公开(公告)号：US6065282A

公开(公告)日：2000-05-23

申请号：US960466

申请日：1997-10-29

申请人： Ichiro Fukue ,  Eiji Akita ,  Yasuoki Tomita

发明人： Ichiro Fukue ,  Eiji Akita ,  Yasuoki Tomita

IPC分类号： F02C7/18 ,  F02G3/00 ,  F02C5/00

CPC分类号： F02C7/185 ,  F05D2260/205

摘要： A gas turbine comprises: a first closed circuit in which cooling gas is supplied to a casing, allowed to pass through stationary blades, and removed to the outside of casing after cooling the stationary blades; a second closed circuit in which cooling air is supplied to the casing, allowed to pass through moving blades, and removed to the outside of casing after cooling the moving blades; a cooler for cooling the cooling gas in the first and second closed circuits; and a booster for pressurizing and circulating the cooling gas cooled by the cooler.Also, A gas turbine comprises: a first closed circuit in which cooling air cooled after being extracted from a combustor plenum is allowed to pass through stationary blades successively to cool the stationary blades, and then recovered and returned to a compressor on the upstream side of the combustor plenum; and a second closed circuit in which cooling air cooled after being extracted from the combustor plenum is allowed to pass through moving blades successively to cool the moving blades, and then recovered and returned to the compressor.

摘要翻译： 燃气轮机包括：第一闭合回路，其中冷却气体被供给到壳体，允许其通过固定叶片，并且在冷却固定叶片之后被移除到壳体外部; 第二闭合回路，其中冷却空气被供给到壳体，允许通过动叶片，并且在冷却动叶片之后被移除到壳体外部; 用于冷却第一和第二闭合回路中的冷却气体的冷却器; 以及用于对由冷却器冷却的冷却气体进行加压和循环的增压器。 此外，A燃气轮机包括：第一闭合回路，其中在从燃烧室增压室抽出之后冷却的冷却空气被允许依次通过固定叶片以冷却固定叶片，然后回收并返回到压缩机的上游侧 燃烧室增压室; 以及第二闭合回路，其中冷却从冷却室抽出的冷却空气被连续通过运动叶片以冷却动叶片，然后回收并返回压缩机。

公开(公告)号：US5779447A

公开(公告)日：1998-07-14

申请号：US800985

申请日：1997-02-19

申请人： Yasuoki Tomita ,  Lars Thomsen

发明人： Yasuoki Tomita ,  Lars Thomsen

IPC分类号： F01D5/18 ,  F04D29/58

CPC分类号： F01D5/187 ,  F05D2240/81 ,  F05D2260/2214

摘要： A gas turbine rotor, more particularly a gas turbine rotor blade, which is manufactured so as to be longer, larger, and thin walled and is provided on a rear side of a gas turbine blade array. The gas turbine rotor blade is cooled with cooling air flowing interiorly thereof. A cavity is provided to facilitate the flow of cooling air. The cavity is formed inside a rotor root and inside a hub unit disposed adjacent to a rotor profile unit. Projections are provided inside of the cavity so that the projections, which protrude from an inner wall of the cavity, project into the cooling air flow. Consequently, cooling efficiency of the rotor blade can be improved, and the strength of the portions forming the cavity can be significantly increased. The device also allows the core for cooling to be manufactured and easily set.

摘要翻译： 燃气轮机转子，更具体地，燃气轮机转子叶片，其被制造为更长，更大和薄壁，并且设置在燃气轮机叶片阵列的后侧。 燃气轮机转子叶片由其内部流动的冷却空气冷却。 提供空腔以便于冷却空气的流动。 空腔形成在转子根部内部和靠近转子轮廓单元设置的轮毂单元内部。 突出部设置在腔体的内部，使得从空腔的内壁突出的突出部突出到冷却空气流中。 因此，能够提高转子叶片的冷却效率，能够显着提高形成空腔的部分的强度。 该装置还允许芯体制造和容易设置。

