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1. 发明申请

WO2005005888A8 COOLING STRUCTURE OF GAS TURBINE TAIL PIPE 审中-公开
标题翻译：气体涡轮尾管的冷却结构
公开(公告)号：WO2005005888A8
公开(公告)日：2005-05-12
申请号：PCT/JP0316484
申请日：2003-12-22
申请人： MITSUBISHI HEAVY IND LTD , TAKAYA HIROYA , TERAZAKI MASAO
发明人： TAKAYA HIROYA , TERAZAKI MASAO
IPC分类号： F23R3/42 , F01D9/02 , F02C7/18 , F02C7/28 , F23R3/00
CPC分类号： F23R3/002 , F01D9/023 , F05D2240/55 , F05D2260/201 , F23R2900/03042 , F23R2900/03044
摘要： A cooling structure of a gas turbine tail pipe, wherein a plate spring (6) of shook shape in cross section is fitted, from the underside, near the other end (b) of an impingement cooling plate (4). The lower side one end (c) of the plate spring is fixedly welded to a rib (1d) and the upper side other end (d) thereof is freed and allowed to abut on the impingement cooling device (4) near the other end (b) thereof by the elastic force thereof. Thus, a clearance formed between the impingement cooling plate (4) and a tail pipe (1) can be shielded on the rib (1d) side while avoiding that a thermal stress occurred, for example, in the rib (1d) affects the impingement cooling plate (4).
摘要翻译：燃气轮机尾管的冷却结构，其中横截面为摇摆形状的板簧（6）从下侧安装在冲击冷却板（4）的另一端（b）附近。板簧的下侧一端（c）被固定地焊接到肋（1d），并且其上侧的另一端（d）被释放并允许其靠近另一端的冲击冷却装置（4） b）其弹力。因此，在冲击冷却板（4）和尾管（1）之间形成的间隙可以在肋（1d）侧被屏蔽，同时避免发生热应力，例如在肋（1d）中影响冲击冷却板（4）。

2. 发明公开

EP2522830A4 GAS TURBINE 有权
公开(公告)号：EP2522830A4
公开(公告)日：2013-06-19
申请号：EP10842143
申请日：2010-11-11
申请人： MITSUBISHI HEAVY IND LTD
发明人： KOJIMA KATSUHISA , UEDA YASUTOSHI , SONODA TAKASHI , TERAZAKI MASAO
IPC分类号： F02C7/052 , F01D25/00 , F02C7/055 , F02C7/143 , F02C7/18
CPC分类号： F01D25/12 , F02C7/18 , F05D2260/606 , F05D2260/607

3. 发明公开

EP0805263A4 VANE FOR GAS TURBINE 失效
标题翻译： GASTURBINENSCHAUFEL
公开(公告)号：EP0805263A4
公开(公告)日：1999-10-20
申请号：EP96938510
申请日：1996-11-20
申请人： MITSUBISHI HEAVY IND LTD
发明人： AOYAMA KUNIAKI , TERAZAKI MASAO
IPC分类号： F01D5/18 , F02C7/18
CPC分类号： F01D5/186 , F05D2260/202
摘要： Shower head cooling in film cooling for vanes of a gas turbine has a drawback that since the cooling holes are arranged linearly from the tip side to the hub side, the pressures at the respective cooling holes are different from one another in association with the swirl and so film cooling cannot be uniformly effected. Such drawback being removed, the pressures at all the cooling holes are uniform and the film cooling is also uniform. A plurality of shower head cooling holes (1) made in the tip end of a vane (2) are so arranged differently as to be adapted to the swirl which revolves rightward in the combustor and the swirl revolves leftward. For the rightward swirl, the cooling holes are arranged on a line extending from the tip side (TS) where the line is curved to the left when viewed from the upstream side of the vane (2), to the hub side (HS) where the line is curved to the rightward when viewed from the upstream side of the vane (2). For the leftward swirl, the cooling holes are arranged on a line extending reversely to the above line. Thus the influence of the swirl is averted, the pressures are made constant at the respective cooling holes (1), and uniform cooling is achieved.
摘要翻译：用于燃气轮机叶片的膜冷却中的喷淋头冷却的缺点在于，由于冷却孔从尖端侧到轮毂侧线性地布置，所以各个冷却孔处的压力与涡流相关地彼此不同所以薄膜冷却不能均匀地进行。这种缺点被消除，所有冷却孔处的压力均匀并且薄膜冷却也是均匀的。在叶片（2）的末端制成的多个喷头冷却孔（1）的布置方式不同，以适应在燃烧器中向右旋转的旋涡并且旋涡向左旋转。对于向右旋转，当从叶片（2）的上游侧观察时，冷却孔布置在从线弯曲的尖端侧（TS）延伸到轮毂侧（HS）的左侧的线上当从叶片（2）的上游侧观察时，该线向右弯曲。对于向左漩涡，冷却孔布置在与上述线相反的线上。因此避免了涡流的影响，在相应的冷却孔（1）处使压力恒定，并且实现均匀的冷却。

