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11. 发明专利

JP2006097981A Gas turbine combustor 审中-公开
标题翻译：气体涡轮搅拌机
公开(公告)号：JP2006097981A
公开(公告)日：2006-04-13
申请号：JP2004285260
申请日：2004-09-29
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： ISHIGURO TATSUO , TANAKA KATSUNORI , MIYAUCHI KOTARO , KONDO MITSURU
IPC分类号： F23R3/06 , F02C7/18 , F23R3/18
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor comprising an acoustic liner capable of preventing shortening of its service life by heat stress and largely adjusting its aperture ratio.
SOLUTION: A cooling groove extending obliquely to a line of intersection of a central axis and a wall of a heat chamber, is formed inside of the wall of the heat chamber in the acoustic liner. Thus uniform cooling can be performed even when a diameter of an acoustic hole is large. Inside of the acoustic liner, a cooling fin is mounted on an outer wall of the heat chamber to improve cooling efficiency. Several kinds of materials different in coefficients of thermal expansion are used in the acoustic liner. The material of high coefficient of thermal expansion is used at a part far from the heat chamber 2 and decreased in its temperature during operation, to reduce the difference in thermal expansion with respect to a part of high temperature. A housing of the acoustic liner is mounted on the heat chamber in a state of being incorporated by a bolt or inserted by a guide. Thus the thermal expansion is further relieved by the play of a mounting part. The housing is covered by a thermal shield to prevent the release of heat, thus the temperature difference from a wall surface of the heat chamber is reduced, and heat stress can be reduced.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供一种燃气轮机燃烧器，其包括能够防止由于热应力而缩短其使用寿命并大大调节其开口率的声衬。解决方案：在声学衬垫中的加热室的壁的内部形成有一个倾斜地延伸到加热室的中心轴和壁的相交线的冷却槽。因此即使在声孔的直径较大的情况下也能够进行均匀的冷却。在声学衬垫的内部，散热片安装在加热室的外壁上，以提高冷却效率。在声学衬垫中使用了几种热膨胀系数不同的材料。在远离加热室2的部分使用高热膨胀系数的材料，并且在运转时其温度降低，以减少相对于高温部分的热膨胀差。声学衬垫的壳体被安装在加热室中，处于由螺栓结合或由引导件插入的状态。因此，通过安装部件的播放进一步减轻了热膨胀。壳体被热屏蔽覆盖以防止热量的释放，因此与加热室的壁表面的温度差减小，并且可以降低热应力。版权所有（C）2006，JPO＆NCIPI

12. 发明专利

JP2001153362A GAS TURBINE COMBUSTOR 失效
公开(公告)号：JP2001153362A
公开(公告)日：2001-06-08
申请号：JP33620599
申请日：1999-11-26
申请人： MITSUBISHI HEAVY IND LTD
发明人： BANDAI SHIGEMI , OOTA MASATOYO , NISHIDA KOICHI , MIYAUCHI KOTARO
IPC分类号： F23R3/02
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor which is reduced in cost and increased in strength and combustion performance through the simplification of its configuration. SOLUTION: The gas turbine combustor is constituted in such a way that an inner tube is mounted on a substrate, with a plurality of main swirelers being arranged along the inner periphery of the tube, and a pilot swirler is provided at the central part surrounded by the main swirlers. Then a flame stabilizer is provided on the downstream side of the pilot swirler, and a combustion chamber and a transmission pipe are connected to each other on the downstream side of the inner tube. In the combustor, at least two of the main swirlers, substrate, pilot swirler, flame stabilizer, and transition pipe are integrally formed.

13. 发明专利

JP2000039147A PILOT NOZZLE FOR COMBUSTOR EQUIPPED WITH FLEXIBLE JOINT 失效
公开(公告)号：JP2000039147A
公开(公告)日：2000-02-08
申请号：JP20528898
申请日：1998-07-21
申请人： MITSUBISHI HEAVY IND LTD
发明人： KOBAYASHI KAZUYA , SATOU HISAYASU , MIYAUCHI KOTARO
IPC分类号： F02C7/22 , F23R3/28
摘要： PROBLEM TO BE SOLVED: To remove the affection of a thermal stress on the tip end unit of a combustor by absorbing the difference of thermal elongation between the outside and the inside of the same, with respect to a dual system pilot nozzle for the gas turbine combustor employed by switching oil into gas. SOLUTION: An air passage 21 is formed between a cylindrical unit 13 and an outside pipe 14 while a gas passage 22 is formed between the outside pipe 14a and an inside pipe 15 to pass air 34 and gas pilot fuel 32 respectively and inject them from an air injection port 25 and a gas injection port 24, which are equipped at the tip end of a combustor. An oil fuel nozzle 20 is penetrated through the inside pipe 15 and water is passed through the periphery of the nozzle 20 while oil is injected from an oil injection port 26. The temperature of air is 400 deg.C, the temperature of the gas fuel is 15-200 deg.C, the temperature of the water passage is a normal temperature and, accordingly, the difference of thermal elongation is generated between the outside pipe 14 and the inside pipe 15, however, one end of the outside cover 2 is fixed to the fore outside tube 14a the other end of the same is slid on a rear tube 14b and a flexible tube 1 is also contractable whereby the difference of thermal elongation can be absorbed and a stress will not be generated in the tip end unit.

