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1. 发明授权

US06092991A Gas turbine blade 失效
标题翻译：燃气轮机叶片
公开(公告)号：US06092991A
公开(公告)日：2000-07-25
申请号：US35500
申请日：1998-03-05
申请人： Yasuoki Tomita , Taku Ichiryu , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Taku Ichiryu , Kiyoshi Suenaga
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/2212
摘要： A gas turbine blade having a platform and a turbine wheel plate, in which cooling passages are arranged in a plurality of rows and connected to one another in a blade trunk section of a moving blade and a supply-side passage and a discharge-side passage are formed in a blade root section. The gas turbine blade comprises a pocket having an inlet and an outlet formed in the blade root section. The supply-side passage is connected to one of the cooling passages and the inlet of the pocket, the outlet of the pocket is connected to another of the cooling passages, and the discharge-side passage is connected to one of the cooling passages other than the ones connected individually to the supply-side passage and the pocket.
摘要翻译：一种具有平台和涡轮机叶轮板的燃气轮机叶片，其中，冷却通道以多行排列并且在动叶片的叶片主干部分和供给侧通道和排出侧通道中彼此连接形成在叶片根部中。燃气轮机叶片包括具有形成在叶片根部中的入口和出口的袋。供给侧通路连接到一个冷却通道和袋的入口，口袋的出口连接到另一个冷却通道，排出侧通道连接到除了它们分别连接到供应侧通道和口袋。

2. 发明授权

US6089827A Rotor for gas turbines 有权
标题翻译：燃气轮机转子
公开(公告)号：US6089827A
公开(公告)日：2000-07-18
申请号：US242108
申请日：1999-02-09
申请人： Taku Ichiryu , Koichi Akagi , Yasuoki Tomita
发明人： Taku Ichiryu , Koichi Akagi , Yasuoki Tomita
IPC分类号： F01D5/06 , F01D5/08 , F01D11/00 , B63H1/00
CPC分类号： F01D5/066 , F01D11/005 , F01D5/084
摘要： A gas turbine rotor, in which a plurality of discs having teeth of a bevel gear are juxtaposed to engage the teeth and are integrally fastened by a bolt extending through the discs, so that the discs may be cooled by feeding cooling air to the air passages of the individual discs sequentially at the running time, is provided whereby the cooling air is prevented from leaking by means having no wear. Radially outward of an air passage through hole of the faces of the adjoining discs, there are provided arms which are made lower than the dedendums of the teeth and protruded in an annular shape to confront each other; one of the arms has a tip made to have an elastically deformable thickness and a sectional shape bent inward or outward, whereas there is welded to the other arm an extension which has a tip made to have an elastically deformable thickness and a sectional shape bent inward or outward; and the end face of the tip of the one arm and the end face of the tip of the extension of the other arm are held in abutment against each other so that the two end faces may be forced, when the discs are integrated, into contact with each other to prevent leakage of cooling air.
摘要翻译： PCT No.PCT / JP98 / 02564 Sec。 371日期1999年2月9日 102（e）1999年2月9日PCT PCT 1996年6月10日PCT公布。第WO98 / 57040号公报日期1998年12月17日一种燃气轮机转子，其中具有锥齿轮齿的多个盘并列配合以接合齿，并且通过延伸穿过盘的螺栓一体地紧固，使得盘可以通过进给冷却来冷却提供了在运行时间顺序地对各个盘的空气通道的空气，由此通过没有磨损的装置防止冷却空气泄漏。设置在相邻盘的表面的空气通道通孔的径向外侧，设置有比齿的齿根低的突出的环状并相互对置的臂。其中一个臂具有制成具有可弹性变形的厚度和向内或向外弯曲的截面形状的尖端，而焊接到另一个臂的延伸部，该延伸部具有制成具有可弹性变形的厚度和向内弯曲的截面形状或向外; 并且一个臂的末端的端面和另一个臂的延伸部的末端的端面保持彼此抵靠，使得当盘被一体化时两个端面可能被强制接触相互防止冷却空气泄漏。

