% in order 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 period of time, reducing the 10'h creep rupture strength, so the content must be 0.15 γ or less. The most preferable range is 0.07 to 0.12%.
Ｓｉは脱酸剤、Ｍｎは脱酸・脱硫剤として鋼の溶解の際
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ｍ法などによればＳｉ添加の必要
がない６Ｓｌ低減は使用中脆化の防止効果があり、０．
３％以下、特に０．ｏ ｉ％％以下好ましい。多量のＭ
ｎ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 melting steel, 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., the reduction of 6Sl, which does not require the addition of Si, has the effect of preventing embrittlement during use.
3% or less, especially 0. o i%% or less is preferred. large amount of M
Since n addition reduces high temperature strength, it must be kept at 1.5% or less. Particularly preferred is 0.5 to 0.9%.
Ｃｒは耐食性と高温強度を高めるが、１３％以１―添加
するとδフエライト組織生成の原因になる。Cr improves corrosion resistance and high-temperature strength, but if it is added in excess of 13%, it causes the formation of a δ-ferrite structure.
８％より少ないとｉ−１食性及び高温げ４１度が不１−
分なので、Ｃｒは８〜１：３°Ａに決定された。特に１
１〜１２．５％がり了ましい。If it is less than 8%, the i-1 eating quality and high temperature of 41 degrees are poor.
Cr was determined to be 8-1:3°A. Especially 1
1 to 12.5% is good.
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＋ｈ効果がある。Mo increases creep rupture strength through solid solution and precipitation strengthening effects, and at the same time has an embrittlement prevention effect.
、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、Ｊ、Ｆ）％以北になるとδフェライ１〜生成原
因になるので１，５〜３ 、５ ’Ｘ、に限定された。, 1.5% or less, the creep rupture strength improvement effect is insufficient, and north of J, F)%, it causes the formation of δ ferrite 1~, so it was limited to 1,5~3,5'X, .
特に２〜３％が好ましい、、ＭＯの代りにＷを１部又は
全部を添加することができる。In particular, 2 to 3% is preferable, and one part or all of W can be added instead of MO.
■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フェライ１−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Ｖ
０．１５〜０．２０％ 、Ｎｂ０．０４〜０．０８％が
好マシイ。(2) and Nb 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 1 and tends to lower the creep rupture strength. Especially V
0.15-0.20% and Nb 0.04-0.08% are better.
ＴａもＮｂと同じ効果がある。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。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. Especially from 1.5 to 1.9%.
１．７〜１．９％ が好ましい。1.7 to 1.9% is preferable.
Ｎはクリープ破断強度の改善及びδフエライ１〜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 1, but if it is less than 0.02%, the effect is not sufficient, and if it exceeds 0.1%, it reduces toughness. In particular, excellent properties can be obtained in 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 a completely tempered martensitic structure.
４５０℃、１０”ｈクリープ破断強度は４．５ｋｇ／ｍ
ｔｎ”以上で、２０”ＣＶノツチシャルピー衝撃値が５
ｋｇ−ｍ／ｃｍ２以上が必要である。特に、前者が５
０ｋｇ／ｍｍ２以上、後者が９ ｋｇ−ｍ／ｃｍ’−以
上が好ましい。450℃, 10"h creep rupture strength is 4.5kg/m
tn" or more, 20" CV notch Charpy impact value is 5
kg-m/cm2 or more is required. In particular, the former is 5
The latter is preferably 0 kg/mm2 or more, and the latter is preferably 9 kg-m/cm'- or more.
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３０００
ｈ加熱後の室温のＶノツチシャルピー衝撃値が３ ｋ
ｇ−ｍ／ｃｍ”以上、特に７ ｋｇ−ｍ／ｃｍ”以上と
することが好ましい。FATT is preferably 20°C or lower, particularly 15°C or lower. In particular, high temperature embrittlement is also an important factor;
The V-notch Charpy impact value at room temperature after heating is 3k.
g-m/cm" or more, particularly preferably 7 kg-m/cm" or more.
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。Ｎｎ２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（ＭＩＳＺ鋼）であ
り、比較鋼４は、１２ 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Ｃｒｕｃｉｂｌｅ ４２
２ ｍ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. Nn2 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 (MISZ steel) used for gas turbine wheels and steam turbine blades, and comparative steel 4 is Crucible 42, which is the most widely used material for high-temperature members among 12 Cr heat-resistant steels.
It is 2 m.
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Ｑ 、
８ ｋＦＣ−ｍ／ｃｍ２と高いがクリープ破断強度が４
１． 、９ｋｇ／ｍｍ２と低い。賦香４は衝撃値及びク
リープ破断強度がともに低い。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 Q,
Although it is high at 8 kFC-m/cm2, the creep rupture strength is 4
1. , as low as 9 kg/mm2. Fragrance 4 has low impact value and low creep rupture strength.
これに対し１本発明林状番１，２及び３は４５０℃、１
０５ ｈクリープ破断強度、引張特性及び衝ｕ 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。In contrast, forest numbers 1, 2, and 3 of the present invention were heated at 450°C.
It was confirmed that the material had excellent creep rupture strength, tensile properties, and impact u 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粱いことも重
要なので、脆化材の衝撃値も調べた。As a high-temperature component, it is important that the material becomes brittle during long-term use, so we also investigated the impact value of the brittle material.
