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1. 发明授权

US4662820A Turbine stage structure 失效
标题翻译：涡轮舞台结构
公开(公告)号：US4662820A
公开(公告)日：1987-05-05
申请号：US752860
申请日：1985-07-08
申请人： Tetsuo Sasada , Takeshi Sato , Haruo Urushidani , Katsukuni Hisano , Ryoichi Kaneko , Kazuo Ikeuchi , Kunio Tsuji
发明人： Tetsuo Sasada , Takeshi Sato , Haruo Urushidani , Katsukuni Hisano , Ryoichi Kaneko , Kazuo Ikeuchi , Kunio Tsuji
IPC分类号： F01D9/02 , F01D11/08 , F01D11/02
CPC分类号： F04D29/161 , F01D11/08
摘要： A stage structure of an axial turbine includes a stationary inner ring, a stationary outer wall, a row of stationary blades mounted on the stationary inner ring and outer wall, a row of moving blades, and a shroud ring mounted on the tips of the moving blades. An annular solid substance, disposed immediately downstream of an axial gap formed between an axial end of the shroud ring and surface of the outer wall axially facing the axial end of the shroud ring, reduces an expansion space provided immediately downstream of the axial gap, whereby circulation of an ejection flow from a main stream through the axial gap is reduced so that the turbine stage efficiency is improved. The annular solid substance may be a ring fixed to the stationary outer wall, a protrusion or a cylinder formed by a portion of the outer wall.
摘要翻译：轴流式涡轮机的级结构包括固定内环，固定外壁，安装在固定内环和外壁上的一排固定叶片，一排活动叶片和安装在移动的尖端上的护罩环刀片。设置在形成在护罩环的轴向端部和轴向面向护罩环的轴向端部的外壁的表面之间的轴向间隙的紧邻下游的环形固体物质减小了紧邻轴向间隙的下游的膨胀空间，由此从主流通过轴向间隙的喷射流的循环减少，从而提高了涡轮级的效率。环状固体物质可以是固定在静止的外壁上的环，由外壁的一部分形成的突起或圆筒。

2. 发明授权

US5121597A Gas turbine combustor and methodd of operating the same 失效
标题翻译：燃气轮机及其运行方法
公开(公告)号：US5121597A
公开(公告)日：1992-06-16
申请号：US470596
申请日：1990-01-26
申请人： Haruo Urushidani , Seiichi Kirikami , Isao Sato , Nobuo Shimizu , Osamu Arai , Akira Shimura , Michio Kuroda , Tsuguaki Koga , Tadashi Kurokawa , Yoji Ishibashi , Katsukuni Hisano
发明人： Haruo Urushidani , Seiichi Kirikami , Isao Sato , Nobuo Shimizu , Osamu Arai , Akira Shimura , Michio Kuroda , Tsuguaki Koga , Tadashi Kurokawa , Yoji Ishibashi , Katsukuni Hisano
IPC分类号： F02C7/26 , F02C9/34 , F23C99/00 , F23R3/16 , F23R3/20 , F23R3/26 , F23R3/34
CPC分类号： F02C9/34 , F02C7/26 , F23R3/16 , F23R3/26 , F23R3/34 , F05D2270/31
摘要： A gas turbine combustor and a method of operating the gas turbine combustor, with the gas turbine combustor comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of the combustion sleeve and having an air and fuel supply system, and a combustion main chamber disposed on a downstream side of the sub-chamber and having an air and fuel supply system. The combustion sub-chamber and combustion main chamber are formed in such a manner that the start-up of the gas turbine is effected by the hot combustion gas generated in the sub-chamber. The combustion sub-chamber is provided with an inner sleeve protruding from a side wall of the sub-chamber such that a tip of the inner sleeve is located in the vicinity of a downstream end of the sub-chamber, and a fuel nozzle is provided in a tip of the inner sleeve for increasing the fuel-to-air ratio during an initiating period of an increase in the gas turbine rotation speed.

