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21. 发明专利

JPH03153847A NI-CR AUSTENITIC STAINLESS STEEL HAVING EXCELLENT CREEP RUPTURE PROPERTY 失效
公开(公告)号：JPH03153847A
公开(公告)日：1991-07-01
申请号：JP29223289
申请日：1989-11-13
申请人： NIPPON STEEL CORP , MITSUBISHI HEAVY IND LTD
发明人： NAKAZAWA TAKANORI , YANO MITSURU , KOMATSU HAJIME , OKADA KEIZO , TAKANABE KIYOSHI , KANEKO HIDEAKI
IPC分类号： C22C38/00 , C22C38/40 , C22C38/44
摘要： PURPOSE:To manufacture the Ni-Cr austenitic stainless steel having excellent creep rupture properties by incorporating specified ratios of C, Si, Mn, P, Ni, Cr, Al and N into Fe. CONSTITUTION:An Ni-Cr austenitic stainless steel contg., by weight,

22. 发明专利

JP2014178253A Remaining lifetime evaluation method of high temperature machine part 有权
标题翻译：高温机械部件的寿命寿命评估方法
公开(公告)号：JP2014178253A
公开(公告)日：2014-09-25
申请号：JP2013053334
申请日：2013-03-15
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： KARATO TAKANORI , KANEKO HIDEAKI , OHARA TOSHINOBU , SATO YOICHI , KANESAWA YOSHIYUKI , SHIMIZU TAKESHI
IPC分类号： G01M99/00 , G01N3/00
摘要： PROBLEM TO BE SOLVED: To provide a remaining lifetime evaluation method of a high temperature machine part, capable of calculating a remaining lifetime of a high temperature machine part using a simple method and improving reliability of the calculated remaining lifetime of the high temperature machine part.SOLUTION: A remaining lifetime evaluation method of a high temperature machine part comprises the steps of: forming a master curve F on the basis of a result obtained by performing creep-test on a plurality of first test pieces cut down from a plurality of turbine rotor blades unused and manufactured by the same material and the same manufacturing method; and calculating a remaining lifetime X of the turbine rotor blade on the basis of a second creep rate S, and second creep rupture time Tobtained by performing creep-test on a second test piece cut down from a turbine rotor blade manufactured by the same material and the same manufacturing method as the first turbine rotor blades and used for a predetermined time after attached to the turbine, the master curve F, and the predetermined time.
摘要翻译：要解决的问题：为了提供高温机器部件的剩余寿命评估方法，能够使用简单的方法计算高温机器部件的剩余寿命并提高高温机器部件的计算剩余寿命的可靠性。解决方案：高温机器部件的剩余寿命评估方法包括以下步骤：基于通过对从多个涡轮转子切割的多个第一试件进行蠕变试验获得的结果来形成主曲线F. 未使用的刀片和由相同材料制造的刀片和相同的制造方法; 并且基于第二蠕变速率S计算涡轮转子叶片的剩余寿命X，以及通过对由相同材料制造的涡轮转子叶片切割的第二试片进行蠕变试验而得到的第二蠕变断裂时间，以及与第一涡轮转子叶片相同的制造方法，并且在安装到涡轮机之后的预定时间内使用主曲线F和预定时间。

23. 发明专利

JP2005194599A Plasma spraying apparatus and method for detecting temperature of spray particle in the apparatus 审中-公开
标题翻译：用于检测装置中喷雾颗粒温度的等离子喷涂装置和方法
公开(公告)号：JP2005194599A
公开(公告)日：2005-07-21
申请号：JP2004003646
申请日：2004-01-09
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： MEGA MASAHIKO , TORIGOE TAIJI , KANEKO HIDEAKI , TAKAHASHI KOJI , IZUTSU DAISUKE , OHARA MINORU , SHIMONO ATSUSHI , NARITA ATSUSHI , SATO NORIMOTO
IPC分类号： B05B7/22 , C23C4/12
摘要： PROBLEM TO BE SOLVED: To provide plasma spraying apparatus where the temperature of spray particles in a thermal spraying application point can be grasped, and to provide a method for detecting the temperature of spray particles in the plasma spraying apparatus. SOLUTION: A temperature detecting means 9 is arranged at a prescribed temperature measurement position, and a thermal spraying gun 2 is positioned at a position separated by a prescribed thermal spraying length L from a temperature detection point by the temperature detecting means 9. The temperature of spray particles corresponding to the temperature of the spray particles in a thermal spraying application point P is detected with high precision, and the detection result can be used for the proper control of the coating thickness and coating quality in a sprayed coating. COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供一种等离子体喷涂装置，其中可以抓住热喷涂施加点中的喷雾颗粒的温度，并提供一种用于检测等离子喷涂装置中的喷雾颗粒的温度的方法。解决方案：温度检测装置9布置在规定的温度测量位置，并且热喷枪2位于通过温度检测装置9从温度检测点与规定的热喷涂长度L分开的位置。以高精度检测对应于热喷涂施加点P中的喷雾粒子的温度的喷雾粒子的温度，并且检测结果可用于适当控制喷涂中的涂层厚度和涂层质量。版权所有（C）2005，JPO＆NCIPI

