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1. 发明专利

JP2012002614A Damage evaluation method and apparatus for metallic material 有权
标题翻译：金属材料的损伤评估方法和装置
公开(公告)号：JP2012002614A
公开(公告)日：2012-01-05
申请号：JP2010136752
申请日：2010-06-16
申请人： Hitachi Ltd , Kyushu Electric Power Co Inc , 九州電力株式会社 , 株式会社日立製作所
发明人： SATO JUN , KONNO SHINYA , ICHIKAWA KUNIHIRO , KANETANI AKIHIRO , WATANABE HAJIME , KUSUMOTO JUNICHI
IPC分类号： G01N23/203
摘要： PROBLEM TO BE SOLVED: To provide a method capable of high accuracy damage evaluation for metallic material and residual life prediction as well.SOLUTION: A damage evaluation method for metallic material comprises a measurement step (S2) of measuring crystal orientation at a plurality of measuring points of a specimen of metallic material by an EBSP method, an analysis step (S3) of analyzing a misorientation function value that is defined by a crystal misorientation at each measuring point relative to a reference measuring point among the plurality of measuring points to obtain a damage parameter of the specimen, and evaluation steps (S4) and (S5) of evaluating a damage rate of the specimen based on the damage parameter of the specimen from the analysis in the analyzing step by reference to a correlation between damage rate and damage parameter previously obtained from an other specimen that is made of the same kind of metallic material as the specimen and has a known damage rate.
摘要翻译：要解决的问题：提供一种能够对金属材料进行高精度损伤评估和残余寿命预测的方法。解决方案：金属材料的损伤评估方法包括通过EBSP方法测量金属材料样品的多个测量点处的晶体取向的测量步骤（S2），分析取向差的分析步骤（S3）通过在各测量点处相对于基准测量点的晶体取向定义的功能值，以获得样本的损伤参数，以及评估步骤（S4）和（S5）评估损伤率参照分析步骤中分析的试样的损伤参数，根据先前从与样品相同种类的金属材料制成的其他样品获得的损伤率和损伤参数之间的相关性，并且具有已知伤害率。版权所有（C）2012，JPO＆INPIT

2. 发明专利

JPH10123123A METHOD FOR ESTIMATING CREEP LIFE OF GAS TURBINE HIGH-TEMPERATURE PART 失效
公开(公告)号：JPH10123123A
公开(公告)日：1998-05-15
申请号：JP27941696
申请日：1996-10-22
申请人： HITACHI LTD , KYUSHU ELECTRIC POWER
发明人： KONNO SHINYA , NAKAMURA SHIGEYOSHI , DOI HIROYUKI , KUMADA KAZUHIKO , KANETANI AKIHIRO , HAYAKAWA HIROYUKI , WATANABE HAJIME
IPC分类号： G01M13/00 , G01N33/20
摘要： PROBLEM TO BE SOLVED: To estimate the creep life of gas turbine high-temperature parts whose operating temperature is unknown, with the average particle diameter of a deposit that can be measured after using for a certain period as an index. SOLUTION: An unused material of an alloy used for an actual machine is used, a creep test at various kinds of temperatures and stresses selected from a stress range applied to a turbine part is performed, and the average particle diameter of a deposit on creep rupture is measured, thus obtaining a constant. Then, a test is interrupted at various kinds of times, the average particle diameter and the deposit area rate of a test material and a creep distortion are measured at each interruption, and a constant is obtained. On the other hand, a deposit average diameter and an area rate are measured for a gas turbine high-temperature part that is used for a certain period and a deposit coarseness speed under usage conditions is calculated from an operation time, thus measuring the relationship between the operation time and the speed. Then, the change of a creep damage rate with time is estimated. The change of the creep distortion with time is estimated from the area rate and the average particle diameter of the part for a certain period. Time for reaching the creep damage rate is compared with time for reaching the creep distortion and the shorter time is used as a life.