3. 发明授权

US5069029A Gas turbine combustor and combustion method therefor 失效
标题翻译：燃气轮机燃烧器及其燃烧方法
公开(公告)号：US5069029A
公开(公告)日：1991-12-03
申请号：US563191
申请日：1990-08-06
申请人： Michio Kuroda , Seiichi Kirikami , Katsukuni Hisano , Nobuyuki Iizuka , Haruo Urushidani , Isao Sato , Yoji Ishibashi , Takashi Ohmori
发明人： Michio Kuroda , Seiichi Kirikami , Katsukuni Hisano , Nobuyuki Iizuka , Haruo Urushidani , Isao Sato , Yoji Ishibashi , Takashi Ohmori
IPC分类号： F23C99/00 , F23R3/26 , F23R3/34 , F02C3/14 , F23R3/32
CPC分类号： F23R3/26 , F23R3/346
摘要： A gas turbine combustor comprising a head combustion chamber and a rear combustion chamber connected to a downstream side of the head combustion chamber, a first stage burner for premixing first stage fuel and air and supplying the resultant fuel and air premixture into the head combustion chamber to effect first stage premix combution, a second stage burner for premixing second stage fuel and air and the resultant fuel and air premixture into the rear combustion chamber to effect premix combustion in addition to the first stage premix combustion, and a device for regulating flow rates of combustion air to be premixed with first and second stage fuel. The combustor is further provided with a pilot burner in the head combustion chamber to form pilot flame and stabilize the first stage premix combustion.

4. 发明授权

US4478082A Method and apparatus for detecting rubbing in a rotary machine 失效
标题翻译：用于检测旋转机器中的摩擦的方法和装置
公开(公告)号：US4478082A
公开(公告)日：1984-10-23
申请号：US408949
申请日：1982-08-17
申请人： Ichiya Sato , Takao Yoneyama , Tsuguaki Koga , Kazuo Ikeuchi , Katsukuni Hisano
发明人： Ichiya Sato , Takao Yoneyama , Tsuguaki Koga , Kazuo Ikeuchi , Katsukuni Hisano
IPC分类号： G01M13/04 , G01H1/00 , G01H1/04 , G01H17/00 , G01M99/00 , G01N29/12 , G01M13/00
CPC分类号： G01N29/12 , G01H1/003 , G01N2291/014 , G01N2291/101 , G01N2291/2693
摘要： A method and apparatus for detecting the occurrence of rubbing in a rotary machine, in which at least one acoustic sensor is mounted on at least the rotor part or the stator part of the rotary machine, and the output signal from the acoustic sensor is detected and then filtered to extract a frequency component having a frequency substantially equal to the rotational frequency of the rotary machine, so as to detect the occurrence of rubbing in the rotary machine as early as possible and also to locate the source of the rubbing. Even when the occurrence of abnormal metal-to-metal contact at a bearing of the rotary machine is detected, it is discriminated from rubbing so that the occurrence of the rubbing can be reliably detected.
摘要翻译：一种在旋转机器中检测摩擦发生的方法和装置，其中至少一个声传感器安装在至少旋转机器的转子部分或定子部分上，并且检测来自声传感器的输出信号，然后过滤以提取频率基本上等于旋转机的旋转频率的频率分量，以便尽可能早地检测旋转机器中的摩擦的发生并且还可以定位摩擦源。即使检测到在旋转机械的轴承处发生异常金属对金属的接触，也可以将其与摩擦进行区别，从而能够可靠地检测摩擦的发生。

5. 发明授权

US4187685A Method and system for effecting control governing of a steam turbine 失效
标题翻译：实现蒸汽轮机控制控制的方法和系统
公开(公告)号：US4187685A
公开(公告)日：1980-02-12
申请号：US876944
申请日：1978-02-10
申请人： Kunio Tsuji , Katsukuni Hisano , Akira Sakai , Shozo Nakamura
发明人： Kunio Tsuji , Katsukuni Hisano , Akira Sakai , Shozo Nakamura
IPC分类号： F01D17/24 , F01K13/02
CPC分类号： F01K13/02
摘要： A method and system for effecting control governing of a steam turbine wherein the steam chamber of a first stage nozzle is divided into a plurality of steam compartments, control valves each connected to one of the steam compartments are individually operated for controlling the flow rate of steam introduced into the turbine, and the governing of the nozzle is effected by adjusting the flow rate of steam in accordance with a load. At low load, the degree of opening of the control valves is kept constant and the turbine is driven by steam of a reduced pressure by reducing the pressure of the steam at the inlet of the turbine so as to maintain, in a low load region, the volume flow rate of steam for a high load region. To cope with a change in the value of the load, the degree of opening corresponding to a predetermined change in the value of the load is set beforehand for each control valve. When the change in the value of the load is smaller than the predetermined change in the value of the load, the degree of opening of the control valve involved is adjusted. Conversely, when the change in the value of the load is greater than the predetermined change in the value of the load, the pressure of the steam at the inlet of the turbine is controlled.
摘要翻译：一种用于实现蒸汽轮机的控制控制的方法和系统，其中第一级喷嘴的蒸汽室被分成多个蒸汽隔间，各自连接到一个蒸汽隔间的控制阀被单独操作以控制蒸汽的流量引入涡轮机，并且通过根据负载调节蒸汽的流量来实现喷嘴的调节。在低负载下，控制阀的开度保持恒定，并且通过减小涡轮入口处的蒸汽的压力使涡轮由减压蒸汽驱动，以便在低负荷区域中保持，高负荷区域的蒸汽体积流量。为了应对负载值的变化，对于每个控制阀，预先设定对应于负载值的预定变化的开度。当负载值的变化小于负载值的预定变化时，调节所涉及的控制阀的开度。相反，当负载值的变化大于负载值的预定变化时，控制涡轮入口处的蒸汽的压力。

