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1. 发明授权

US06290462B1 Gas turbine cooled blade 有权
标题翻译：燃气轮机冷却叶片
公开(公告)号：US06290462B1
公开(公告)日：2001-09-18
申请号：US09272559
申请日：1999-03-19
申请人： Tatsuo Ishiguro , Koji Watanabe , Masaaki Matsuura , Kenichiro Takeishi , Junichiro Masada , Yasuoki Tomita , Kiyoshi Suenaga
发明人： Tatsuo Ishiguro , Koji Watanabe , Masaaki Matsuura , Kenichiro Takeishi , Junichiro Masada , Yasuoki Tomita , Kiyoshi Suenaga
IPC分类号： F01D1100
CPC分类号： F01D5/187 , F05D2250/185 , F05D2260/2212
摘要： A gas turbine cooled blade is constructed without an increase in the number of parts or time requirements, in which seal air is maintained at a lower temperature with the heat exchange rate being suppressed, and the heat transfer rate of the cooling medium in cooling passage is enhanced. A plurality of cooling passages (A, B, C, D, E) is provided in a blade, and the first row cooling passage (A) is covered at the blade inner and outer peripheries and communicates with the second row cooling passage (B) through communication holes (6) and with the main flow gas path through film cooling holes (7). The second row cooling passage (B) communicates with the blade inner peripheral cavity (10) to form a seal air supply passage. A plurality of ribs (31) are disposed on the inner wall of cooling passage (22) with a predetermined pitch (P). The ribs are arranged alternately and are inclined against cooling medium flow with respective higher first end contacting lower side faces of an immediately upstream rib at a position on both side portions of cooling passage (22). High heat transfer rate areas are formed on both side portions of cooling passage (22), and the average heat transfer rate in cooling passage is enhanced.
摘要翻译：在不增加部件或时间要求的情况下构建燃气轮机冷却叶片，其中密封空气在热交换率被抑制下保持在较低温度，并且冷却通道中的冷却介质的传热速率为增强。多个冷却通道（A，B，C，D，E）设置在叶片中，第一排冷却通道（A）被覆盖在叶片的内周和外周，并与第二排冷却通道）通过连通孔（6）并且主流动气体通道通过膜冷却孔（7）。第二排冷却通道（B）与叶片内周腔（10）连通，形成密封空气供给通道。多个肋（31）以预定的间距（P）设置在冷却通道（22）的内壁上。这些肋交替布置并且相对于冷却介质流倾斜，并且在冷却通道（22）的两侧部分的位置处，相应较高的第一端接触紧紧上游的肋的下侧面。在冷却通道（22）的两侧形成有高的传热率区域，并且冷却通路的平均传热率提高。

2. 发明授权

US06186740B1 Gas turbine cooling blade 失效
标题翻译：燃气轮机冷却叶片
公开(公告)号：US06186740B1
公开(公告)日：2001-02-13
申请号：US09035217
申请日：1998-03-05
申请人： Kenichiro Takeishi , Kiyoshi Suenaga , Kazuo Uematsu
发明人： Kenichiro Takeishi , Kiyoshi Suenaga , Kazuo Uematsu
IPC分类号： F01D518
CPC分类号： F01D5/189 , F05D2260/201 , F05D2260/202 , Y02E20/16
摘要： In a gas turbine cooling blade, cooling passages are defined by ribs formed therein. The cooling blade comprises an insert fitted in one of the cooling passages at the front edge of the blade, a plurality of nozzles formed in the front face of the insert and used to spray an impact jet of a refrigerant against the inner surface of the front edge of the blade, thereby cooling the inner surface, and a passage formed between the rear face of the insert and the rib and communicating with a rear-side flow.
摘要翻译：在燃气轮机冷却叶片中，冷却通道由其中形成的肋限定。冷却叶片包括嵌入在叶片前缘的一个冷却通道中的插入件，形成在插入件的前表面中的多个喷嘴，用于将制冷剂的冲击射流喷射到前部的内表面上从而冷却内表面，以及形成在插入件的后表面和肋之间并与后侧流连通的通道。