14. 发明专利

JP2001254947A GAS TURBINE COMBUSTOR 失效
公开(公告)号：JP2001254947A
公开(公告)日：2001-09-21
申请号：JP2000071117
申请日：2000-03-14
申请人： MITSUBISHI HEAVY IND LTD
发明人： NISHIDA HIROYUKI , ITSURA TETSUO , HASHIMURA JUNJI , BANDAI SHIGEMI , HIRASAKI TAKEO , MIYAUCHI KOTARO
IPC分类号： F23R3/34 , F23R3/14 , F23R3/32
摘要： PROBLEM TO BE SOLVED: To restrain combustion vibration of a gas turbine combustor. SOLUTION: A pilot nozzle 31 is provided at the center of a combustor 1 to form pilot flames, while a plurality of main nozzles 33 are disposed around the pilot nozzle to inject a premixed gas of air and fuel which are ignited by the pilot flames to form premixed flames in the combustor 1. Oval extension pipes 34 are provided in order to direct the premixed gas injected from the main nozzles 33 to the surrounding of the exit of a pilot cone 36 which is disposed around the exits of the pilot nozzles. A portion of the oval extension pipes of the main nozzles are rendered to have different exit forms (opening area, shape or the like) from the others so as to prevent the premixed gas from all of the main nozzles from being ignited and combusted at the same position in the axial direction of an inner cylinder 5b of the combustor. Thus, conversion of heat generated by combustion to a narrow region in the inner cylinder is prevented, thereby restraining combustion vibration.

15. 发明专利

JP2000310422A FUEL NOZZLE 失效
公开(公告)号：JP2000310422A
公开(公告)日：2000-11-07
申请号：JP11809299
申请日：1999-04-26
申请人： MITSUBISHI HEAVY IND LTD
发明人： OOTA MASATOYO , INADA MITSURU , HARUTA HIDEKI , NISHIDA KOICHI , TSUKAGOSHI KEIZO , AKAMATSU SHINJI , MIYAUCHI KOTARO
IPC分类号： F23R3/28 , F23D11/12
摘要： PROBLEM TO BE SOLVED: To uniform the mixing condition of fuel and gas in a state where the load of a gas turbine is varied and a fuel flow rate is varied, by alternately establishing large diameter nozzle holes and small diameter nozzle holes in a circumferential direction, and conducting switching between a fuel supply path which communicates with the large diameter nozzle hole and a fuel supply path which communicates with the small diameter nozzle hole, according to the load variation. SOLUTION: A main fuel nozzle body 50 is provided in its circumference at a downstream side with large diameter nozzle holes 53 and small diameter nozzle holes 54 having a smaller diameter than the former, which are alternately arranged and established in the circumferential direction. There are also provided a fuel supply path 52 which communicates with the large diameter nozzle hole 53 and a fuel supply path 51 which communicates with the small nozzle hole 54. The path 51 and the path 52 are selectively used to suitably supply fuel therethrough in accordance with the load variation of a gas turbine. For example, when low load is imposed on the gas turbine, as the fuel flow rate is reduced, the path 51 is selected to jet the fuel to fuel air through the small nozzle hole 54.

16. 发明专利

JP2000171038A GAS TURBINE COMBUSTOR 失效
公开(公告)号：JP2000171038A
公开(公告)日：2000-06-23
申请号：JP34883898
申请日：1998-12-08
申请人： MITSUBISHI HEAVY IND LTD
发明人： SATOU HISAYASU , KAWACHI YOJI , AKAGI KOICHI , CHIKAMI RINTAROU , KOBAYASHI KAZUYA , NISHIDA KOICHI , AKAMATSU SHINJI , HARUTA HIDEKI , MIYAUCHI KOTARO
IPC分类号： F02C7/18 , F23R3/16 , F23R3/28
摘要： PROBLEM TO BE SOLVED: To improve the performance of a combustor by a method wherein the suction of air of a gas turbine combustor is unified, the thermal stress of the same is reduced and the cooling of the same is unified. SOLUTION: A pilot fuel nozzle and a pilot cone 33 are arranged at the center of an inner tube 28 for a combustor 20 while a main fuel nozzle and a main swirler 32 are arranged around the pilot cone 33. A flow regulating tube 11 is provided in an air suction unit (X-1) to unify suction air and the optimum number of air holes are provided around the inner tube 28 in the air suction unit (X-2) while the main swirler 32 is connected to a main swirler unit (X-3) and a pilot cone unit (X-4) by bolts respectively while the optimization of welding at the welded places of the pilot cone 33 is applied to obtain a structure for reducing the effect of a thermal stress and the cooling mechanism of a flange unit 71 for a tail tube 24 is constituted so as to unify the cooling of a tail tube cooling unit (X-5) and minimize the affection of a thermal stress. According to the improvement in the units (X-1)-(X-5), troubles accompanied by the high temperature of the combustor are eliminated to improve the performance of the combustor.

17. 发明专利

JPH11223341A COMBUSTOR 失效
公开(公告)号：JPH11223341A
公开(公告)日：1999-08-17
申请号：JP2705098
申请日：1998-02-09
申请人： MITSUBISHI HEAVY IND LTD
发明人： BANDAI SHIGEMI , NISHIDA KOICHI , OOTA MASATOYO , TANIMURA SATOSHI , MIYAUCHI KOTARO , INADA MITSURU , AKAMATSU SHINJI
IPC分类号： F23R3/20 , F23R3/28 , F23R3/32
摘要： PROBLEM TO BE SOLVED: To provide a combustor for a gas turbine in which high temperatureflame of premixed gas is prevented from flowing back to the main swirler region. SOLUTION: A pilot nozzle 02 arranged with a plurality of main nozzles 03 on the outer circumference is disposed in the center of an inner tube 01 having forward end opening into a combustion chamber. A flame holding cone 014 projecting forward from the pilot nozzle 02 fires fuel F ejected from the main nozzle 03 by generating flame internally and in front of the inner tube 01. An extension pipe 16 having elliptical cross-section is arranged along the outer circumference of the cone 014 such that the long axis is directed in the circumferential direction of the inner tube 01 with an opening being made at an axial position where the cone 014 is opened while projecting forward of the main nozzle 03.

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