公开(公告)号：US07033138B2

公开(公告)日：2006-04-25

申请号：US10235825

申请日：2002-09-06

申请人： Yasuoki Tomita ,  Osamu Isumi ,  Shinichi Inoue ,  Friedrich Soechting ,  Vincent Laurello ,  Hiroshige Matsuoka

发明人： Yasuoki Tomita ,  Osamu Isumi ,  Shinichi Inoue ,  Friedrich Soechting ,  Vincent Laurello ,  Hiroshige Matsuoka

IPC分类号： F01D25/08

CPC分类号： F01D25/12 ,  F01D11/005 ,  F01D11/08 ,  F01D25/246 ,  F05D2240/55 ,  F05D2260/201

摘要： An object of the present invention is to provide a ring segment of a gas turbine in which the temperature is maintained low, damage due to high temperature oxidation is prevented, and high temperature deformation is prevented. In order to achieve the object, the present invention provides a ring segment of a gas turbine which comprises a blade ring, a main shaft and moving blades comprising a plurality of individual units which define an annular form by being arranged around the peripheral direction of the main shaft, and disposed so that its inner peripheral surface is maintained at a constant distance from the tips of the moving blades, wherein grooves which extend along the axial direction of the main shaft of the turbine are formed upon of the individual units so as mutually to confront one another; a seal plate which is inserted into each mutually confronting pair of the grooves so as to connect together the adjacent pair of individual units; and contact surfaces which are formed at positions more radially inward than the seal plates, which extend in the axial direction and the peripheral direction and which mutually contact one another.

摘要翻译： 本发明的目的是提供一种燃气轮机的环段，其中温度保持较低，防止了由于高温氧化引起的损坏，并且防止了高温变形。 为了实现该目的，本发明提供了一种燃气轮机的环形段，其包括叶片环，主轴和包括多个独立单元的活动叶片，所述多个单独的单元通过围绕 主轴，并且配置成使其内周面与动叶片的前端保持恒定的距离，其中沿涡轮主轴的轴向延伸的槽形成在各个单元上，以便相互 相互对抗 密封板，其插入每个相互面对的一对槽中，以将相邻的一对单独的单元连接在一起; 以及形成在比轴向和周向延伸并彼此相互接触的密封板更径向向内的位置处的接触表面。

公开(公告)号：US06983659B2

公开(公告)日：2006-01-10

申请号：US10635494

申请日：2003-08-07

申请人： Friedrich Soechting ,  Charles Ellis ,  Yasuoki Tomita ,  Yugo Tokunaga

发明人： Friedrich Soechting ,  Charles Ellis ,  Yasuoki Tomita ,  Yugo Tokunaga

IPC分类号： G01M15/00

CPC分类号： G01B5/205 ,  F01D21/003 ,  F05D2260/80 ,  F05D2270/11 ,  G01B5/30 ,  G01M13/00

摘要： In order to provide a turbine blade creep life evaluating method for quantitively evaluating the life of a turbine blade, the turbine blade is determined to be within its allowable life if the creep elongation strain in the longitudinal direction of the turbine blade is less than 0.5% of an initial length, and is determined to exceed its allowable life if the creep elongation strain is 0.5% or more than the initial length. A turbine blade creep elongation strain measuring apparatus 20 comprises a first fixed end 21, a second fixed end 22, and a dial gauge 24. A dimension in the longitudinal direction is stamped on the surface of a turbine blade.