3. 发明授权

US07694522B2 Heat exchanging wall, gas turbine using the same, and flying body with gas turbine engine 有权
标题翻译：换热墙，采用相同的燃气轮机，带燃气轮机的飞机
公开(公告)号：US07694522B2
公开(公告)日：2010-04-13
申请号：US10912565
申请日：2004-08-06
申请人： Tomoyoshi Nakae , Kenichiro Takeishi , Masaaki Matsuura , Tsuyoshi Kitamura , Atsushi Moriwaki
发明人： Tomoyoshi Nakae , Kenichiro Takeishi , Masaaki Matsuura , Tsuyoshi Kitamura , Atsushi Moriwaki
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/002 , F23R3/005 , F23R2900/03043 , F28F3/02 , F28F3/022 , F28F13/12 , Y02T50/675
摘要： A heat exchange wall include a base plate; a plurality of first protrusions distributedly provided on a surface of the base plate, and a plurality of second protrusions distributedly provided on the base plate surface. The height of the second protrusion in a normal direction of the base plate is desirably less than ½ of a height of the first protrusion in the normal direction. The height of the second protrusion in the normal direction is desirably between 1/20 and ¼ of the height of the first protrusion in the normal direction. More desirably, the height of the second protrusion in the normal direction is 1/10 of the height of the first protrusion in the normal direction.
摘要翻译：热交换壁包括基板; 多个第一突起分布设置在基板的表面上，多个第二突起分布设置在基板表面上。第二突起在基板的法线方向上的高度优选小于第一突起在法线方向的高度的1/2。第二突起在法线方向的高度优选为第一突起的高度在正常方向的1/20和1/4之间。更优选地，第二突起在法线方向上的高度是第一突起在法线方向上的高度的1/10。

4. 发明授权

US07300251B2 Turbine cooling vane of gas turbine engine 有权
标题翻译：燃气轮机的涡轮冷却叶片
公开(公告)号：US07300251B2
公开(公告)日：2007-11-27
申请号：US10544844
申请日：2004-03-03
申请人： Tsuyoshi Kitamura , Kenichiro Takeishi , Masaaki Matsuura , Ryoma Nogami
发明人： Tsuyoshi Kitamura , Kenichiro Takeishi , Masaaki Matsuura , Ryoma Nogami
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F01D5/186 , F05D2260/201 , Y02T50/676
摘要： A cooled blade of a small gas turbine engine can enhance cooling performance without increasing the amount of cooling air in a simple configuration. A cooled turbine blade is provided with a cooling passageway 12 formed inside thereof, making the cooling air flow therein. Film-cooling holes 13 penetrate from an inner wall surface 111 to an external wall surface 112 and form a cooling film. An impingement cooling member 2 has a multiple number of small holes 21 ejecting the cooling air. A gap t made by the inner wall surface 111 and the impingement cooling member 2 has a sealing portion 14 mounted thereon which divides the gap in a blade chord direction.
摘要翻译：小型燃气涡轮发动机的冷却叶片可以在不以简单的结构增加冷却空气量的情况下提高冷却性能。冷却的涡轮叶片设置有形成在其内部的冷却通道12，使得冷却空气流入其中。薄膜冷却孔13从内壁面111穿过外壁面112形成冷却膜。冲击冷却构件2具有多个排出冷却空气的小孔21。由内壁面111和冲击冷却部件2构成的间隙t具有安装在其上的密封部14，该密封部14沿着叶片弦方向分隔间隙。

5. 发明申请

US20060210399A1 Turbine cooling vane of gas turbine engine 有权
标题翻译：燃气轮机的涡轮冷却叶片
公开(公告)号：US20060210399A1
公开(公告)日：2006-09-21
申请号：US10544844
申请日：2004-03-03
申请人： Tsuyoshi Kitamura , Kenichiro Takeishi , Masaaki Matsuura , Ryoma Nogami
发明人： Tsuyoshi Kitamura , Kenichiro Takeishi , Masaaki Matsuura , Ryoma Nogami
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F01D5/186 , F05D2260/201 , Y02T50/676
摘要： The present invention is intended to provide a cooled blade of a small gas turbine engine which can enhance cooling performance without increasing an amount of cooling air although it is in a simple configuration. A cooled turbine blade is provided with a cooling passageway 12 formed inside thereof, making the cooling air flow therein; film-cooling holes 13 formed, penetrating from an inner wall surface 111 to an external wall surface 112 and forming a cooling film; and an impingement cooling member 2 which has a multiple number of small holes 21 ejecting the cooling air. It is characterized by that a gap t made by the inner wall surface 111 and the impingement cooling member 2 has a sealing portion 14 mounted thereon which divides the gap in a blade chord direction.
摘要翻译：本发明旨在提供一种小型燃气涡轮发动机的冷却叶片，其可以在不增加冷却空气量的情况下提高冷却性能，尽管其处于简单的构造。冷却的涡轮叶片设置有形成在其内的冷却通道12，使冷却空气流入其中; 形成有从内壁面111向外壁面112贯通并形成冷却膜的薄膜冷却孔13。以及具有排出冷却空气的多个小孔21的冲击冷却部件2。其特征在于，由内壁面111和冲击冷却部件2构成的间隙t具有安装在其上的密封部14，该密封部14沿着叶片弦方向分隔间隙。