24. 发明专利

JP2001348655A THERMAL BARRIER COATING MATERIAL, GAS TURBINE MEMBER APPLIED WITH THE SAME AND GAS TURBINE 失效
公开(公告)号：JP2001348655A
公开(公告)日：2001-12-18
申请号：JP2000173399
申请日：2000-06-09
申请人： MITSUBISHI HEAVY IND LTD
发明人： TORIGOE TAIJI , KANEKO HIDEAKI , OKADA IKUO , TAKAHASHI KOJI , OHARA MINORU
IPC分类号： F01D5/28 , C23C4/08 , C23C4/10 , C23C28/00 , F01D9/02 , F02C7/00 , F23R3/42
摘要： PROBLEM TO BE SOLVED: To improve the durability at higher temperatures in a thermal barrier coasting material coating a gas turbine member. SOLUTION: In a thermal barrier coating film, on a base material 21 composing the moving blade, or the like, of a gas turbine, a metallic bonding layer 22 excellent in corrosion resistance and oxidation resistance and a high strength and high toughness ceramics layer 23 whose physical properties change by the occurance of phase transformation and sintering at >=1,100 deg.C in spite of its high strength and toughness are successively laminated, and on the outermost layer, a high temperature phase stabilized ceramics layer 24 excellent in phase stability at high temperature in spite of its low strength and toughness is laminated. The metallic bonding phase 22 is composed of MCrAlY alloy series, the high strength and high toughness ceramics layer 23 is composed of ZrO2.6 to 12 wt.%Y2O3 or ZrO2.8 to 16 wt.%Dy2O3, and the high temperature phase stabilized ceramics layer 24 is composed of ZrO2.15 to 20 wt.%Y2O3 or ZrO2.16 to 20 wt.%Dy2O3.

25. 发明专利

JPH08200001A MOVING VANE OF GAS TURBINE 失效
公开(公告)号：JPH08200001A
公开(公告)日：1996-08-06
申请号：JP1253895
申请日：1995-01-30
申请人： MITSUBISHI HEAVY IND LTD
发明人： OKADA IKUO , KANEKO HIDEAKI
IPC分类号： F01D5/14 , F01D5/18 , F01D5/28
摘要： PURPOSE: To realize a moving vane of a gas turbine which is prevented from the degradation of thermal fatigue strength of a platform part in the manufacturing process. CONSTITUTION: A vane part 1 made of a one-way solidified Ni base alloy is welded to a platform part 2 made of polycrystal Ni base alloy to form a moving vane. Also, the vane part made of a Ni group single crystal alloy is soldered to the platform part made of either of the polycrystal Ni base alloy or Ni base single crystal alloy to form the moving vane. Thus, the thermal fatigue strength of the platform part 2 can be improved while the yield of products in the manufacturing process can be remarkably improved.

26. 发明专利

JP2012172610A Method for manufacturing thermal shield coating, turbine member provided with the thermal shield coating, and gas turbine 有权
标题翻译：用于制造热风涂层的方法，用热风涂层提供的涡轮构件和气体涡轮
公开(公告)号：JP2012172610A
公开(公告)日：2012-09-10
申请号：JP2011036126
申请日：2011-02-22
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： MEGA MASAHIKO , TANIGAWA HIDETSUGU , HORIE JO , TORIGOE TAIJI , NAGANO ICHIRO , KANEKO HIDEAKI , TAKAHASHI KOJI , KAMIMURA YOSHIHISA , OKAYA NAOTOSHI , OKAJIMA YOSHIFUMI
IPC分类号： F02C7/00 , B05D5/00 , C23C4/04 , C23C4/18 , F01D5/28 , F23R3/42
摘要： PROBLEM TO BE SOLVED: To provide a method for manufacturing a thermal shield coating having a ceramic layer that can form a smooth surface with high erosion resistance, while securing an excellent thermal shield performance.SOLUTION: The method for manufacturing the thermal shield coating includes processes of: forming a metal bonding layer 12 on a heat resistant base 11; and forming the ceramic layer 13 on the metal bonding layer 12. The process of forming the ceramic layer 13 has steps of: forming a high porous layer 14 including pores by thermal spray coating on the metal bonding layer 12; forming a dense layer 15 having a more dense structure than the high porous layer 14, on the high porous layer 14; and polishing the top surface of the dense layer 15 such that the dense layer 15 becomes a predetermined thickness.
摘要翻译：要解决的问题：提供一种制造具有能够形成具有高耐侵蚀性的光滑表面的陶瓷层的热屏蔽涂层的方法，同时确保优异的隔热性能。解决方案：用于制造热屏蔽涂层的方法包括以下过程：在耐热基底11上形成金属粘合层12; 在金属接合层12上形成陶瓷层13.形成陶瓷层13的工序具有以下步骤：在金属接合层12上通过热喷涂形成包含孔的高多孔层14; 在高多孔层14上形成具有比高多孔层14更致密结构的致密层15; 并且对致密层15的顶表面进行抛光，使致密层15成为预定厚度。版权所有（C）2012，JPO＆INPIT