6. 发明授权

US4401411A Device for connecting turbine blades 失效
标题翻译：涡轮叶片连接装置
公开(公告)号：US4401411A
公开(公告)日：1983-08-30
申请号：US270599
申请日：1981-06-04
申请人： Katsukuni Hisano , Kazuo Ikeuchi , Makoto Nishimura , Hazime Sibaoka , Kiyoshi Namura , Akira Isida , Katsumi Oyabu
发明人： Katsukuni Hisano , Kazuo Ikeuchi , Makoto Nishimura , Hazime Sibaoka , Kiyoshi Namura , Akira Isida , Katsumi Oyabu
IPC分类号： F01D5/22 , F01D25/04
CPC分类号： F01D5/225 , Y10S416/50
摘要： A device for connecting the turbine blades of a turbine having a plate-shaped member provided at the radially outer end of each turbine blade and extended substantially at a right angle to the longitudinal plane of the turbine blade. The plate-shaped member is projected from the leading and trailing edges of the turbine blade, and is provided with through bores formed in each projected portion. Connecting members having cylindrical pins or the like projections are disposed between two adjacent turbine blades in such a manner that the projections are rotatably received by respective through bores. Namely, one of the connecting members is connected to the plate-shaped member of the leading edge of the turbine blade while the other connecting member is connected to the plate-shaped member of the trailing edge of the preceding adjacent turbine blade. The connecting members are disposed such that they partially underlie the plate-shaped members of the adjacent turbine blades and that they make contact with each other during the running of the turbine thereby to restrict the untwisting of the turbine blades while attaining a vibration damping effect.
摘要翻译：一种用于连接涡轮机的涡轮叶片的装置，其具有设置在每个涡轮机叶片的径向外端处并基本上与涡轮叶片的纵向平面成直角延伸的板状构件。板状构件从涡轮叶片的前缘和后缘突出，并且在每个突出部分中设置有通孔。具有圆柱形销或类似突起的连接构件以这样的方式设置在两个相邻的涡轮叶片之间，使得突起可旋转地被相应的通孔接收。也就是说，其中一个连接构件连接到涡轮叶片的前缘的板状构件，而另一个连接构件连接到前一相邻涡轮叶片的后缘的板状构件。连接构件被布置成使得它们部分地位于相邻涡轮叶片的板状构件的下面，并且在涡轮机的运行期间它们彼此接触，从而限制涡轮叶片的解捻，同时获得减振效果。

