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1. 发明专利

JP2009079483A Gas turbine combustor 有权
标题翻译：气体涡轮搅拌机
公开(公告)号：JP2009079483A
公开(公告)日：2009-04-16
申请号：JP2007247225
申请日：2007-09-25
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： MOTAI TADAYUKI , ISHIGURO TATSUO , NAKAMURA SOSUKE , TANAKA KATSUNORI
IPC分类号： F02C7/18 , F01D25/00 , F01D25/12 , F02C7/24 , F23R3/06 , F23R3/16 , F23R3/28 , F23R3/42
摘要： PROBLEM TO BE SOLVED: To efficiently cool down a gas turbine combustor in accordance with thermal load distribution. SOLUTION: This gas turbine combustor 1 includes a fuel supply part 9 and a heat chamber 2. The fuel supply part 9 supplies fuel to a heat chamber inner space 8 positioned inside the heat chamber 2. The heat chamber 2 supplies combustion gas generated by combustion of the fuel to a turbine. The fuel supply part 9 includes a plurality of fuel nozzles 14 disposed along a circle with an axial line S of the heat chamber 2 centered. A plurality of passages 31, 32, 51 extending in a main flow direction of the combustion gas flowing in the heat chamber inner space 8 are provided along a circumferential direction of the heat chamber 2. Coolant is supplied to each of a plurality of the passages 31, 32, 51. A plurality of the passages 31, 32, 51 include a fuel nozzle correspondence passage 321 which is disposed on the downstream side in the main flow direction of the fuel nozzle 14 and a fuel nozzle interval correspondence passage 322 which is disposed on the downstream side in the main flow direction between the two adjacent nozzles among a plurality of the fuel nozzles 14. The equivalent diameter of the fuel nozzle correspondence passage 321 is larger than the equivalent diameter of the fuel nozzle interval correspondence passage 322. COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：根据热负荷分布有效地冷却燃气轮机燃烧器。解决方案：该燃气轮机燃烧器1包括燃料供给部9和加热室2.燃料供给部9向位于加热室2内的加热室内部空间8供给燃料。加热室2供给燃烧气体通过将燃料燃烧到涡轮而产生。燃料供给部9包括沿着加热室2的轴线S居中的圆形配置的多个燃料喷嘴14。沿着加热室2的圆周方向设置沿着加热室内部空间8流动的燃烧气体的主流动方向延伸的多个通路31,32,51。冷却液被供给到多个通路多个通道31,32,51包括燃料喷嘴对应通道321，其设置在燃料喷嘴14的主流动方向的下游侧，燃料喷嘴间隔对应通道322 设置在多个燃料喷嘴14中的两个相邻喷嘴之间的主流动方向的下游侧。燃料喷嘴对应通道321的等效直径大于燃料喷嘴间隔对应通道322的当量直径。 P>版权所有（C）2009，JPO＆INPIT

2. 发明专利

JP2007309644A Combustor for gas turbine 有权
标题翻译：燃气轮机
公开(公告)号：JP2007309644A
公开(公告)日：2007-11-29
申请号：JP2007204702
申请日：2007-08-06
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： ISHIGURO TATSUO , SUENAGA KIYOSHI , TANAKA KATSUNORI , BANDAI SHIGEMI
IPC分类号： F23R3/18 , F23R3/06 , F23R3/44
摘要： PROBLEM TO BE SOLVED: To provide a combustor for a gas turbine with uniform combustion in both gas firing and oil firing.
SOLUTION: An inner cylinder of the combustor is formed into a trumpet shape with a diameter getting larger along toward a downstream. Oil is prevented from accumulating because a low-velocity area is not generated in the trumpet shape. The oil is further film-cooled by cooling air from a cooling hole having a shape free from a step difference of depositing the oil. A spacer getting to a cause of the low-velocity area of depositing the oil is not installed in the cooling hole. The oil in the vicinity of the cooling hole is blown off by the cooling air. The cooling hole is constituted to make an opening get larger in a portion with a higher calorific value. The used cooling air is small in a portion with a lower calorific value, and the air saved thereby is used for combustion.
COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：在气体燃烧和油烧制中提供具有均匀燃烧的燃气轮机的燃烧器。解决方案：燃烧器的内筒形成为具有朝向下游的直径变大的喇叭形状。由于小喇叭形状中不会产生低速区域，所以防止油积聚。通过从具有没有沉积油的阶梯差的形状的冷却孔冷却空气来进一步进行膜冷却。导致沉积油的低速区域的原因的间隔物没有安装在冷却孔中。冷却孔附近的油被冷却空气吹出。冷却孔被构成为使得开口在具有较高热值的部分中变大。所使用的冷却空气在热值较低的部分较小，并且由此节省的空气用于燃烧。版权所有（C）2008，JPO＆INPIT

