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1. 发明专利

JP2006063837A Gas turbine 有权
标题翻译：燃气轮机
公开(公告)号：JP2006063837A
公开(公告)日：2006-03-09
申请号：JP2004245435
申请日：2004-08-25
申请人： Hitachi Engineering & Services Co Ltd , Hitachi Ltd , 株式会社日立エンジニアリングサービス , 株式会社日立製作所
发明人： ICHIKAWA KUNIHIRO , MOMOZAKI HISATAKA , ENDO TAKAO
IPC分类号： F01D11/08 , F01D5/20 , F01D5/22 , F02C7/28 , F16J15/44
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine capable of improving gas turbine performance by minimizing gaps between turbine moving blade and a stationary body and of preventing fracture of shroud covers. SOLUTION: The gas turbine driving a turbine 3 by combustion gas obtained by burning compressed air together with fuel is provided with the shroud covers 12 out of which the shroud covers 12 adjacent to each other in the blade rotational direction contact with each other to enhance rigidity of the turbine moving blades 6; honeycomb seals 14 provided in shroud blocks 10 so as to oppose to diametrical direction outside of the shroud covers 12; shroud fins 13 which are protruded on diametrical direction outside faces of the shroud covers 12 so as to oppose to the honeycomb seals 14 and are approximately parallel with the blade rotational direction; and cut parts 15 defined by projecting parts 16 projecting outwardly from rotation loci R of contours of linear parts of the shroud fins 13 and weight adjustment parts 17 inclined so as to enter into inside of the rotation loci R toward the blade rotational direction forward side. COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供一种能够通过使涡轮机动叶片与固定体之间的间隙最小化并防止护罩盖的断裂来提高燃气轮机性能的燃气轮机。解决方案：通过燃烧压缩空气与燃料一起燃烧得到的燃烧气体来驱动涡轮机3的燃气轮机设置有护罩罩12，其中叶片旋转方向上彼此相邻的护罩罩12彼此接触以提高涡轮机动叶片6的刚性; 蜂窝密封件14设置在护罩块10中，以便与护罩罩12外侧的直径方向相反; 护罩翅片13，其在护罩罩12的径向外侧突出，以与蜂窝状密封件14相对，并且与刀片旋转方向大致平行; 以及从罩体翅片13的直线部分和重量调节部分17的轮廓线的旋转轨迹R向外突出的突出部分16所限定的切割部分15，其倾斜以朝向叶片旋转方向前侧进入旋转轨迹R的内部。版权所有（C）2006，JPO＆NCIPI

2. 发明专利

JP2004150700A Gas turbine facility 有权
标题翻译：气体涡轮机设施
公开(公告)号：JP2004150700A
公开(公告)日：2004-05-27
申请号：JP2002315926
申请日：2002-10-30
申请人： Hitachi Engineering & Services Co Ltd , Hitachi Ltd , 株式会社日立エンジニアリングサービス , 株式会社日立製作所
发明人： ENDO TAKAO , ICHIKAWA KUNIHIRO , MOMOZAKI HISATAKA
IPC分类号： F23R3/42
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine facility capable of preventing early wear of a seal member by easily repairing change of a gap between a combustion gas outlet of a transition piece and a combustion gas inlet of a turbine part.
SOLUTION: The gas turbine facility 1 is composed so that the gaps K and L are provided in an opposing part of the combustion gas outlet 13 of the transition piece 5B and the combustion gas inlet 14 of the turbine part 2, and the gaps K and L are sealed by the seal members 21 and 22. A displacement adjusting means 28 is provided for adjusting displacements of the gaps between the transition piece 5 and the turbine part 2.
COPYRIGHT: (C)2004,JPO
摘要翻译：解决的问题：提供一种能够通过容易地修复过渡件的燃烧气体出口与涡轮机部件的燃烧气体入口之间的间隙的变化来防止密封构件的早期磨损的燃气轮机设备。解决方案：燃气轮机设备1被构成为使得间隙K和L设置在过渡件5B的燃烧气体出口13和涡轮部分2的燃烧气体入口14的相对部分中，并且间隙K和L被密封构件21和22密封。设置位移调节装置28，用于调节过渡件5和涡轮部分2之间的间隙的位移。版权所有（C）2004，JPO

