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1. 发明专利

JP2002364302A RADIAL TURBINE 失效
公开(公告)号：JP2002364302A
公开(公告)日：2002-12-18
申请号：JP2001168124
申请日：2001-06-04
申请人： KAWASAKI HEAVY IND LTD
发明人： KINOUCHI SOSUKE , TAKEHARA TAKESHI
IPC分类号： F01D5/14
摘要： PROBLEM TO BE SOLVED: To provide a radial turbine with high turbine efficiency, hardly producing chipping. SOLUTION: A front end face 25 including a leading edge 24 of a turbine blade is smoothly curved on the blade section along the direction of flow of a high temperature gas G flowing in rows of turbine blades 22. It is preferable that the part from the front end face 25 to the frond end part 28a of the upper edge of the turbine blade 22 is formed as a smooth curved part viewed from the direction P orthogonally crossing the blade face 22a. Moreover, it is preferable that the part from the front end face 25 to the front end part 27a of the lower edge of the turbine blade 22 is formed as a smooth curved part viewed from the direction P orthogonally crossing the blade face 22a.

2. 发明专利

JP2002242695A GAS TURBINE ENGINE PROVIDED WITH FOREIGN MATERIAL REMOVING STRUCTURE 失效
公开(公告)号：JP2002242695A
公开(公告)日：2002-08-28
申请号：JP2001042888
申请日：2001-02-20
申请人： KAWASAKI HEAVY IND LTD
发明人： TAKEHARA TAKESHI , TATSUMI TETSUO
IPC分类号： F01D25/00 , F02C7/00
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine engine capable of having a structure downsized and inexpensive for removing foreign material entering into the engine or produced in the engine, by utilizing existing parts in the engine. SOLUTION: A turbine 7 in the gas turbine engine has turbine rotors 2, 3 in plural stages. Turbine shrouds 17, 18 forming an outer peripheral wall of a gas passage 14 between adjacent turbine rotors 2, 3 are provided with a collecting port 19 for making the foreign material E enter into the collecting port 19 and introducing the foreign material E outside the gas passage 14.

3. 发明专利

JP2002021581A GAS TURBINE DEVICE EQUIPPED WITH HEAT EXCHANGER 失效
公开(公告)号：JP2002021581A
公开(公告)日：2002-01-23
申请号：JP2000206644
申请日：2000-07-07
申请人： KAWASAKI HEAVY IND LTD
发明人： TAKEHARA TAKESHI
IPC分类号： F02C7/08 , F02C3/05 , F23L15/04 , F23R3/02 , F23R3/50 , F28D9/00
摘要： PROBLEM TO BE SOLVED: To compact the whole construction of a gas turbine device and reduce the cost by eliminating necessity for pipings tying the gas turbine to a heat- exchanger. SOLUTION: A heat-exchanger 3 to make heat exchange between a compressed air A discharged from a compressor 4 and the exhaust gas E emitted from turbine 6 is coupled with the exhaust gas outlet side at the back of the gas turbine 1. Inside a casing 18, the heat-exchanger 3 is equipped with a core 19 having a plurality of heat conducting plates 23 to partition a first passage 21 for compressed air A from a second passage 22 for exhaust gas E. A first inlet 24 for compressed air A is provided in the rear side face of the core 19 while an outlet 25 for compressed air A is provided in the front side face of the core 19. An introducing passage 26 to introduce the compressed air A into the first inlet 24 is formed between the core 19 and casing 18. The exhaust gas E having flowed from the front face of the core 19 into the second passage 22 is exhausted from the rear face of the core 19.

4. 发明专利

JPH0886202A INSTALLATION STRUCTURE OF CERAMIC BLADE 失效
公开(公告)号：JPH0886202A
公开(公告)日：1996-04-02
申请号：JP24730994
申请日：1994-09-14
申请人： KAWASAKI HEAVY IND LTD
发明人： TAKEHARA TAKESHI , TATSUMI TETSUO
IPC分类号： F01D5/30 , F02C7/18
摘要： PURPOSE: To realize the installation structure of a ceramic blade by which the ceramic blade exposed to high temperature gas can be stably attached to the peripheral part of a turbine disc having a comparatively large diameter without providing any mounting hole, and having excellent rotary balance and also including a small number of parts. CONSTITUTION: A ceramic blade 15 is fitted in and attached to the engagement grooves 12 of the outer circumferential part 11a of a metallic turbine disc 11 on its engagement projecting part 18. A contact part 13 brought in contact with one end of the platform part 17 of the turbine blade 15 fitted to and inserted in the engagement grooves 12 of the disc outer circumferential part 11a from the other disc end surface side, is provided on one disc end surface side of one side circumferential surface 11b between respective engagement grooves 12 of the disc 11. And, an engaging locking groove 14 to retain a presser ring 20 brought in contact with and presses the engagement protruding part 18 of the turbine blade 15 engaged with the engagement grooves 12, on the other side disc end surface, is formed on the other disc end surface of the disc outer circumferential part 11a.