3. 发明授权

US5980202A Gas turbine stationary blade 失效
标题翻译：燃气轮机固定叶片
公开(公告)号：US5980202A
公开(公告)日：1999-11-09
申请号：US35587
申请日：1998-03-05
申请人： Yasuoki Tomita , Kiyoshi Suenaga , Taku Ichiryu
发明人： Yasuoki Tomita , Kiyoshi Suenaga , Taku Ichiryu
IPC分类号： F01D5/18 , F01D9/06 , F01D11/02 , F01D11/04
CPC分类号： F01D11/04 , F01D11/02 , F01D5/187 , F01D9/065 , F05D2240/81
摘要： A gas turbine stationary blade having a cooling medium passage and outer and inner shrouds in a blade section, comprising a hollow portion in the blade section, the hollow portion including a plurality of chambers divided in the chord direction, the cooling medium passage being formed by connecting the divided chambers in series, one of the chambers located in the center with respect to the chord direction being formed as a sealing air passage in order to allow a cooling medium to flow from the outside of the outer shroud to the bore of the inner shroud.
摘要翻译：一种燃气轮机固定叶片，其具有冷却介质通道和叶片部分中的外护罩和外护罩，包括叶片部分中的中空部分，所述中空部分包括沿弦弦方向分开的多个室，所述冷却介质通道由连接分开的室，其中一个相对于弦方向位于中心的腔室形成为密封空气通道，以便使冷却介质从外护罩的外部流动到内罩的孔裹尸布。

4. 发明授权

US6053701A Gas turbine rotor for steam cooling 有权
标题翻译：用于蒸汽冷却的燃气轮机转子
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）。

5. 发明授权

US5915923A Gas turbine moving blade 失效
标题翻译：燃气轮机动叶片
公开(公告)号：US5915923A
公开(公告)日：1999-06-29
申请号：US861753
申请日：1997-05-22
申请人： Yasuoki Tomita , Taku Ichiryu , Kiyoshi Suenaga
发明人： Yasuoki Tomita , Taku Ichiryu , Kiyoshi Suenaga
IPC分类号： F01D5/18 , F16D5/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/205 , F05D2260/2322
摘要： A gas turbine moving blade in which the moving blade operating in a high temperature operating gas is cooled from its interior by steam and the steam after being used for the cooling is recovered, by use of a simple structure. A supply side passage (10), through which steam (6) is supplied directly into a cooling passage (51) of a blade leading edge side (11), is provided within a blade root portion (2) and a pocket (19). One end of the pocket is connected to the supply side passage and the other end of which is connected to a cooling passage (52) of a blade trailing edge side (12). The pocket is covered with a plate, which extends in a blade chord direction on an outer peripheral side face of the blade root portion between a blade platform and a rotor plate. Thus, efficiency of the gas turbine can be effectively enhanced.
摘要翻译：一种燃气轮机动叶片，其中在高温操作气体中操作的移动叶片由其内部由蒸汽冷却，并且在用于冷却之后蒸汽被回收，通过使用简单的结构。供给侧通道（10）设置在叶片根部（2）和袋（19）内，蒸汽（6）直接供给到叶片前缘侧（11）的冷却通道（51）。袋的一端连接到供给侧通道，另一端连接到叶片后缘侧（12）的冷却通道（52）。该口袋被覆盖有板，其在刀片平台和转子板之间的叶片根部的外周侧面上以叶片弦方向延伸。因此，能够有效地提高燃气轮机的效率。

6. 发明授权

US5846048A Gas turbine stationary blade unit 失效
标题翻译：燃气轮机固定叶片单元
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。

7. 发明授权

US06761529B2 Cooling structure of stationary blade, and gas turbine 有权
公开(公告)号：US06761529B2
公开(公告)日：2004-07-13
申请号：US10202654
申请日：2002-07-25
申请人： Friedrich Soechting , Satoshi Hada , Masamitsu Kuwabara , Junichiro Masada , Yasuoki Tomita
发明人： Friedrich Soechting , Satoshi Hada , Masamitsu Kuwabara , Junichiro Masada , Yasuoki Tomita
IPC分类号： F01D906
CPC分类号： F01D5/187 , F01D9/041 , F05D2240/81 , F05D2260/201
摘要： A collision plate having plural small holes is provided at an interval from a bottom surface of an inner shroud to form a chamber and guides cooling air from the small holes into the chamber. A leading edge flow path is provided at a leading edge side along a width direction and introduces the cooling air. A side flow path is provided along both sides of the inner shroud and guides the cooling air to a trailing edge side. A header is formed along the width direction near the trailing edge and guides the cooling air from the side flow path. Plural trailing edge flow paths are formed at the trailing edge side at intervals along a width direction, in which one end of each flow path is connected to the header and the other end is open at the trailing edge, and the cooling air in the header is ejected from the trailing edge.