3. 发明专利

JP2011163184A Outlet blade cascade of gas turbine compressor 审中-公开
标题翻译：气体涡轮压缩机出口叶片
公开(公告)号：JP2011163184A
公开(公告)日：2011-08-25
申请号：JP2010025741
申请日：2010-02-08
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ENDO TAKAO , ICHIKAWA KUNIHIRO , MOMOZAKI HISATAKA , AKUTSU HIROYUKI
IPC分类号： F04D29/52
摘要： PROBLEM TO BE SOLVED: To provide an outlet blade cascade of a gas turbine compressor capable of suppressing the wear of a fitting portion of a stator blade cascade in the compressor.
SOLUTION: The outlet blade cascade 3 of the gas turbine compressor 57 includes an outer ring 5 inserted in a turbine circumferential direction and fitted in the inner peripheral part of a turbine casing 1, an inner ring 7 inserted in the turbine circumferential direction and fitted in a recessed groove 11 of an inner barrel 4 enclosing a turbine rotating shaft, a plurality of stator blades 6 connected at a tip side to the outer ring 5 and at a root side to the inner ring 7, and a spacer 14 provided between the turbine casing 1 and the outer ring 5 and formed of a material higher in the coefficient of thermal expansion than the outer ring 5.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供能够抑制压缩机中定子叶片级联的装配部分的磨损的燃气轮机压缩机的出口叶片级联。解决方案：燃气轮机压缩机57的出口叶片级联3包括以涡轮机圆周方向插入并装配在涡轮机壳体1的内周部分中的外环5，插入涡轮机圆周方向的内环7 并且装配在封装有涡轮机转轴的内筒4的凹槽11中，多个定子叶片6在前端侧连接到外圈5并且在根部侧连接到内圈7，并且设置有间隔件14 在涡轮壳体1和外环5之间并且由比外环5更高的热膨胀系数的材料形成。版权所有（C）2011，JPO＆INPIT

4. 发明专利

JPS60173302A MOVING BLADE IMPLANTING EQUIPMENT FOR GAS TURBINE 失效
公开(公告)号：JPS60173302A
公开(公告)日：1985-09-06
申请号：JP2855384
申请日：1984-02-20
申请人： HITACHI LTD , HITACHI SERVICE ENG
发明人： MOMOZAKI HISATAKA , HIROSE FUMIYUKI
IPC分类号： F01D5/22 , F01D5/30
摘要： PURPOSE:To enable turbine buckets to be pulled out or implanted one by one by fabricating dovetail grooves for both a turbine bucket and a turbine wheel 12 in such a manner that the grooves form a circular arc whose center coincides with the center of a tip shroud. CONSTITUTION:Dovetail grooves 10 for both a turbine bucket 8 and a turbine wheel 12 are machined in a circular arc so that they form a part of a circle with radius 24 and whose center is the intersection 23 between the middle line 22 of the plate thickness in the radial direction 15 of a tip shroud 16 located at the tip of a bucket 8 and the middle line 21 in the axial direction 11 of the tip shroud 16. With this contrivance, the buckets 8 can be pulled out from or implanted to the wheel 12 one by one without causing interference among the tip shrouds 16.