3. 发明专利

JP2006097983A Gas turbine combustor 审中-公开
标题翻译：气体涡轮搅拌机
公开(公告)号：JP2006097983A
公开(公告)日：2006-04-13
申请号：JP2004285292
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 , OKADA IKUO
IPC分类号： F23R3/06 , F02C7/00 , F23R3/18
摘要： PROBLEM TO BE SOLVED: To provide an inexpensive and strong acoustic liner for a gas turbine combustor.
SOLUTION: At least an acoustic liner portion of the gas turbine combustor is manufactured by casting. A core for forming a housing and a sound absorbing hole of the acoustic liner is formed by manufacturing a number of small cores of the same shape and combining them to be used as the core of the acoustic liner as a whole.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：为燃气轮机燃烧器提供便宜且强大的声学衬垫。解决方案：通过铸造制造燃气轮机燃烧器的至少一个声衬套部分。用于形成声衬垫的外壳和吸音孔的芯通过制造相同形状的多个小芯体并将其组合以整体用作声垫的芯体而形成。版权所有（C）2006，JPO＆NCIPI

4. 发明专利

JP2005076982A Gas turbine combustor 审中-公开
标题翻译：气体涡轮搅拌机
公开(公告)号：JP2005076982A
公开(公告)日：2005-03-24
申请号：JP2003308062
申请日：2003-08-29
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： IKEDA KAZUFUMI , ISHIGURO TATSUO , TANAKA KATSUNORI , TANIMURA SATOSHI
IPC分类号： F23R3/16 , F02C7/00 , F02C7/24 , F23M99/00 , F23R3/00 , F23R3/12 , F23R3/42
CPC分类号： F23R3/002 , F23M20/005 , F23R2900/00014
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor provided with a combustion vibration suppressing means with high heat resisting performance. SOLUTION: The gas turbine combustor includes an acoustic liner (resonance box) set in the circumferential direction of a combustor liner, which extends in a length equal to or longer than the diameter of the combustor liner. The wall surface of the combustor liner in the part where the acoustic liner is set has pores, so that the combustion gas in the combustor liner and the gas in the acoustic liner are mutually resonated, and combustion vibration is attenuated by the friction with the wall surfaces of the pores. The acoustic liner has a partition-free space having a length equal to or longer than the diameter of the combustor liner in the inner part. The acoustic liner has high heat resisting strength with minimized stress concentration because it is molded so as to have no acute angle or right angle by press working. COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供一种具有高耐热性能的燃烧式振动抑制装置的燃气轮机燃烧器。解决方案：燃气轮机燃烧器包括设置在燃烧器衬套的圆周方向上的声学衬垫（共振箱），其在等于或长于燃烧器衬套的直径的长度上延伸。在设置声学衬垫的部分中的燃烧器衬套的壁表面具有孔，使得燃烧器衬套中的燃烧气体和声衬垫中的气体相互谐振，并且燃烧振动由于与壁的摩擦而衰减孔的表面。声学衬垫具有长度等于或大于内部部分中的燃烧器衬套直径的无分隔空间。声学衬垫具有高耐热强度和最小化的应力集中，因为它被模制成通过冲压加工没有锐角或直角。版权所有（C）2005，JPO＆NCIPI