27. 发明专利

JP2011213520A Method for manufacturing powder for thermal spray, turbine member, and gas turbine 有权
标题翻译：用于制造热喷涂粉末，涡轮部件和气体涡轮的方法
公开(公告)号：JP2011213520A
公开(公告)日：2011-10-27
申请号：JP2010081961
申请日：2010-03-31
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： NANBA KATSUMI , TORIGOE TAIJI , NAGANO ICHIRO , KANEKO HIDEAKI , MATSUI TAKUYA , SHIDA MASAHITO , OKADA IKUO , MORI KAZUTAKA , TSURU YASUHIKO , ITO EISAKU , OKAJIMA YOSHIFUMI
IPC分类号： C04B35/628 , C23C4/00
摘要： PROBLEM TO BE SOLVED: To provide a method for manufacturing a powder for thermal spray capable of efficiently manufacturing a powder of an optional particle size in relatively easy operation.SOLUTION: A slurry 13 formed by mixing a raw material of the powder for thermal spray, water and a dispersing agent is adjusted to have a solid concentration of 60 wt.% or higher and 86 wt.% or lower. The slurry 13 is then supplied to a disk-type atomizer 12 of a spray dryer 10, of which the rotation speed is adjusted so that the discharging velocity of the slurry 13 from the atomizer 12 is 30 m/s or higher and 110 m/s or lower. The slurry 13 is dried in the spray dryer 10 to form a powder body 22 for thermal spray, which is subjected to heat treatment to obtain the powder for thermal spray having an optional particle size distribution.
摘要翻译：要解决的问题：提供一种制造用于热喷涂的粉末的方法，其能够在相对容易的操作中有效地制造任选粒径的粉末。溶液：通过将用于热喷涂的粉末的原料混合而形成的浆料13，将水和分散剂调节至固体成分浓度为60重量％以上且86重量％以下。然后将浆料13供给到喷雾干燥器10的盘式雾化器12，其中调节转速使得来自雾化器12的浆料13的排出速度为30m / s以上且110m / s或更低。将浆料13在喷雾干燥器10中干燥，形成用于热喷涂的粉末体22，进行热处理，得到具有任意粒度分布的热喷涂用粉末。

28. 发明专利

JP2005163172A Coating material for shielding heat, gas turbine member and gas turbine applied with the same material, and gas turbine 有权
标题翻译：用于屏蔽热的涂料，气体涡轮部件和气体涡轮应用于相同的材料和气体涡轮机
公开(公告)号：JP2005163172A
公开(公告)日：2005-06-23
申请号：JP2004304422
申请日：2004-10-19
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： TORIGOE TAIJI , MORI KAZUTAKA , OKADA IKUO , AOKI SUNAO , TAKAHASHI KOJI , OHARA MINORU , HIRATA TAKEHIKO , KANEKO HIDEAKI
IPC分类号： F01D25/00 , C23C4/10 , C23C4/18 , C23C14/08 , C23C30/00 , F02C7/00 , F02C7/24
摘要： PROBLEM TO BE SOLVED: To provide a coating material for shielding heat, coating a gas turbine member whereby a higher heat-shielding property and a higher stripping resistance are obtained. SOLUTION: The coating material for shielding heat is obtained by stacking a metallic bond layer on the surface of a base material, and further stacking, on the metallic bond layer, a ceramics layer composed of partially stabilized zirconia partially stabilized by addition of Dy 2 O 3 and/or Yb 2 O 3 as an additive. Preferably, the additive is Dy 2 O 3 and Yb 2 O 3 , the ratio of the Dy 2 O 3 to be added is 0.01 to 16.00 wt%, the ratio of the Yb 2 O 3 to be added is 0.01 to 17.00 wt%, and the total of the ratio of the Dy 2 O 3 to be added and the ratio of the Yb 2 O 3 to be added is 10 to 20 wt%, and the ratio of ZrO 2 other than a stabilizer to be added is 80 to 90 wt%. COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：为了提供用于屏蔽热量的涂层材料，涂覆燃气轮机部件，由此获得更高的热屏蔽性和更高的剥离性。解决方案：用于屏蔽热的涂料通过在基材的表面上堆叠金属粘合层而获得，并且在金属粘合层上进一步堆叠由部分稳定的部分稳定的氧化锆组成的陶瓷层，通过添加作为添加剂的Dy 2 3 和/或Yb O 3 。优选地，添加剂为Dy 3 3和/或SBB，其中Dy 2 O 3 的比例为0.01〜16.00重量％，添加的Yb 2 O 3 为0.01〜17.00重量％，添加的Dy 2 3 的比例和Yb 2 添加量为10〜20重量％，添加稳定剂以外的ZrO 2 SB <2 SB比例为80〜90重量％。版权所有（C）2005，JPO＆NCIPI