5. 发明专利

JPS62106224A SUPPORT DEVICE FOR GAS TURBINE COMBUSTOR 失效
公开(公告)号：JPS62106224A
公开(公告)日：1987-05-16
申请号：JP24617685
申请日：1985-11-05
申请人： HITACHI LTD , HITACHI SERVICE ENG
发明人： MOMOZAKI HISATAKA , KOZUKA YOSHIO , NIHEI MINORU
IPC分类号： F23R3/60
摘要： PURPOSE:To make small the torsional vibration acting on a transition piece and reduce the wear on a side seal by increasing the number of rear side support points of the transition piece and providing the support position on both side faces of the transition piece. CONSTITUTION:On the rear side face of a transition piece 4 a base 14 of the subject device is welded. A bracket 19 for mounting a transition piece 4 to a gas turbine casing is formed in a plate form, and the base 18 and the bracket 19 are connected by a pin 20. The device is mounted at two places so that the device is symmetrical with respect to both side faces. With this arrangement torsional vibration of the transition piece 4 generated around the support device becomes small. As a result, the up-and-down vibration 16 of the transition piece 4 in the vicinity of a side seal 17 also becomes small and reduces the wear on the side seal 17. Further, air 2 of relatively low temperature from a compressor directly hits the surface of the transition piece 4 round the support base 18, where a largest stress develops and lowers the metal temperature, restraining drop in the tensile strength.

6. 发明专利

JPH11257016A GAS TURBINE 失效
公开(公告)号：JPH11257016A
公开(公告)日：1999-09-21
申请号：JP6250698
申请日：1998-03-13
申请人： HITACHI LTD
发明人： ICHIKAWA KUNIHIRO , SATO ISAO , HIROSE FUMIYUKI , MOMOZAKI HISATAKA
IPC分类号： F01D11/08
摘要： PROBLEM TO BE SOLVED: To prevent the generation of crack due to thermal fatigue by disposing a support rail for supporting a shroud which is located on the outer periphery of the shroud and in circumferential direction of the shroud, connecting both ends of the rail at the inner periphery side surface of the rail, and providing a slit for forming a circumferential clearance in the inner periphery side surface. SOLUTION: A turbine portion of a gas turbine is provided with a turbine casing 1. A plurality of shroud blocks which form an outer periphery wall of a passage for high temperature high pressure gas are provided along an entire circumference. The shroud blocks are fittingly fixed to shroud rails 3 provided in circuferential direction of the inner periphery side of the casing 1. In this case a slit 5 is provided on the inner periphery side of the shroud rail 3 for forming a clearance which connects both ends of the shroud rail 3. This relieves the restraint on heat deformation in circumferential direction, and reduces the thermal stress generated in the circumferential direction of the shroud rail upon activation and stop. Accordingly, the generation of cracks due to thermal fatigue is prevented.

7. 发明专利

JPS61173024A GAS TURBINE COMBUSTOR 失效
公开(公告)号：JPS61173024A
公开(公告)日：1986-08-04
申请号：JP1269385
申请日：1985-01-28
申请人： HITACHI LTD , HITACHI SERVICE ENG
发明人： MOMOZAKI HISATAKA , SAKUTA OSAMU
IPC分类号： F23R3/60
摘要： PURPOSE:To improve durability and reliability of a combustor by installing a circumferential groove, into which a front end of a flat spring is allowed to enter to prevent erosion and cutting of the plate spring. CONSTITUTION:A gap g1 is kept between an inner cylinder 4 of a combustor and a transition piece 3. A plate spring 13 is assembled in a state with some initial load and is placed at the outerside of a groove 22 made on the inner cylinder 4 of the combustor. When the combustion gas flows in the inner cylinder of the combustor, the size of the gap becomes small as g2 due to the expansion of the cylinder by heat and then the plate spring 13 is compressed radically but a fulcrum moves in the direction of the arrow 23 as the spring is fixed at the rear end 11 of the inner cylinder 4 and the fulcrum drops into the circumferential groove 22. As a result, the fulcrum 21 of the plate spring 13 escapes from the direction of compressive load and the compressive load on the plate spring 13 becomes small.