8. 发明授权

US06602048B2 Gas turbine split ring 有权
公开(公告)号：US06602048B2
公开(公告)日：2003-08-05
申请号：US09998201
申请日：2001-12-03
申请人： Tatsuaki Fujikawa , Yasuoki Tomita , Shunsuke Torii , Ryotaro Magoshi , Masamitsu Kuwabara , Shinichi Inoue
发明人： Tatsuaki Fujikawa , Yasuoki Tomita , Shunsuke Torii , Ryotaro Magoshi , Masamitsu Kuwabara , Shinichi Inoue
IPC分类号： F01D1124
CPC分类号： F01D11/08 , F01D9/00 , F01D11/18 , F05D2250/181 , F05D2250/282 , F05D2260/201 , F05D2260/30
摘要： In the gas turbine split ring, on an outer peripheral surface 1b between two cabin attachment flanges, a circumferential rib which extends in the circumferential direction and an axial rib which extends in the axial direction and has a height taller than that of the circumferential rib are, respectively, formed in plural lines, so that it is possible to suppress heat deformation in the axial direction which largely contributes to reduction of the tip clearance compared to head deformation in the circumferential direction more efficiently.

9. 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。

10. 发明授权

US6146098A Tip shroud for cooled blade of gas turbine 有权
标题翻译：燃气轮机冷却叶片的顶盖
公开(公告)号：US6146098A
公开(公告)日：2000-11-14
申请号：US242678
申请日：1999-02-22
申请人： Hiroki Fukuno , Yasuoki Tomita , Eisaku Ito
发明人： Hiroki Fukuno , Yasuoki Tomita , Eisaku Ito
IPC分类号： F01D5/08 , F01D5/18 , F01D5/20 , F01D5/22 , F01D11/10 , F02C7/18 , B63H1/14
CPC分类号： F01D11/10 , F01D5/18 , F01D5/187 , F01D5/225 , F05B2240/33 , F05D2240/81
摘要： A tip shroud for a moving blade that is made thin and light for use at a gas turbine downstream stage. Cooling air holes (13 to 16) having a slot shape, are formed in a tip shroud (11) of the moving blade (10). The cooling holes are opened in two side faces of the tip shroud to release the cooling air from the inside of the moving blade (10). In the upper face of the tip shroud 11, there are formed cooling air holes 20, which communicate with the higher pressure side in a combustion gas flow direction R to release the cooling air so that the cooling air flows from the higher pressure side to the lower pressure side so as to cool a high stress portion Y. A high stress portion X is likewise cooled with the cooling air coming from an adjoining moving blade. The slot shapes of the cooling air holes (13 to 16) allow the cooling air to flow widely, thereby cooling the face of the tip shroud (11), and the cooling air holes 20 cool the high stress portions X and Y effectively.
摘要翻译： PCT No.PCT / JP98 / 02689 Sec。一九九九年二月二十二日 102（e）1999年2月22日PCT PCT 1998年6月18日PCT公布。公开号WO98 / 59157 日期1998年12月30日用于在燃气轮机下游阶段使用的薄而轻的移动叶片的尖端罩。具有狭槽形状的冷却气孔（13至16）形成在活动叶片（10）的尖端罩（11）中。冷却孔在尖端护罩的两个侧面上打开，以从动叶片（10）的内部释放冷却空气。在顶部护罩11的上表面形成有冷却空气孔20，其在燃烧气体流动方向R上与高压侧连通以释放冷却空气，使得冷却空气从高压侧流向低压侧，以冷却高应力部分Y.同样，高应力部分X同样地冷却来自邻接的活动叶片的冷却空气。冷却空气孔（13〜16）的槽形状允许冷却空气大量流动，从而冷却尖端罩（11）的表面，并且冷却空气孔20有效地冷却高应力部分X和Y.

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