5. 发明专利

JP2006125234A Integrated support structure for turbine nozzle 审中-公开
标题翻译：涡轮喷嘴综合支撑结构
公开(公告)号：JP2006125234A
公开(公告)日：2006-05-18
申请号：JP2004311986
申请日：2004-10-27
申请人： Kawasaki Heavy Ind Ltd , 川崎重工業株式会社
发明人： ICHIKAWA YOSHIHIRO , TAKEHARA TAKESHI
IPC分类号： F01D9/02 , F01D9/04 , F01D25/00 , F02C7/00
摘要： PROBLEM TO BE SOLVED: To provide a support structure stably supporting a turbine nozzle with sufficient retention force by a small spring body which can be stored in a narrow space. SOLUTION: This structure is provided with an outside flange 20 formed on the turbine nozzle 7 and projecting outward in a radial direction R, an inside flange 19 formed on the turbine nozzle 7 and projecting inward in the radial direction R, a duct support 28 supporting a transfer duct 26 leading combustion gas G from a combustor 2 to the turbine nozzle 7 on a housing 27, and a support mechanism 41 supporting attachment flanges 26c, 26d provided on a rear end of the transfer duct 26, the outside flange 20 and the inside flange 19 on the housing 27 under a condition where the same are abutted by spring force. The turbine nozzle 7 and the transfer duct 26 are integrally supported. COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供一种通过可以存储在狭窄空间中的小弹簧体来以足够的保持力稳定地支撑涡轮喷嘴的支撑结构。解决方案：该结构设置有形成在涡轮喷嘴7上并且沿径向R向外突出的外凸缘20，形成在涡轮喷嘴7上并沿径向R向内突出的内凸缘19，支撑件28支撑将燃烧气体G从燃烧器2引导到壳体27上的涡轮喷嘴7的传送管道26，以及支撑机构41，其支撑设置在传送管道26的后端上的附接凸缘26c，26d， 20和位于壳体27上的内侧凸缘19在与弹簧力抵接的状态下。涡轮喷嘴7和输送管道26一体地支撑。版权所有（C）2006，JPO＆NCIPI

6. 发明专利

JP2002242699A GAS TURBINE ENGINE PROVIDED WITH FOREIGN MATERIAL REMOVING STRUCTURE 失效
公开(公告)号：JP2002242699A
公开(公告)日：2002-08-28
申请号：JP2001042887
申请日：2001-02-20
申请人： KAWASAKI HEAVY IND LTD
发明人： TAKEHARA TAKESHI , TATSUMI TETSUO
IPC分类号： F02C7/052 , B01D45/16 , F04D29/70
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine engine capable of having a structure downsized and inexpensive for removing foreign material by utilizing existing parts in the engine. SOLUTION: A collecting port 17 for making enter a foreign material E in the air A into the port 17 and introducing and discharging the foreign material E outside a curved passage 14 is formed on a diametrical outer peripheral portion of the curved passage 14 connected to a downstream side of a centrifugal compressor 1. A collecting port 39 is formed in a boundary portion between a top wall 37 and a peripheral wall 38 in an outer cylinder 11 of a combustion room C of a combustor 4. A collecting port 61 is formed on a compressor shroud 51 of an axial compressor 44.

7. 发明专利

JP2002022372A HEAT EXCHANGER AND TURBINE APPARATUS USING SAME 失效
公开(公告)号：JP2002022372A
公开(公告)日：2002-01-23
申请号：JP2000206645
申请日：2000-07-07
申请人： KAWASAKI HEAVY IND LTD
发明人： TAKEHARA TAKESHI
IPC分类号： F02C7/08 , F28D9/00 , F28F3/08
摘要： PROBLEM TO BE SOLVED: To provide a small-sized heat exchanger with high heat exchange efficiency, and gas turbine using the same. SOLUTION: A heat exchanger 3 is constructed by housing a heat exchange core 19 between a first fluid A and a second fluid E in the interior of a circular cross section casing 18. The core 19 has a hexagonal cross sectional configuration and is divided into three core divided structures 20 each having a parallel piped cross section containing adjacent hexagonal two sides P1 and P2. The core divided structure 20 is adapted such that a plurality of flat heat transfer plates 23 each for partitioning a first passage 21 trough which the first fluid A flows and a second passage 22 through which the second fluids E flows are arranged in parallel at a predetermined interval. Since in the heat exchanger 3 the cross sectional configuration of the core 19 contained in the interior of the casing 18 is hexagonal, a space between the lateral cross sectional configuration capable of securing pressure resistance strength and the core 19 is reduced to obtain a small-sized efficiency heat exchanger 3 with high heat exchange. A gas turbine apparatus using the heat exchanger 3 is also made small-sized.