５００°Ｃ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試＃に１が８ 、６ ｋｇ−ａ＋／
ｃｍ” 、賦香５が８ 、９ ｋｇ−ｍ／ｃｍ” 、賦
香３が３ 、８ ｋｇ−ｍ／ｃｍ”であった。発明材（
全焼もどしマルテンサイト組ｉｔ＞は脆化処理後でも３
ｋｇ−ｍ／ｃｍ２以上、特に、Ｎａ １及び５は８
ｋｇ−ｍ／ｃｍ”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 is 8,6 kg-a+/
cm'', fragrance 5 was 8.9 kg-m/cm'', and fragrance 3 was 3.8 kg-m/cm''. Inventive material (
The completely tempered martensite group is 3 even after embrittlement treatment.
kg-m/cm2 or more, especially Na 1 and 5 are 8
It has an excellent impact absorption energy of more than "kg-m/cm". On the other hand, the perfume 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ペーサを第１表に示すＮ
１１５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。本発
明に係るスペーサ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。The gas turbine spacer according to the present invention is shown in Table 1.
By using the material No. 115, it is possible to increase the temperature and pressure of the gas turbine, thereby improving efficiency. The spacer 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.
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
。It is adjusted to have a fully tempered martensitic structure.
本発明ガスタービン用スペーサは、４００〜４５０℃ク
リープ破断強度が著しく優れており。The gas turbine spacer of the present invention has extremely excellent creep rupture strength at 400 to 450°C.
高温破壊に対する信頼性が高い。High reliability against high temperature breakdown.
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。
４・・・タービンスペーサ。FIG. 1 is a sectional view of a gas turbine according to an embodiment of the present invention. 4...Turbine spacer.
Claims (1)
ｇ／ｍｍ＾２以上２０℃Ｖノツチシヤルピー衝撃値が５
ｋｇ−ｍ／ｃｍ＾２以上であるマルテンサイト系合金鋼
によつて構成されることを特徴とするガスタービン用ス
ペーサ。 ２、前記マルテンサイト系合金鋼は、重量比でＣ０．０
５〜０．２％、Ｓｉ１％以下、Ｍｎ１．５％以下、Ｎｉ
１〜２．５％、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ペーサ。 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
ペーサ。 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
スペーサ。[Claims] Creep rupture strength of 45k at 1,450°C for 100,000 hours
g/mm^2 or more at 20°C V-notch mechanical pyroimpact value is 5
A spacer for a gas turbine, characterized in that it is made of martensitic alloy steel having a tensile strength of kg-m/cm^2 or more. 2. The martensitic alloy steel has a weight ratio of C0.0
5-0.2%, Si 1% or less, Mn 1.5% or less, Ni
1-2.5%, 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%, N0.1
% or less 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 gas turbine spacer according to claim 1, which has a creep rupture strength of 50 kg/mm^2 or more for 100,000 hours. 4. The spacer 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 |
|---|---|---|---|
| JP2382986A JPS62182254A (en) | 1986-02-07 | 1986-02-07 | Spacer for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2382986A JPS62182254A (en) | 1986-02-07 | 1986-02-07 | Spacer for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS62182254A true JPS62182254A (en) | 1987-08-10 |
Family
ID=12121264
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2382986A Pending JPS62182254A (en) | 1986-02-07 | 1986-02-07 | Spacer for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS62182254A (en) |
-
1986
- 1986-02-07 JP JP2382986A patent/JPS62182254A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JPH0563544B2 (en) | ||
| US5008072A (en) | Heat resistant steel and gas turbine components composed of the same | |
| US4090813A (en) | High-efficiency turbo-machine impellers | |
| JPH0621323B2 (en) | High strength and high chrome steel with excellent corrosion resistance and oxidation resistance | |
| JPH0319295B2 (en) | ||
| JPH02290950A (en) | Ferritic heat resisting steel excellent in strength at high temperature | |
| JP2005171339A (en) | High strength high toughness high corrosion resistance martensite steel, steam turbine blade, and steam turbine power plant | |
| US4414024A (en) | Martensitic heat-resistant steel | |
| JP2002235154A (en) | HIGH Cr FERRITIC HEAT RESISTANT STEEL | |
| JPH06306550A (en) | Heat resistant steel and heat treatment therefor | |
| JPS62180040A (en) | Compressor blade for gas turbine | |
| JPS58110662A (en) | Heat resistant steel | |
| JPS62182254A (en) | Spacer for gas turbine | |
| JPH0885850A (en) | High chromium ferritic heat resistant steel | |
| JPS62218544A (en) | Stacking bolt for gas turbine | |
| JPS6187852A (en) | Heat resisting austenitic stainless cast steel | |
| JPS63145750A (en) | Low alloy steel for turborotor | |
| JPS60165358A (en) | High strength and high toughness steel for high and medium pressure rotor of steam turbine | |
| JP3345988B2 (en) | Steam turbine rotor | |
| JPS62180041A (en) | Distance piece for gas turbine | |
| JPS6283451A (en) | Disk of gas turbine | |
| JP3296816B2 (en) | Heat resistant steel and its applications | |
| JPH01230723A (en) | Manufacture of turbine rotor | |
| JPH07118812A (en) | Heat-resistant cast steel turbine casting and its production | |
| JPH1036944A (en) | Martensitic heat resistant steel |