8. 发明专利

JPS62267598A ROTOR BLADE FOR GAS TURBINE COMPRESSOR 失效
公开(公告)号：JPS62267598A
公开(公告)日：1987-11-20
申请号：JP11077986
申请日：1986-05-16
申请人： HITACHI LTD , HITACHI SERVICE ENG
发明人： MOMOZAKI HISATAKA , IKAI YUTAKA
IPC分类号： F01D5/30 , F04D29/34
摘要： PURPOSE:To shorten the replacing work of rotor blade considerably by supporting the rotor blade dove tail section at each stage while holding between a front and rear wheels. CONSTITUTION:A projecting wheel dove tail 10 fittable to a recess in a rotor blade dove tail 3 is provided on the entire circumference in the front and rear faces at a rim section 4 of a wheel 1. A notch 13 for inserting a rotor blade dove tail 3 is made at a portion on the entire circumference of the wheel dove tail 10. The wheel rim section 4 simply holds the rotor blade dove tail 3. Consequently, a broken rotor blade can be replaced easily by simply removing the locking bolts thereby the rotor blade replacing work can be shortened.

9. 发明专利

JPS6030431A SEAL FOR GAS TURBINE COMBUSTOR 失效
公开(公告)号：JPS6030431A
公开(公告)日：1985-02-16
申请号：JP13773683
申请日：1983-07-29
申请人： HITACHI LTD , HITACHI SERVICE ENG
发明人： MOMOZAKI HISATAKA , HIROSE FUMIYUKI , NIHEI MINORU
IPC分类号： F02C7/28 , F01D9/02 , F23R3/60
摘要： PURPOSE:To reduce a crack and wearing generated in a seal, by dividing the seal, provided between a transition piece and a turbine inlet nozzle of a combustor, in a peripheral direction. CONSTITUTION:A seal, provided between a transition piece 4 and a turbine inlet nozzle connected to this piece in a combustor, is divided into seals 20, 21 in a peripheral direction, and the divided parts are formed in construction overlapped with each other. In this way, the seals 20, 21 never generate strong force of contact because their length is decreased as a single seal even if the turbine inlet nozzle is elongated in a radial direction. Accordingly, a crack and wearing generated in the seals 20, 21 can be reduced.

10. 发明专利

JPS58200024A Supporting device of combustor of gas turbine 失效
标题翻译：支持燃气轮机的装置
公开(公告)号：JPS58200024A
公开(公告)日：1983-11-21
申请号：JP8139382
申请日：1982-05-17
申请人： Hitachi Ltd , Hitachi Service Eng Co Ltd
发明人： MOMOZAKI HISATAKA , HIROSE FUMIYUKI , IIZUKA NOBUYUKI
IPC分类号： F02C7/20 , F23R3/60
CPC分类号： F23R3/60
摘要： PURPOSE:To contrive an improvement of reliability of a gas turbine by extending life of a transition piece, by a method wherein a combustor is made to be supported by installing a bracket provided with a plurality of slits on a transition piece part of a burner of the gas turbine. CONSTITUTION:The combustor of a gas turbine is connected by a transition piece 3a with a nozzle of a gas turbine inlet. A support 25 is formed by welding a bracket 23 and providing a plurality of slits 24 on the external surface of the transition piece body 3a. Holes 26 for alleviation in concentration of stress are provided on ends of the slits 24. Three way 27, 28 and 29 thermal extensions can be absorbed through bending of supports 25, 25a and 25b of the bracket 23 and shearing force acting upon a welded part 30 can be alleviated. The life of the transition piece is improved and an improvement of reliability on the gas turbine is realized.
摘要翻译：目的：为了通过延长过渡件的寿命来改进燃气轮机的可靠性，通过一种方法，其中通过将设置有多个狭缝的托架安装在燃烧器的过渡件部分上来进行支撑，燃气轮机。构成：燃气轮机的燃烧器通过过渡片3a与燃气轮机入口的喷嘴连接。通过焊接支架23并在过渡件体3a的外表面上设置多个狭缝24来形成支撑件25。在狭缝24的端部设置有用于缓解应力集中的孔26.三通27,28和29的热延伸部可以通过支架23的支撑件25,25a和25b的弯曲而被吸收，并且作用在焊接部分上的剪切力 30可以缓解。改善了过渡件的使用寿命，实现了燃气轮机的可靠性提高。

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