8. 发明专利

JPH11263675A HEAT RESISTANT CERAMIC COMPOSITE AND ITS PRODUCTION 失效
公开(公告)号：JPH11263675A
公开(公告)日：1999-09-28
申请号：JP9074198
申请日：1998-03-18
申请人： KAWASAKI HEAVY IND LTD
发明人： NISHIO KOJI , SUEMITSU TAKESHI , IGASHIRA KENICHIROU , TAKEHARA TAKESHI
IPC分类号： C04B37/00 , F01D25/00 , F02C7/00
摘要： PROBLEM TO BE SOLVED: To obtain a ceramic composite capable of preventing getting loose of fiber by increasing the binding between the fibers a ceramic fiber, which binds ceramic-made separated bodies, and having high heat resistance and oxidation resistance in a heat resistant ceramic composite. SOLUTION: A ceramic matrix 16 is formed from the surface of fiber binding parts 14a to the inside by assembling plural ceramic made separated bodies 10 constituting the heat resistant ceramic composite into a structural body shape, winding plural fibers 12a, 12b each having different diameter around the outer surface of the structural body shaped ceramic made separated bodies 10 to bind the ceramic made separated bodies 10 and next infiltrating a resin or a gas to be the starting material of the ceramic matrix 16 into the surface and fiber gaps of the fiber binding parts 14a of the ceramic-made separated bodies 10 integrated into the structural body shape.

9. 发明专利

JPH11141305A GAS TURBINE HAVING MOVING BLADE SEGMENT WHOSE INCLINATION IS PREVENTED 失效
公开(公告)号：JPH11141305A
公开(公告)日：1999-05-25
申请号：JP30153997
申请日：1997-11-04
申请人： KAWASAKI HEAVY IND LTD
发明人： TAKEHARA TAKESHI , ICHIKAWA YOSHIHIRO
IPC分类号： F01D5/08 , F01D5/30 , F02C7/00
摘要： PROBLEM TO BE SOLVED: To prevent inclination of a moving blade segment of a gas turbine in a circumferential direction of a rotor disc. SOLUTION: A number of moving blade segments 15 are arranged circumferentially on an outer periphery of a rotor disc 13 of a turbine. A dovetail engagement part 17 having a single expansion portion is formed on a moving blade part 16 of each moving blade segment 15, on its inner side in a diameter direction. The engagement part 17 of the moving blade segment 15 is axially slid and fitted to the rotor disc 13. An engagement recession 14 is formed on the rotor disc 13 for preventing diametrally outer movement of the engagement part. A projection 17a is formed on a diametrally inner end of the engagement part 17, which the projection 17a is in contact with an inner bottom surface 14c of the engagement part 14 for preventing inclination of the moving blade segment 15 in a circumferential direction.

10. 发明专利

JPH07217450A SCROLL SUPPORTING STRUCTURE FOR CERAMIC GAS TURBINE 失效
公开(公告)号：JPH07217450A
公开(公告)日：1995-08-15
申请号：JP2627994
申请日：1994-01-28
申请人： KAWASAKI HEAVY IND LTD
发明人： TATSUMI TETSUO , TAKEHARA TAKESHI
IPC分类号： F02C7/20
摘要： PURPOSE:To provide a scroll supporting structure, which absorbs a thermal expansion difference between a metallic supporting structure member and a ceramic scroll while coping with a vibration load during operation and can stably fix and hold the ceramic scroll while securing centering, for a ceramic gas turbine. CONSTITUTION:A ceramic deflector 12 is constrained in the circumference direction and the radius direction via an uneven engaging part, with an outer circumference flange part 12a of the deflector 12 by means of a supporting ring 15 fixed on a metallic supporting frame 5. One end circumference part of a ceramic outer scroll 14 is placed on the outer circumference flange part of the deflector 12, the outer circumference part, of a ceramic inner scroll 13 is brought into contact with the other end circumference part of the ceramic outer scroll 14, one end part of a circular retainer 22 is engaged with the outer circumference part of the inner scroll 13, and the other end outside flange part of the retainer 22 is energized to the outer circumference flange part 12a side of the deflector 12 by means of plural ceramic springs 21 to be elastically supported and constrained in the gas turbine axial direction.

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