6. 发明申请

US20050047932A1 Heat exchanging wall, gas turbine using the same, and flying body with gas turbine engine 有权
标题翻译：换热墙，采用相同的燃气轮机，带燃气轮机的飞机
公开(公告)号：US20050047932A1
公开(公告)日：2005-03-03
申请号：US10912565
申请日：2004-08-06
申请人： Tomoyoshi Nakae , Kenichiro Takeishi , Masaaki Matsuura , Tsuyoshi Kitamura , Atsushi Moriwaki
发明人： Tomoyoshi Nakae , Kenichiro Takeishi , Masaaki Matsuura , Tsuyoshi Kitamura , Atsushi Moriwaki
IPC分类号： F23R3/00 , F04B23/00
CPC分类号： F23R3/002 , F23R3/005 , F23R2900/03043 , F28F3/02 , F28F3/022 , F28F13/12 , Y02T50/675
摘要： A heat exchange wall include a base plate; a plurality of first protrusions distributedly provided on a surface of the base plate, and a plurality of second protrusions distributedly provided on the base plate surface. The height of the second protrusion in a normal direction of the base plate is desirably less than ½ of a height of the first protrusion in the normal direction. The height of the second protrusion in the normal direction is desirably between {fraction (1/20)} and ¼ of the height of the first protrusion in the normal direction. More desirably, the height of the second protrusion in the normal direction is {fraction (1/10)} of the height of the first protrusion in the normal direction.
摘要翻译：热交换壁包括基板; 多个第一突起分布设置在基板的表面上，多个第二突起分布设置在基板表面上。第二突起在基板的法线方向上的高度优选小于第一突起在法线方向的高度的1/2。第二突起在法线方向的高度优选为{法线方向的第一突起的高度的1/20〜1/4，更优选地，第二突起在法线方向的高度为{分数（第一突起在正常方向的高度的1/10。

7. 发明授权

US5873695A Steam cooled blade 失效
标题翻译：蒸汽冷却叶片
公开(公告)号：US5873695A
公开(公告)日：1999-02-23
申请号：US861539
申请日：1997-05-22
申请人： Kenichiro Takeishi , Yoshikuni Kasai
发明人： Kenichiro Takeishi , Yoshikuni Kasai
IPC分类号： F01D5/18 , F02C7/18 , F04D29/32 , F04D29/58 , F04D29/38
CPC分类号： F01D5/187 , F05D2260/205 , F05D2260/2212 , F05D2260/2322
摘要： A steam cooled blade operating in a high temperature gas with a high cooling effect on a trailing edge portion has an impingement plate, disposed in the blade lengthwise direction within a trailing edge side cooling passage formed on a trailing edge side of a moving blade. The impingement plate partitions the trailing edge side cooling passage into a convection cooling steam passage, into which steam is introduced, and an impingement cooling steam passage, formed along a trailing edge of the moving blade. The steam cooled blade further has a by-pass passage 14 for joining the steam, after it is used for cooling the moving blade, flowing from a blade tip side of the impingement cooling steam passage with the steam flowing to a leading edge direction of the moving blade from the convection cooling steam passage.
摘要翻译：在后缘部分具有高冷却效果的高温气体中工作的蒸汽冷却叶片具有在形成于活动叶片的后缘侧的后缘侧冷却通道中沿叶片长度方向设置的冲击板。冲击板将后缘侧冷却通道分隔成引入蒸汽的对流冷却蒸汽通道和沿着动叶片的后缘形成的冲击冷却蒸汽通道。蒸汽冷却叶片还具有用于连接蒸汽的旁通通道14，在用于冷却动叶片之后，蒸汽流经冲击冷却蒸汽通道的叶片末端侧流动，从对流冷却蒸汽通道移动叶片。

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