4. 发明专利

DE102004057985A1 Gas-turbine combustion apparatus for use in vehicle, has turbine bypass mechanism has a shut-off valve which controls displacement of exhaust by the circular pipe out of the compartment through the exhaust gas opening material 未知
公开(公告)号：DE102004057985A1
公开(公告)日：2005-07-14
申请号：DE102004057985
申请日：2004-12-01
申请人： MITSUBISHI HEAVY IND LTD
发明人： TERAZAKI MASAO , KANEZAWA YOSHIYUKI , HORIKAWA HIDETO
IPC分类号： F01D25/24 , F01D17/00 , F01D25/28 , F01D25/30 , F02C7/00 , F02C7/057 , F02C9/00 , F02C9/18 , F02C9/20 , F23R3/16 , F23R3/26 , F23R3/42
摘要： A steam-extraction pipe (12) performs uniform steam extraction of compressed air discharged in a compartment (5). A circular pipe (11) collects compressed air after steam extraction and exhausts to an exhaust gas opening material (10). A turbine bypass mechanism has a shut-off valve (14) which controls displacement of exhaust by circular pipe out of the compartment through the exhaust gas opening material. The exhaust gas opening material is fitted into the manhole (4a) of a casing (4) and connected outside the compartment.

5. 发明专利

DE69628818D1 未知
公开(公告)号：DE69628818D1
公开(公告)日：2003-07-31
申请号：DE69628818
申请日：1996-11-20
申请人： MITSUBISHI HEAVY IND LTD
发明人： AOYAMA KUNIAKI , TERAZAKI MASAO
IPC分类号： F01D5/18 , F02C7/18
摘要： Shower head cooling in film cooling for vanes of a gas turbine has a drawback that since the cooling holes are arranged linearly from the tip side to the hub side, the pressures at the respective cooling holes are different from one another in association with the swirl and so film cooling cannot be uniformly effected. Such drawback being removed, the pressures at all the cooling holes are uniform and the film cooling is also uniform. A plurality of shower head cooling holes (1) made in the tip end of a vane (2) are so arranged differently as to be adapted to the swirl which revolves rightward in the combustor and the swirl revolves leftward. For the rightward swirl, the cooling holes are arranged on a line extending from the tip side (TS) where the line is curved to the left when viewed from the upstream side of the vane (2), to the hub side (HS) where the line is curved to the rightward when viewed from the upstream side of the vane (2). For the leftward swirl, the cooling holes are arranged on a line extending reversely to the above line. Thus the influence of the swirl is averted, the pressures are made constant at the respective cooling holes (1), and uniform cooling is achieved.

6. 发明专利

CA2209851C GAS TURBINE BLADE 未知
公开(公告)号：CA2209851C
公开(公告)日：2000-05-02
申请号：CA2209851
申请日：1996-11-20
申请人： MITSUBISHI HEAVY IND LTD
发明人： AOYAMA KUNIAKI , TERAZAKI MASAO
IPC分类号： F01D5/18 , F02C7/18
摘要： In shower head cooling out of a prior art film cooling of gas turbine blade, as cooling holes (1) are arrayed on a straight line toward blade hub side (HS) from blade tip side (TS), there occur different pressures at each position of the cooling holes (1) with result that uniform film cooling cannot be done. The present invention is to provide a gas turbine blade which dissolves said problem in the prior art and attains uniform pressure over the shower head cooling holes, so that uniform film cooling can be done. A plurality of shower head cooling holes (1) bored in blade leading edge portion are arranged on one line biased so as to correspond to a respective case where direction of swirling flow in combustor is clockwise or counter-clockwise; that is, on one line biased to the left hand side, seen from upstream, toward blade hub side (HS) from blade tip side (TS) in the former case or on one line biased to the reverse side in the latter case, thus avoiding influence of the swirling flow, pressure at each position of the cooling holes (1) is made constant, so that uniform cooling can be attained.

7. 发明专利

DE69504400T2 未知
公开(公告)号：DE69504400T2
公开(公告)日：1999-05-27
申请号：DE69504400
申请日：1995-04-11
申请人： MITSUBISHI HEAVY IND LTD
发明人： TERAZAKI MASAO , TSUKAGOSHI KEIZO
IPC分类号： F01D9/02 , F01D5/18 , F01D25/00
摘要： A gas turbine cooling blade for maintaining a cooling effect and preventing sticking of deposits to the belly surface of the blade. This blade is provided with a relatively big cooling hole 5 formed on the belly part of a hollow stator blade 1 at an acute angle with the blade surface for blowing off cooling air and a relatively small cooling hole 6 disposed on the downstream thereof at an acuter angle with the blade surface so as to bring the jet of cooling air along therewith for blowing off cooling air.