3. 发明专利

JP2009041449A Repair method for gas turbine rotor vane 审中-公开
标题翻译：燃气轮机转向架维修方法
公开(公告)号：JP2009041449A
公开(公告)日：2009-02-26
申请号：JP2007207345
申请日：2007-08-09
申请人： Hitachi Ltd , Kyushu Electric Power Co Inc , 九州電力株式会社 , 株式会社日立製作所
发明人： ICHIKAWA KUNIHIRO , DOI HIROYUKI , KONNO SHINYA , KANETANI AKIHIRO , KUSUMOTO JUNICHI , KITAGAWA HIDEAKI
IPC分类号： F01D25/00 , B23K31/00 , F02C7/00
CPC分类号： B23P6/045 , B23P6/005
摘要： PROBLEM TO BE SOLVED: To provide a repair method capable of suppressing the frequency of repairs of thermal fatigue cracks generated in a turbine rotor vane and of improving economy and reliability. SOLUTION: In the repair method for the gas turbine rotor vane for repairing thermal fatigue cracks generated in a blade part 1 of the gas turbine rotor vane having a structure for introducing compressed air discharged from a compressor to a blade inner part as cooling air, a range where thermal fatigue cracks may be generated in the blade part 1 under the operation after this repair is predicted, and a section in the region where thermal fatigue cracks may be generated including the portion where thermal fatigue cracks were generated is removed. A coupon material 10 having the same shape and material quality of that of the blade part 1 is fitted to the removed section and is welded to the blade part 1 by a laser. COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供能够抑制在涡轮转子叶片中产生的热疲劳裂纹的修理频率并提高经济性和可靠性的修复方法。解决方案：在用于修复燃气轮机转子叶片的叶片部分1中产生的热疲劳裂纹的燃气轮机转子叶片的修理方法中，其具有用于将从压缩机排出的压缩空气引入到叶片内部的结构作为冷却空气，预测在该修复之后的操作中可能在叶片部分1中产生热疲劳裂纹的范围，并且去除可能产生包括产生热疲劳裂纹的部分的热疲劳裂纹的区域中的部分。具有与刀片部1的形状和材料质量相同的形状和材料质量的优惠券材料10被装配到去除部分，并通过激光焊接到刀片部分1。版权所有（C）2009，JPO＆INPIT

4. 发明专利

JP2006200962A Damage evaluation method of gas turbine part 有权
标题翻译：燃气涡轮机损伤评估方法
公开(公告)号：JP2006200962A
公开(公告)日：2006-08-03
申请号：JP2005011141
申请日：2005-01-19
申请人： Hitachi Ltd , Kyushu Electric Power Co Inc , 九州電力株式会社 , 株式会社日立製作所
发明人： ICHIKAWA KUNIHIRO , KONNO SHINYA , DOI HIROYUKI , KANETANI AKIHIRO , NAGAE MASATAKA
IPC分类号： G01N33/20 , G01M99/00
摘要： PROBLEM TO BE SOLVED: To provide a damage evaluation method of a gas turbine part which enables a reduction of the estimate error of life.
SOLUTION: The damage of the gas turbine part is evaluated on the basis of FEM temperature analyzing results by performing a step (a) for transferring the metal texture of the surface of the gas turbine part to a replica using an electrolytic etching method, a step (b) for observing the replica, on which a conductive substance is vapor-deposited by a scanning electron microscope to measure the mean particle size of a precipitate, a step (c) for estimating a metal temperature from the measured mean particle size of the precipitate and a step (d) for analyzing an FEM temperature using the estimate result of the metal temperature and an inverse problem analyzing technique.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供能够降低生命估计误差的燃气轮机部件的损伤评估方法。解决方案：通过执行使用电解蚀刻方法将燃气轮机部件的表面的金属质感转印到副本的步骤（a），基于FEM温度分析结果来评价燃气轮机部件的损坏，用于观察复制品的步骤（b），通过扫描电子显微镜气相沉积导电物质以测量沉淀物的平均粒度;步骤（c），用于从测量的平均粒子估计金属温度沉淀物的尺寸和使用金属温度的估计结果和逆问题分析技术来分析FEM温度的步骤（d）。版权所有（C）2006，JPO＆NCIPI