摘要翻译： 为了提供用于定量评估涡轮叶片的寿命的涡轮机叶片蠕变寿命评估方法，如果涡轮叶片的纵向方向上的蠕变伸长应变小于0.5％，则涡轮叶片被确定在其允许寿命内 如果蠕变伸长应变为初始长度的0.5％或更大，则确定其超过其允许寿命。 涡轮叶片蠕变伸长应变测量装置20包括第一固定端21，第二固定端22和千分表24。 纵向上的尺寸被压印在涡轮叶片的表面上。

公开(公告)号：US20050186074A1

公开(公告)日：2005-08-25

申请号：US11059644

申请日：2005-02-17

申请人： Yasuoki Tomita ,  Masaki Ono ,  Eiji Akita ,  Masao Terazaki ,  Masayuki Takahama ,  Kouji Watanabe ,  Hideki Murata

发明人： Yasuoki Tomita ,  Masaki Ono ,  Eiji Akita ,  Masao Terazaki ,  Masayuki Takahama ,  Kouji Watanabe ,  Hideki Murata

IPC分类号： F01D5/26 ,  B63H1/14 ,  F01D5/18 ,  F01D5/22 ,  F01D5/30 ,  F01D11/00 ,  F16F15/20

CPC分类号： F01D11/006 ,  F01D5/22 ,  F01D11/008

摘要： In a gas turbine having a plurality of moving blades provided on a rotary shaft in a circumferentially adjoining condition, a seal pin is provided in a spacing between the shanks of the adjacent moving blades for preventing leakage of cooling air from a blade root portion side to an airfoil side; an arcuately depressed portion is formed on the shank of each of the moving blades; and vibration of each of the moving blades is suppressed in such a manner that the seal pin serves as a spring system while the airfoil portion, the platform, the shank, and the blade root portion serve as a mass system.

摘要翻译： 在具有沿周向邻接状态设置在旋转轴上的多个动叶片的燃气轮机中，密封销以相邻的动叶片的柄之间的间隔设置，用于防止冷却空气从叶片根部侧泄漏到 机翼一侧 在每个动叶片的柄部上形成弓形凹陷部分; 并且以这样一种方式抑制每个动叶片的振动，使得当翼型部分，平台，柄部和叶片根部部分用作质量系统时，密封销用作弹簧系统。

公开(公告)号：US06508623B1

公开(公告)日：2003-01-21

申请号：US09959310

申请日：2001-10-22

申请人： Shigehiro Shiozaki ,  Yasuoki Tomita

发明人： Shigehiro Shiozaki ,  Yasuoki Tomita

IPC分类号： F01D1124

CPC分类号： F01D25/12 ,  F01D9/04 ,  F01D11/08 ,  F01D25/246 ,  F05D2260/201

摘要： A gas turbine segmental ring has an increased rigidity to suppress a thermal deformation and enables less cooling air leakage by less number of connecting portions of segment structures. Cooling air (70) from a compressor flows through cooling holes (61) of an impingement plate (60) to enter a cavity (62) and to impinge on a segmental ring (1) for cooling thereof. The cooling air (70) further flows into cooling passages (64) from openings (63) of the cavity (62) for cooling an interior of the segmental ring (1) and is discharged into a gas path from openings of a rear end of the segmental ring (1). Waffle pattern (10) of ribs arranged in a lattice shape is formed on an upper surface of the segmental ring (1) to thereby increase the rigidity. A plurality of slits (6) are formed in flanges (4, 5) extending in the turbine circumferential direction to thereby absorb the deformation and thermal deformation of the segmental ring (1) is suppressed.

摘要翻译： 燃气轮机节段环具有增加的刚性以抑制热变形，并且通过较少数量的节段结构的连接部分能够减少冷却空气泄漏。 来自压缩机的冷却空气（70）流过冲击板（60）的冷却孔（61）进入空腔（62）并撞击节段环（1）以进行冷却。 冷却空气（70）进一步从空腔（62）的开口（63）流入冷却通道（64），用于冷却节段环（1）的内部，并从其后端的开口排出气体通道 节段环（1）。 排列成格子状的肋的楔形花纹（10）形成在节段环（1）的上表面上，从而增加刚性。 多个狭缝（6）形成在沿涡轮机圆周方向延伸的凸缘（4,5）中，从而吸收变形，并且抑制了节段环（1）的热变形。