8. 发明专利

AR044702A1 DISEÑO PARA REFRIGERAR UNA PIEZA DE TRANSICION DE UNA TURBINA DE GAS 未知
公开(公告)号：AR044702A1
公开(公告)日：2005-09-21
申请号：ARP040102067
申请日：2004-06-15
申请人： MITSUBISHI HEAVY IND LTD
发明人： TAKAYA HIROYA , TERAZAKI MASAO
IPC分类号： F23R3/42 , F01D9/02 , F02C7/18 , F02C7/28 , F23R3/00 , F02C7/12
摘要： Un resorte de placa, (6), que tiene una sección transversal en forma de gancho desde su parte inferior, es instalado en una vecindad de un extremo "b" de una placa de refrigeración por choque, (4). Uno de los extremos, "c" en el lado inferior está fijado a un nervio (1b) mediante soldadura, mientras que el otro extremo "b" en el lado superior está libre, lo cual le hace contactar estrechamente la vecindad del otro extremo "b" de la placa de refrigeración por choque, (4), gracias a su fuerza elástica. Esta condición hace que sea posible sellar un huelgo formado entre la placa de refrigeración por choque, (4), y la pieza de transición, (1), en el lado de un nervio, (1d), con lo cual se impide que las tensiones térmicas generadas en el nervio (1d), por ejemplo, afecten la placa de refrigeración por choque, (4).

9. 发明专利

CA2496621A1 COOLING STRUCTURE OF GAS TURBINE TAIL PIPE 未知
公开(公告)号：CA2496621A1
公开(公告)日：2005-01-20
申请号：CA2496621
申请日：2003-12-22
申请人： MITSUBISHI HEAVY IND LTD
发明人： TERAZAKI MASAO , TAKAYA HIROYA
IPC分类号： F23R3/42 , F01D9/02 , F02C7/18 , F02C7/28 , F23R3/00
摘要： A cooling structure of a gas turbine tail pipe, wherein a plate spring (6) o f shook shape in cross section is fitted, from the underside, near the other e nd (b) of an impingement cooling plate (4). The lower side one end (c) of the plate spring is fixedly welded to a rib (1d) and the upper side other end (d ) thereof is freed and allowed to abut on the impingement cooling device (4) near the other end (b) thereof by the elastic force thereof. Thus, a clearan ce formed between the impingement cooling plate (4) and a tail pipe (1) can be shielded on the rib (1d) side while avoiding that a thermal stress occurred, for example, in the rib (1b) affects the impingement cooling plate (4).

10. 发明专利

CA2230291A1 COOLING STRUCTURE TO COOL PLATFORM FOR DRIVE BLADES OF GAS TURBINE 未知
公开(公告)号：CA2230291A1
公开(公告)日：1998-08-25
申请号：CA2230291
申请日：1998-02-23
申请人： MITSUBISHI HEAVY IND LTD
发明人： TERAZAKI MASAO , TOMITA YASUOKI , AKITA EIJI
IPC分类号： F01D5/08 , F01D5/18 , F01D5/30 , F02C7/18 , F01D25/12
摘要： A mechanism for cooling the platform for the drive blades of a gas turbine, which uses a simple configuration which will reliably cool the platform, the mechanism being constituted by cooling channels in the interior of the platform which open out from one of the cooling air channels for cooling the turbine blades and which exit the platform through the edge nearest the tail. In a preferred embodiment cooling channels 6a and 6b in platform 2 open out from the entrance to blade cooling channel 5a and travel from the head of the blade along the blade sides 3c and 3b and exit through the edge 3e near the tail of the blade. This structure diverts a portion of the cooling air 4a entering the blade 3 from the cooling channel in base 1 in order to cool platform 2. Alternatively or in addition, at least one of the following types of cooling passages may be provided: (a) cooling air channels 7, which extend from enclosed air space 11 below platform 2 to the upper surface of the platform; (b) convection cooling channels 8 which extend from the leading edge of the platform to the upper surface of the platform at the front or rear side of the blade, and/or (c) air channels 9 which extend on the rear of the turbine blade obliquely from the underside of the platform to the trailing edge of the platform. These various channels or combinations thereof constitute a cooking structure through which air can flow to cool a platform for the drive blades of a gas turbine in an efficient and effective manner.

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