29. 发明专利

JP2004058091A Casting mold to mold unidirectional solidified blade, manufacturing method for unidirectional blade using the mold and unidirectional solidified blade 有权
公开(公告)号：JP2004058091A
公开(公告)日：2004-02-26
申请号：JP2002219228
申请日：2002-07-29
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： OSAWA KEI , ISHIKAWA HIROSHI , KANEKO HIDEAKI , OKADA IKUO , TAKAHASHI KOJI , IZUTSU DAISUKE
IPC分类号： F01D5/28 , B22C9/04 , B22C9/22 , B22D27/04 , B22D27/18 , F02C7/00
摘要： PROBLEM TO BE SOLVED: To provide a casting mold for a blade to manufacture a unidirectional solidified blade which can control the number of crystal grains to the most suitable one.
SOLUTION: In the casting mold for the blade 10 to form a turbine blade which is the unidirectional solidified blade, a plurality of crystal nucleation parts 14 which are projected to the same direction as the growth direction of the crystal grains during the molding of the turbine blade (a longitudinal direction of the blade), are arranged in a section around the blade molding section 11 in the bottom of a platform formation part 12.
COPYRIGHT: (C)2004,JPO

30. 发明专利

JP2003311392A Method for manufacturing unidirectional solidified wing, and unidirectional solidified wing 审中-公开
标题翻译：制造单向固化方法和单向固化方法
公开(公告)号：JP2003311392A
公开(公告)日：2003-11-05
申请号：JP2002116220
申请日：2002-04-18
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： OSAWA KEI , KANEKO HIDEAKI , OKADA IKUO , TAKAHASHI KOJI
IPC分类号： F01D5/28 , B22C9/06 , B22C9/22 , B22D21/00 , B22D23/00 , B22D27/04 , F02C7/00
摘要： PROBLEM TO BE SOLVED: To provide a method for producing a unidirectional solidified wing having high mechanical strength and excellent product yield, and to provide the unidirectional solidified wing.
SOLUTION: The method for producing the unidirectional solidified wing used for wing material of an energy machinery driven at high temperature, comprises a process in which a simple crystal block combining nucleus crystals or a unidirectional solidified columnar nucleus crystals are set into a starter block supported with a cooling setter in a mold and communicated with a selector so that the crystal orientation becomes the longitudinal direction of the wing and the crystal orientation in a wing profile part becomes parallel with a tangential line of a wing profile cross sectional shape and a platform part becomes parallel with the platform end surface, a process in which the nucleus crystals and the selector are preheated till a prescribed temperature and the surrounding atmosphere in the mold is evacuated, and a process in which molten metal is supplied into the mold and successively, the temperature of cooling setter is relatively dropped to the mold while adjusting the selector temperature, and the columnar crystal starting the solidification with the nucleus crystal as the starting point is unidirectionally solidified to the desired crystal orientation while guiding with the selector.
COPYRIGHT: (C)2004,JPO
摘要翻译：要解决的问题：提供一种具有高机械强度和优异的产物收率的单向固化翼的制造方法，并提供单向凝固翼。解决方案：用于高温驱动的能量机械的机翼材料的单向凝固翼的制造方法包括将核晶体或单向凝固柱状核晶体结合的简单晶块设置为起动器的方法模块中的冷却装置支撑并与选择器连通，使得晶体取向<001>成为机翼的纵向方向，并且机翼轮廓部分中的晶体取向<100>变得与机翼的切线平行剖面形状和平台部分与平台端面平行，将核晶体和选择器预热至预定温度并使模具中的周围环境抽真空的过程，以及熔融金属为供应到模具中，并且相应地，在调节t的同时，冷却装置的温度相对下降到模具其选择器温度，以晶核为起点开始凝固的柱状晶体在选择器引导的同时单向凝固至所需的晶体取向。版权所有（C）2004，JPO

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