5. 发明专利

JP2012073126A Evaluation method and device for crack evolution velocity of metallic material 有权
标题翻译：金属材料裂纹演化速度的评估方法和装置
公开(公告)号：JP2012073126A
公开(公告)日：2012-04-12
申请号：JP2010218447
申请日：2010-09-29
申请人： Hitachi Ltd , Kyushu Electric Power Co Inc , 九州電力株式会社 , 株式会社日立製作所
发明人： KONNO SHINYA , ICHIKAWA KUNIHIRO , SATO JUN , KANETANI AKIHIRO , WATANABE HAJIME , KUSUMOTO JUNICHI
IPC分类号： G01N23/20 , G01N17/00
摘要： PROBLEM TO BE SOLVED: To evaluate crack evolution velocity of metallic material with high accuracy and to evaluate remaining life as well.SOLUTION: The evaluation method for crack evolution velocity of metallic material of the present invention comprises: a measurement step (S2) for measuring crystal orientation at multiple measurement points in a region including a tip of crack in a sample formed of metallic material by an EBSP method; an analysis step (S3) for analyzing a misorientation function value indicating deviation of the crystal orientation at each measurement point to acquire an evaluation parameter of the sample; and evaluation steps (S4, S5) for evaluating the crack evolution velocity of the sample based on the evaluation parameter of the sample acquired by the analysis at the analysis step, by referring to correlation between a crack evolution velocity and an evaluation parameter acquired from another sample which is formed of the same kind of metallic material as the sample and whose crack evolution velocity is known since a crack evolution test is performed in advance.
摘要翻译：要解决的问题：以高精度评估金属材料的裂纹演化速度，并评估剩余寿命。解决方案：本发明的金属材料的裂纹扩展速度的评价方法包括：测量步骤（S2），用于测量由金属材料形成的样品中的包括裂纹尖端的区域中的多个测量点处的晶体取向通过EBSP方法; 分析步骤（S3），用于分析指示每个测量点处的晶体取向的偏差的取向函数值，以获取样本的评估参数; 以及评估步骤（S4，S5），用于基于通过分析步骤中的分析获得的样本的评估参数，通过参考裂纹演化速度和从另一个获取的评估参数之间的相关性来评估样品的裂纹演变速度样品由与样品相同种类的金属材料形成，并且由于进行裂纹扩展试验，所以其已知的裂纹扩展速度是已知的。版权所有（C）2012，JPO＆INPIT

6. 发明专利

JP2014095101A Ni-BASED CASTING ALLOY AND STEAM TURBINE CASTING MEMBER USING THE SAME 有权
标题翻译：镍基铸造合金和蒸汽涡轮铸件会员使用它
公开(公告)号：JP2014095101A
公开(公告)日：2014-05-22
申请号：JP2012245469
申请日：2012-11-07
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： KAMOSHIDA HIROKI , KONNO SHINYA , MURATA KENICHI
IPC分类号： C22C19/05 , F01D25/00 , F01D25/24 , F01D25/26
CPC分类号： C22C19/055 , C22C19/056 , Y10T428/12
摘要： PROBLEM TO BE SOLVED: To provide a Ni-based alloy having a composition so that variation in strength depending on place is minimized even when a solidification rate becomes slow and a microsegregation becomes large when manufacturing large product by casting.SOLUTION: The Ni-based casting alloy has a composition containing, by mass%, C of 0.001% to 0.1%, Cr of 15% to 23%, Mo of 0% to 11.5%, W of 3% to 18%, Fe ot 5% or less, Co of 10% or less, Ti of 0.4% or less, Al of 0.4% or less, and Nb and Ta of 0.5%≤Nb+Ta≤4.15% and the balance inevitable impurities and Ni, and satisfying 7%≤Mo+1/2 W≤13%.
摘要翻译：要解决的问题：提供一种具有如下组成的Ni基合金，即使当通过铸造制造大量产品时，即使固化速度变慢并且微偏析变大，也使得随着位置的强度变化最小化。解决方案：Ni基铸造合金具有以质量％计含有0.001％至0.1％的C，15％至23％的Cr，0％至11.5％的Mo，3％至18％的W，5％或更少的Fe， Co为10％以下，Ti为0.4％以下，Al为0.4％以下，Nb，Ta为0.5％≤Nb+Ta≤4.15％，余量为不可避免的杂质和Ni，满足7％≤Mo+ 1/2W≤13％。