公开(公告)号：US6086329A

公开(公告)日：2000-07-11

申请号：US38070

申请日：1998-03-11

申请人： Yasuoki Tomita ,  Hiroki Fukuno ,  Eisaku Ito

发明人： Yasuoki Tomita ,  Hiroki Fukuno ,  Eisaku Ito

IPC分类号： F01D5/22 ,  F01D5/02 ,  F01D11/00 ,  F01D11/04 ,  F02C7/28

CPC分类号： F01D11/006

摘要： A seal plate at the platform portion of a gas turbine moving blade. The seal plate is inserted in a gap between the adjacent platforms at each end portion of a seal pin to prevent air from leaking to the outside. A groove is provided at each of four corners of the end portion of platform of the moving blade, and the seal plate is inserted to cover the gap so as to extend the end portions of the adjacent platforms, by which the gap between the platforms is blocked. A seal pin and end seal pins are inserted between the platforms to seal this portion. However, there is a gap at the end portions, so that cooling air leaks from the lower part of platform. Since the seal plate is inserted in the groove to block the gap, the sealing property is increased.

摘要翻译： 在燃气轮机动叶片的平台部分处的密封板。 密封板在密封销的每个端部处插入相邻平台之间的间隙中，以防止空气泄漏到外部。 在活动叶片的平台的端部的四个角部的每一个处设置有凹槽，并且插入密封板以覆盖间隙，以延伸相邻平台的端部，由此平台之间的间隙为 被阻止 密封销和端部密封销插入平台之间以密封该部分。 然而，在端部处存在间隙，使得冷却空气从平台的下部泄漏。 由于密封板插入凹槽以阻挡间隙，所以密封性能增加。

公开(公告)号：US6053701A

公开(公告)日：2000-04-25

申请号：US125882

申请日：1998-08-27

申请人： Taku Ichiryu ,  Yasuoki Tomita

发明人： Taku Ichiryu ,  Yasuoki Tomita

IPC分类号： F01D5/08 ,  F02C7/18 ,  F04D29/58

CPC分类号： F01D5/084 ,  F01D5/085 ,  F05D2260/205 ,  F05D2260/2322

摘要： A cooling steam circulation passage for a gas turbine rotor (30) having turbine discs (41.about.47) are composed of center line bores (73.about.77) open at an axial end of the rotor and extending through a central portion of the rotor; a steam inlet-outlet pipe (79) coaxially disposed therein so as to define an annular passage (81) for cooling steam at an outer side; steam cavities (89a, 89b) defined between and by facing side surfaces of said turbine discs; steam cavities (91a, 91b) each defined at non-facing side surface portions of said turbine discs (41, 43); axial steam holes (61, 63) formed to extend through the turbine discs and including a partition tube (99); and radial steam holes (97, 103a, 103b, 105, 107) extending from each of the steam cavities (91a, 101, 89a) to mounting portions for the rotor blades.

摘要翻译： PCT No.PCT / JP98 / 00243 Sec。 371日期：1998年9月27日第 102（e）日期1998年8月27日PCT 1997年1月22日PCT PCT。 第WO98 / 32953号公报 日期1998年7月30日具有涡轮盘（41差值47）的燃气轮机转子（30）的冷却蒸汽循环通道由在转子的轴向端部开口并延伸穿过中心线的中心线孔（73差） 转子的一部分; 同时设置在其中以形成用于在外侧冷却蒸汽的环形通道（81）的蒸汽入口 - 出口管（79） 限定在所述涡轮盘的相对侧表面之间的蒸汽腔（89a，89b） 每个限定在所述涡轮盘（41,43）的非面对侧表面部分处的蒸汽腔（91a，91b）; 轴向蒸汽孔（61,63）形成为延伸穿过涡轮盘并且包括分隔管（99）; 以及从每个蒸汽腔（91a，101,89a）延伸到用于转子叶片的安装部分的径向蒸汽孔（97,103a，103b，105,107a）。