5. 发明专利

JP2004183945A Gas turbine combustor and gas turbine equipped with the same 审中-公开
标题翻译：燃气轮机和燃气涡轮机配备
公开(公告)号：JP2004183945A
公开(公告)日：2004-07-02
申请号：JP2002349763
申请日：2002-12-02
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： IKEDA KAZUFUMI , ONO MASAKI , TANAKA KATSUNORI
IPC分类号： F23R3/26 , F02C9/20
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor capable of reducing combustion vibration so as to consistently realize low NOx.
SOLUTION: The combustor 3 comprises a tail cylinder 7 connected to a front end of an inner cylinder 6 having a combustion area, and a bypass duct 11 in which one end 11a is opened in the tail cylinder 7 and the other end 11b is opened in a wheel chamber forming a periphery of the inner cylinder 6 and the tail cylinder 7, and a plate-like member 50 having a large number of through holes 52 and passing through a bypass duct 11 is disposed therein. Fluid particles which are vibrational elements of the combustion vibration occurred in the combustion area are introduced from one end 11a of the bypass duct 11 and effectively captured by each through hole 51 of the plate-like member 50, and vibrated through each through hole 51 in resonance with air in the wheel chamber 5 connected by the bypass duct 11.
COPYRIGHT: (C)2004,JPO&NCIPI
摘要翻译：要解决的问题：提供一种能够减少燃烧振动以便始终实现低NOx的燃气轮机燃烧器。解决方案：燃烧器3包括连接到具有燃烧区域的内筒6的前端的尾缸7和在尾气缸7中一端11a打开的旁通管道11，另一端11b 在形成内筒6和尾筒7的周边的轮室中打开，并且具有多个通孔52并通过旁通管道11的板状构件50设置在其中。作为在燃烧区域中发生的燃烧振动的振动元件的流体颗粒从旁通管道11的一端11a引入，并被板状构件50的每个通孔51有效地捕获，并通过各个通孔51振动与通过旁路管道11连接的车轮室5中的空气共振。版权所有（C）2004，JPO＆NCIPI

6. 发明专利

JP2004101105A Combustor 有权
公开(公告)号：JP2004101105A
公开(公告)日：2004-04-02
申请号：JP2002265281
申请日：2002-09-11
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： OOTA MASATOYO , BANDAI SHIGEMI , AOYAMA KUNIAKI , TANAKA KATSUNORI , NISHIDA KOICHI , AKIZUKI WATARU , KASAI TAKAKUNI , HASHIMURA JUNJI
IPC分类号： F23R3/28
摘要： PROBLEM TO BE SOLVED: To provide a combustor suppressing combustion vibration while making a pilot ratio low.
SOLUTION: Pilot fuel injected from a fuel injection port 21 of a pilot nozzle 2 collides with the internal wall surface of a cone inner peripheral taper part 41 of a pilot cone 4. The collision position of the pilot fuel from the fuel injection port 21 at this time is located in a range from the intermediate part to the downstream tip in the cone inner peripheral taper part 41.
COPYRIGHT: (C)2004,JPO

7. 发明专利

JP2004101071A Combustor 有权
公开(公告)号：JP2004101071A
公开(公告)日：2004-04-02
申请号：JP2002263663
申请日：2002-09-10
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： OOTA MASATOYO , BANDAI SHIGEMI , AOYAMA KUNIAKI , TANAKA KATSUNORI , AKAMATSU SHINJI , NAKAJIMA HISANARI , TACHIBANA TERUYA
IPC分类号： F23R3/18 , F02C7/232 , F23D14/02 , F23D14/74 , F23R3/28
摘要： PROBLEM TO BE SOLVED: To provide a combustor preventing the occurrence of a stagnant region at the outlet of a main combustor while making a flame stabilizing low speed region larger and more positive.
SOLUTION: A cone internal taper part 41 of a pilot cone 4a is provided with a collar 42 extending from the downstream tip toward the vicinity of the downstream tip of the main combustor 5. The flame stabilizing low speed region is formed downstream of the collar 42, and air between the collar 42 and a collar 44 of a cylinder 43 at the outer periphery of the cone internal taper part 41, flows in the form of a film to the downstream tip of the main combustor 5 to improve the flame stability of the flame stabilizing low speed region.
COPYRIGHT: (C)2004,JPO