7. 发明专利

JP2014051698A Ni-BASED FORGING ALLOY, AND GAS TURBINE USING THE SAME 审中-公开
标题翻译：镍基锻造合金和使用其的气体涡轮机
公开(公告)号：JP2014051698A
公开(公告)日：2014-03-20
申请号：JP2012195660
申请日：2012-09-06
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： SHIBAYAMA TAKASHI , KONNO SHINYA , KAMOSHIDA HIROKI , KUROKI HIDETOSHI , SATO JUN
IPC分类号： C22C19/05 , B21J5/00 , B21K1/32
CPC分类号： F01D5/147 , C22C19/055 , C22C19/056 , F01D5/02 , F01D5/066 , F01D5/28 , F05D2300/176 , Y02T50/671
摘要： PROBLEM TO BE SOLVED: To provide a Ni-based forging alloy easy in hot forging and grain refining while having both excellent high temperature strength and segregation properties.SOLUTION: A Ni-based forging alloy has a solid solubility temperature of a precipitation strengthening phase of 970°C or lower and a solid solubility temperature difference between a δ phase and the precipitation strengthening phase of 50°C or more, and contains, by mass%, Al:0.5 to 1.0%, Cr:17 to 21%, Fe:17 to 19%, Nb:4.5 to 5.5%, Ti:0.8 to 1.3%, W:3.0 to 6.0%, B:0.001 to 0.03%, C:0.001 to 0.1%, Mo:1.0% or less and the balance Ni with inevitable impurities.
摘要翻译：要解决的问题：提供易于热锻和晶粒细化的Ni基锻造合金，同时具有优异的高温强度和偏析性。解决方案：Ni基锻造合金具有沉淀强化相的固溶度温度 970℃以下，δ相与析出强化相之间的固溶度温度差为50℃以上，以质量％计含有Al：0.5〜1.0％，Cr：17〜21％，Fe： 17〜19％，Nb：4.5〜5.5％，Ti：0.8〜1.3％，W：3.0〜6.0％，B：0.001〜0.03％，C：0.001〜0.1％，Mo：1.0％有不可避免的杂质。

8. 发明专利

JP2012136999A Titanium alloy turbine blade 有权
标题翻译：钛合金涡轮叶片
公开(公告)号：JP2012136999A
公开(公告)日：2012-07-19
申请号：JP2010289354
申请日：2010-12-27
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： KONNO SHINYA , KAMOSHIDA HIROKI , HIRANO SATOSHI , MURATA KENICHI , PARK SEUNG HWAN , ASAI KUNIO , YOSHIDA TAKEHIKO
IPC分类号： F01D5/28 , C22C14/00 , F01D25/00 , F02C7/00
CPC分类号： F01D5/14 , F01D5/28 , F01D5/286 , F05D2300/174 , F05D2300/506 , Y02T50/671
摘要： PROBLEM TO BE SOLVED: To provide a titanium alloy turbine blade having both superior erosion resistance and high long term reliability.SOLUTION: The turbine blade is made of an α-β titanium alloy as a base material, the base material having an average Vickers hardness of 320 Hv or less. The turbine blade is characterized in that a friction stir processing region having a thickness of from 0.5 to 3.0 mm is formed on a part of a surface including an leading edge of the turbine blade, and the friction stir processing region has an average Vickers hardness of 340 Hv or more.
摘要翻译：要解决的问题：提供具有优异的耐侵蚀性和高长期可靠性的钛合金涡轮叶片。解决方案：涡轮叶片由α-β钛合金作为基材制成，基体材料的平均维氏硬度为320Hv以下。涡轮叶片的特征在于，在包括涡轮叶片的前缘的表面的一部分上形成厚度为0.5至3.0mm的摩擦搅拌处理区域，并且摩擦搅拌处理区域具有平均维氏硬度 340 Hv以上。版权所有（C）2012，JPO＆INPIT