7. 发明授权

US4566810A Steam turbine rotor shaft 失效
标题翻译：蒸汽轮机转子轴
公开(公告)号：US4566810A
公开(公告)日：1986-01-28
申请号：US484204
申请日：1983-04-12
申请人： Takatoshi Yoshioka , Seishin Kirihara , Masao Shiga , Katsumi Iijima , Katsukuni Hisano , Ryoichi Kaneko
发明人： Takatoshi Yoshioka , Seishin Kirihara , Masao Shiga , Katsumi Iijima , Katsukuni Hisano , Ryoichi Kaneko
IPC分类号： F01D5/06 , F16C3/02 , F16C33/06 , F16C33/04 , F16C33/08 , F16C33/14
CPC分类号： F16C3/02 , F16C33/06 , Y10S384/912
摘要： A steam turbine rotor shaft made of precipitation-hardened forged austenite steel, comprising first, second and succeeding layers of build-up welding provided on an outer surface of a bearing portion of a journal section in the rotor shaft, the first layer being provided by use of a welding rod of Ni base alloy, the second and succeeding layers being provided by use of a welding rod of low alloy steel which layers have better bearing characteristics than those of the austenite steel.
摘要翻译：一种由沉淀硬化的锻造奥氏体钢制成的蒸汽轮机转子轴，包括设置在转子轴上的轴颈部分的轴承部分的外表面上的第一，第二和后续的堆积焊接层，第一层由使用Ni基合金焊条，第二层和后续层通过使用低于奥氏体钢的这些层具有较好的轴承特性的低合金钢焊条提供。

8. 发明授权

US4626174A Turbine blade 失效
标题翻译：涡轮叶片
公开(公告)号：US4626174A
公开(公告)日：1986-12-02
申请号：US721469
申请日：1985-04-09
申请人： Takeshi Sato , Akira Uenishi , Norio Yasugahira , Katsukuni Hisano
发明人： Takeshi Sato , Akira Uenishi , Norio Yasugahira , Katsukuni Hisano
IPC分类号： F01D5/14
CPC分类号： F01D5/141
摘要： A turbine blade of a low blade profile loss with a crossing point of an inlet angle .alpha..sub.1 an outlet angle .alpha..sub.2 being located in a position in which a distance between a crossing point of the outlet end of the blade is greater than one-half of the blade width L.sub.ax, with the inlet angle .alpha..sub.1 being in the range of 35.degree.-40.degree. and the outlet angle .alpha..sub.2 being in the range of 25.degree.-28.degree.. A ratio of a narrowest width S.sub.2 of the flow channel at the blade outlet end to a narrowest width S.sub.1 of a flow channel defined between a backside of the blade in an area of the crossing point and a front side of adjacent blade lies in the range of 0.81-0.96. A ratio of a distance L.sub.ax to a blade width L.sub.ax is in the range of 0.5-0.54, with a ratio of a distance L.sub.m from an outlet end of the blade to the blade width L.sub.ax being in a range of 0.75-0.89. A ratio of a distance from the maximum projecting point to a line connecting to the outlet end of adjacent blades is in a range of 0.6-0.66. By virtue of the blade profile, the flow velocity differential between the fluid flowing along the front side of the blade and the fluid flowing along the backside of the blade can thereby be reduced.
摘要翻译：具有低叶片轮廓损失的涡轮叶片，具有入口角α1的交叉点，出口角α2位于叶片出口端的交叉点之间的距离大于一半的位置叶片宽度Lax，入口角α1在35°-40°的范围内，出口角α2在25°-28°的范围内。在叶片出口端的流道的最窄宽度S2与限定在交叉点的区域中的叶片的背面之间的流动通道的最窄宽度S1与相邻叶片的前侧之间的比率在该范围内为0.81-0.96。距离Lax与叶片宽度Lax的比率在0.5-0.54的范围内，从叶片的出口端到叶片宽度Lax的距离Lm的比率在0.75-0.89的范围内。从最大突出点到连接到相邻叶片的出口端的线的距离的比率在0.6-0.66的范围内。由于叶片轮廓，可以减小沿叶片前侧流动的流体与沿着叶片背面流动的流体之间的流速差。