8. 发明专利

JP2004092409A Combustor and a gas turbine 审中-公开
公开(公告)号：JP2004092409A
公开(公告)日：2004-03-25
申请号：JP2002251025
申请日：2002-08-29
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： TANAKA KATSUNORI , KISHIDA HIROAKI
IPC分类号： F02C7/18
摘要： PROBLEM TO BE SOLVED: To improve durability of a combustion cylinder by preventing thermal fatigue in a connecting part of the combustion cylinder and a bypass tube. SOLUTION: Air and fuel compressed by a compressor is made to react and combusted by the combustor which introduces generated combustion gas into a turbine through a combustion cylinder 5. A through-hole 20 is formed on a side wall of the bypass tube 6 for introducing air into the combustion cylinder 5, and a sleeve 21 for guiding air which is sucked into the bypass tube 6 through the through-hole 20, to the connecting part of the combustion cylinder 5 and the bypass tube 6, is provided inside the bypass tube 6. COPYRIGHT: (C)2004,JPO

9. 发明专利

JP2004084490A Gas turbine combustor and operation method for the same 审中-公开
公开(公告)号：JP2004084490A
公开(公告)日：2004-03-18
申请号：JP2002243235
申请日：2002-08-23
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： AKIZUKI WATARU , NISHIDA KOICHI , TANAKA KATSUNORI
IPC分类号： F02C9/34 , F23R3/14 , F23R3/28 , F23R3/30
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor and an operation method therefor that can effectively suppress emissions of carbon monoxide, unburned hydrocarbon and other unburned gases.
SOLUTION: Main nozzles 10 of the gas turbine combustor have first injection holes 117 for injecting premixed combustion fuel gas, and have on a downstream side of the first injection holes 117 a swirler 112 for agitating the injected premixed combustion fuel gas to promote premixing. At a point of the main nozzles 10 and on a downstream side of the swirler 112, a second injection hole 11 for injecting diffuse combustion fuel gas is provided.
COPYRIGHT: (C)2004,JPO

10. 发明专利

JP2003329243A Combustor transition piece for gas turbine, and gas turbine 有权
标题翻译：用于气体涡轮机和燃气轮机的COMBUSTOR过渡件
公开(公告)号：JP2003329243A
公开(公告)日：2003-11-19
申请号：JP2002136271
申请日：2002-05-10
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： BANDAI SHIGEMI , OOTA MASATOYO , TANAKA KATSUNORI , SATO KENJI
IPC分类号： F23R3/16 , F23R3/42
摘要： PROBLEM TO BE SOLVED: To suppress a temperature rise in a combustor transition piece in a downstream side of a bypass hole.
SOLUTION: This combustor transition piece 10 makes out a body portion 30 of the combustor transition piece 10 in the downstream of the bypass hole 20 bulge from the body portion 03 in an upstream side of the bypass hole 20 toward the bypass hole 20. Bulging δ like this is provided on the body portion 30 of the combustor transition piece 10, thereby lowering the flow speed of combustion gas near a wall surface of the combustion transition piece 10 in the downstream side of the bypass hole 20. The body portion 30 of the combustor transition piece 10 is expanded in the downstream to the bypass hole 20, so that a swirl conventionally generated in the downstream side of the bypass hole 20 is hard to be generated.
COPYRIGHT: (C)2004,JPO
摘要翻译：要解决的问题：抑制旁通孔下游侧的燃烧器过渡件的温度升高。解决方案：该燃烧器过渡片10在旁通孔20的下游形成燃烧器过渡件10的主体部分30，在旁通孔20的上游侧朝向旁通孔20从主体部分03隆起在燃烧器过渡片10的主体部30上设置有膨胀δ，从而降低旁通孔20的下游侧的燃烧用过渡件10的壁面附近的燃烧气体的流速。主体部燃烧器过渡件10的下游侧30被扩展到旁通孔20，从而难以产生通常在旁通孔20的下游侧产生的涡流。版权所有（C）2004，JPO

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