9. 发明专利

JP2011246734A Combustor member, method of manufacturing combustor member, and combustor 有权
标题翻译： COMBUSTOR会员，制造COMBUSTOR会员的方法和COMBUSTOR
公开(公告)号：JP2011246734A
公开(公告)日：2011-12-08
申请号：JP2010117726
申请日：2010-05-21
申请人： Chubu Electric Power Co Inc , Hitachi Ltd , 中部電力株式会社 , 株式会社日立製作所
发明人： HARUYAMA HIROSHI , KONNO SHINYA , ICHIKAWA KUNIHIRO , KAMOSHIDA HIROKI , MATSUMURA SHIGEFUMI , ASAI TSUTOMU
IPC分类号： C22C19/07 , C22C30/00 , C22F1/00 , C22F1/10 , F01D25/00 , F02C7/00 , F23R3/00
摘要： PROBLEM TO BE SOLVED: To provide a combustor member which prevents deterioration of heat-fatigue resistance and ductility.SOLUTION: The combustor member 1 is manufactured by using Co-based alloy formed of 0.07-0.10 mass% C, 0.01-1 mass% Si, 0.5-2 mass% Mn, 20-25 mass% Ni, 20-25 mass% Cr, 10-20 mass% W, and the balance Co with inevitable impurities. An area ratio of separated-out carbide in a sectional structure is -66.7×[C]+8.47% or higher, and lower than -53.3×[C]+8.53%, wherein content of C (mass%) is denoted by [C].
摘要翻译：解决的问题：提供一种防止耐热疲劳性和延展性的劣化的燃烧器部件。解决方案：燃烧器构件1通过使用由0.07-0.10质量％C，0.01-1质量％Si，0.5-2质量％Mn，20-25质量％Ni，20-25 质量％Cr，10-20质量％W，余量为Co与不可避免的杂质。截面结构中分离碳化物的面积比为-66.7×[℃] + 8.47％以上，低于-53.3×[℃] + 8.53％，其中C（质量％）的含量由[ C]。版权所有（C）2012，JPO＆INPIT

10. 发明专利

JP2011084812A HIGH-STRENGTH Ni-BASED FORGED SUPERALLOY, AND METHOD FOR PRODUCING THE SAME 有权
标题翻译：高强度Ni基锻造的超级合金及其制造方法
公开(公告)号：JP2011084812A
公开(公告)日：2011-04-28
申请号：JP2010205741
申请日：2010-09-14
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： KAMOSHIDA HIROKI , KONNO SHINYA
IPC分类号： C22C19/05 , C22F1/00 , C22F1/10 , F01D5/28 , F01D25/00
CPC分类号： C22C19/056 , C22C19/055 , C22F1/10
摘要： PROBLEM TO BE SOLVED: To provide a high-strength heat-resistant Ni-based forged alloy in which each crystal grain size of a polycrystal is made large so as to increase the strength of creep, and simultaneously, deterioration in the ductility of the polycrystal is suppressed, and to provide a method for producing the same. SOLUTION: The Ni-based forged superalloy has a composition comprising 0.005 to 0.2% C, 0 to 1% Si, 0 to 1% Mn, 10 to 24% Cr, at least one kind selected from Mo and W by 5 to 17% in the provision of [Mo concentration]+0.5[W concentration], 0.5 to 2% Al, 1 to 3.5% Ti, 0 to 10% Fe and at least one kind selected from 0.002 to 0.02% B and 0.01 to 0.2% Zr, and the balance Ni of 48 to 80% with inevitable impurities. The superalloy is composed of a polycrystal, and the average grain size of the crystals after heat treatment is 72 to 289 μm. In the superalloy, a plurality of precipitates are precipitated along crystal grain boundaries after the heat treatment, and the average length of the precipitated in the optional cross-section of the polycrystal is 0.5 to 2.5 μm. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：为了提供使多晶体的每个晶粒尺寸增大以提高蠕变强度的高强度耐热Ni基锻造合金，并且同时延展性的劣化抑制多晶体，并提供其制造方法。解决方案：Ni系锻造超合金具有含有0.005〜0.2％的C，0〜1％的Si，0〜1％的Mn，10〜24％的Cr，选自Mo和W中的至少1种，至[17]，提供[Mo浓度] +0.5 [W浓度]，0.5-2％Al，1至3.5％Ti，0至10％Fe和至少一种选自0.002至0.02％B和0.01至 0.2％Zr，余量为48〜80％的不可避免的杂质。超合金由多晶构成，热处理后的结晶的平均粒径为72〜289μm。在该高温合金中，在热处理后，沿晶界析出多个析出物，在多晶体的任意截面中析出的平均长度为0.5〜2.5μm。版权所有（C）2011，JPO＆INPIT

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