9. 发明授权

US4766721A Combustor for gas turbine 失效
标题翻译：燃气轮机燃烧器
公开(公告)号：US4766721A
公开(公告)日：1988-08-30
申请号：US917973
申请日：1986-10-14
申请人： Nobuyuki Iizuka , Yoji Ishibashi , Isao Sato , Fumiyuki Hirose , Hiroshi Inose , Katsukuni Hisano , Katsuo Wada , Seiichi Kirikami , Michio Kuroda , Yoshihiro Uchiyama
发明人： Nobuyuki Iizuka , Yoji Ishibashi , Isao Sato , Fumiyuki Hirose , Hiroshi Inose , Katsukuni Hisano , Katsuo Wada , Seiichi Kirikami , Michio Kuroda , Yoshihiro Uchiyama
IPC分类号： F23R3/00 , F02C9/18 , F23R3/04 , F23R3/26 , F23R3/28 , F23R3/34
CPC分类号： F23R3/34 , F02C9/18 , F23R3/26 , F05D2270/31
摘要： A combustor of two-stage combustion type in which fuel is supplied only from primary fuel nozzles for combustion only in primary combustion chamber under the operating condition where gas turbine load is low, and premixed mixture is supplied into a secondary combustion chamber provided on the downstream side of the primary combustion chamber for combustion in both the primary and secondary combustion chambers under the operating condition where the load is high. An air-bleed passageway opens on a downstream side of air holes for intaking secondary combustion air to be mixed with secondary fuel and communicates with the outside of the combustor. The air-bleed passageway is provided with a regulating valve and the secondary combustion air is bled at the minimum point of the load where the secondary fuel is supplied so that the fuel to air ratio of secondary premixed mixture may not be excessively lean, thereby reducing the production of non-burned components.
摘要翻译：一种二级燃烧式的燃烧器，其中，在燃气轮机负荷低的运行条件下，燃料仅从主燃料喷嘴供给燃料，仅在一级燃烧室中燃烧，并且将预混合物供给到设置在下游的二次燃烧室在一次燃烧室中，在负载高的运行条件下在一次燃烧室和二次燃烧室中燃烧。排气通道在气孔的下游侧开口，用于吸入与二次燃料混合的二次燃烧空气并与燃烧器的外部连通。排气通道设置有调节阀，二次燃烧空气在供给二次燃料的负载的最小点处排出，使得二次预混混合物的燃料与空气的比例可能不会过度减少，从而减少生产非烧成分。

10. 发明授权

US4228359A Rotor-stress preestimating turbine control system 失效
标题翻译：转子应力预估涡轮机控制系统
公开(公告)号：US4228359A
公开(公告)日：1980-10-14
申请号：US929130
申请日：1978-07-28
申请人： Hiroshi Matsumoto , Yoshio Sato , Shigeyoshi Kawano , Yoshiyuki Nakano , Fumio Kato , Katsukuni Hisano , Katsuto Kashiwahara , Yasuhiko Otawara , Toshihiko Higashi , Yasuhiro Tennichi , Jube Matsumura , Koichiro Fukushima
发明人： Hiroshi Matsumoto , Yoshio Sato , Shigeyoshi Kawano , Yoshiyuki Nakano , Fumio Kato , Katsukuni Hisano , Katsuto Kashiwahara , Yasuhiko Otawara , Toshihiko Higashi , Yasuhiro Tennichi , Jube Matsumura , Koichiro Fukushima
IPC分类号： F01D19/02 , F01K7/16
CPC分类号： F01K7/165 , F01D19/02
摘要： The present stress in the turbine rotor is estimated at each control period, from the steam temperature and pressure at the turbine inlet. In addition, the future turbine inlet steam temperature or pressure is preestimated once every n.sub.T control cycles, for a given speed or load changing rate, making use of data concerning the changing rate of the turbine steam inlet temperature or pressure in relation with the change of the speed or load, which has been obtained by a learning of the past turbine operating condition. This future steam temperature or pressure at the turbine inlet is used as a factor for preestimating the future stress expected to be caused in the turbine rotor. The preestimation of the rotor stress is performed for a plurality of assumed speed or load changing rates. The turbine is controlled at the maximum speed increase-rate or load changing rate which would not cause the future stress preestimated over a given preestimation time to exceed a limit stress. An observation of the present stress is made at each control period to check whether the limit stress is not exceeded by the present stress.
摘要翻译：根据涡轮机入口处的蒸汽温度和压力，在每个控制周期估计涡轮转子中的当前应力。另外，对于给定的速度或负荷变化率，在每个nT控制循环中预先设想未来的涡轮进口蒸汽温度或压力一次，利用关于涡轮机进气温度或压力变化率的数据与通过学习过去的涡轮机操作条件而获得的速度或负载。涡轮机入口处的未来蒸汽温度或压力被用作预先估计在涡轮转子中引起的未来应力的因素。对于多个假想速度或负载变化率来执行转子应力的预测。涡轮机以最大速度增加速率或负载变化率进行控制，这不会导致在给定预测时间内预测的未来应力超过极限应力。在每个控制周期进行当前应力的观察，以检查当前应力是否超过极限应力。

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