公开(公告)号：US5846048A

公开(公告)日：1998-12-08

申请号：US862146

申请日：1997-05-22

申请人： Yasuoki Tomita ,  Taku Ichiryu

发明人： Yasuoki Tomita ,  Taku Ichiryu

IPC分类号： F01D5/18 ,  F01D25/12 ,  F04D29/38

CPC分类号： F01D25/12 ,  F01D5/187 ,  F05D2260/205 ,  F05D2260/2322

摘要： Object: Gas turbine blade cooling is generally made by use of air, which has a limitation in enhancement of a thermal efficiency, so steam as a cooling medium is being studied. In a steam cooling method, however, a secure recovery of cooling steam and a secure prevention of leakage is required. The present invention provides a new unit which can satisfy such requirement. Solving means: There are provided a column extending in a radial direction on an outer periphery of a shroud, a supply passage and a recovery passage of a cooling medium within said column and a means for joining a supply tube and a recovery tube of the cooling medium connected to a starting end of said supply passage and a finishing end of said recovery passage, respectively, at a terminal end portion of said column, thereby the cooling medium supplied via the supply tube and the supply passage is recovered securely via the recovery passage and the recovery tube so that no leakage occurs outside, thus an employment of steam etc. as a cooling medium can be realized.

摘要翻译： 对象：燃气轮机叶片冷却通常通过使用空气来制造，这对于提高热效率具有局限性，因此正在研究作为冷却介质的蒸汽。 然而，在蒸汽冷却方法中，需要安全地回收冷却蒸汽并确保防止泄漏。 本发明提供能够满足这种要求的新单元。 解决方案：提供了一个在径向方向上延伸的柱体，该柱体在护罩的外周边，供应通道和所述塔内的冷却介质的回收通道和用于连接供应管和冷却回收管的装置 介质在所述塔的末端部分别连接到所述供应通道的起始端和所述回收通道的末端，由此经由供应管和供给通道供应的冷却介质经由回收通道 和回收管，使得不会在外部发生泄漏，因此可以实现作为冷却介质的蒸汽等的使用。

公开(公告)号：US5785496A

公开(公告)日：1998-07-28

申请号：US803771

申请日：1997-02-24

申请人： Yasuoki Tomita

发明人： Yasuoki Tomita

IPC分类号： F01D5/18 ,  F01D5/20

CPC分类号： F01D5/187 ,  F01D5/225 ,  F05D2240/81

摘要： A gas turbine rotor blade includes a shroud which is cooled effectively with cooling gas used for cooling the blade profile so that the temperature of the shroud is reduced and the life of the gas turbine rotor blade is extended. A two-step groove is engraved in the shroud along the tip of the blade profile and the upper portion of the two-step groove is plugged. Second cooling holes are bored along the direction of the plane of the shroud so as to be connected to and communicate with the first cooling holes which are bored in the blade profile in a direction along the longitudinal axis of the blade for passing cooling gas through the blade. Consequently, most of the cooling gas, after cooling the blade profile, can be used for cooling the shroud, so that the shroud is cooled effectively and the temperature thereof is prevented from rising. Preventing the temperature from rising can also prevent reduction of the creep resistance of the shroud and prevent the blade root on the shroud from being turned up.

摘要翻译： 一种燃气涡轮机转子叶片包括用冷却气体冷却冷却叶片轮廓的罩体，从而使护罩的温度降低，燃气轮机转子叶片的寿命延长。 沿着刀片轮廓的尖端刻在护罩中的两步槽，并且两步槽的上部被堵塞。 第二冷却孔沿着护罩的平面方向钻孔，以便沿着沿着刀片的纵向轴线的方向与在叶片轮廓中钻孔的第一冷却孔连接并连通，以使冷却气体通过 刀。 因此，在冷却叶片轮廓之后，大部分冷却气体可用于冷却护罩，从而有效地冷却护罩并且防止其温度升高。 防止温度升高也可以防止护罩的抗蠕变性降低，并防止护罩上的叶片根部翻倒。