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2. 发明专利

JP2008512597A Cooling of the combustor of the outlet duct 审中-公开
公开(公告)号：JP2008512597A
公开(公告)日：2008-04-24
申请号：JP2007530558
申请日：2005-09-08
申请人：プラットアンドホイットニーカナダコーポレイションPratt & Whitney Canada Corp.
发明人：スタストニー，ホンザ , セー，ロバート
IPC分类号： F02C7/18 , F23R3/06 , F23R3/50 , F23R3/54
CPC分类号： F23R3/002 , F23R3/54 , F23R2900/03041 , F23R2900/03042
摘要：ガスタービン（１０）エンジンの燃焼器（１６）は、２つの交差する燃焼器壁部（３３／３２，３３'／３２'，３３”／３２”）間のコーナ（２４）のすぐ上流の燃焼器壁（２２）に複数の冷却開口（３４）を有する板金製の燃焼器壁を含む。

3. 发明专利

JP2005226923A Gas turbine engine 审中-公开
标题翻译：气体涡轮发动机
公开(公告)号：JP2005226923A
公开(公告)日：2005-08-25
申请号：JP2004036220
申请日：2004-02-13
申请人： Honda Motor Co Ltd , 本田技研工業株式会社
发明人： WARATANI ATSUKUNI , AMANO TAKUYA
IPC分类号： F23R3/52 , F23R3/54
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine engine miniaturizable while ensuring easiness of control.
SOLUTION: In this gas turbine engine, an annular combustor 10 is provided in a high pressure chamber 27 into which air taken in from an air inlet 3a and made high in pressure by a compressor HC is fed, and the ratio of cross-sectional area A of the combustor 10 to the opening area C of the air inlet is set within a range of 0.34-0.41 to prevent too much or two little air in an air-fuel ratio to thereby obtain an easily controllable state of output. The ratio of cross-sectional area A of the combustor 10 to the cross-sectional area B of a high pressure chamber is set within a range of 0.36-0.39 to prevent temperature from becoming high beyond the high temperature resistant limit of a member or becoming low to become low in efficiency. The diameter is reduced while maintaining these relations to obtain a compact gas turbine short in the whole length and small in diameter.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供一种小型化的燃气涡轮发动机，同时确保控制的容易性。解决方案：在该燃气涡轮发动机中，环形燃烧器10设置在高压室27中，从空气入口3a吸入空气并由压缩机HC供给高压的空气被供给到该高压室27中，将空气入口的开口区域C的燃烧器10的截面积A设定在0.34-0.41的范围内，以防止空燃比过多或两个小的空气，从而获得容易控制的输出状态。将燃烧器10的截面积A与高压室的截面积B的比率设定在0.36-0.39的范围内，以防止温度超出部件的耐高温极限或变得高温低到低效率。直径减小，同时保持这些关系，以获得全长短且直径小的紧凑型燃气轮机。版权所有（C）2005，JPO＆NCIPI

4. 发明专利

JP2005098678A Method and apparatus for reducing emission of gas turbine engine 审中-公开
标题翻译：减少气体涡轮发动机排放的方法和装置
公开(公告)号：JP2005098678A
公开(公告)日：2005-04-14
申请号：JP2004212469
申请日：2004-07-21
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： COLIBABA-EVULET ANDREI , BOWMAN MICHAEL JOHN , SANDERSON SIMON RALPH , DEAN ANTHONY JOHN
IPC分类号： F23R3/14 , F02C1/00 , F02C7/00 , F02C7/232 , F02C9/26 , F23R3/00 , F23R3/02 , F23R3/28 , F23R3/30 , F23R3/32 , F23R3/34 , F23R3/42 , F23R3/54
CPC分类号： F23R3/54 , F23R3/002 , F23R3/14 , F23R3/34 , F23R2900/03044 , Y02T50/675
摘要： PROBLEM TO BE SOLVED: To provide a combustor for a gas turbine engine. SOLUTION: A low emission turbine includes a reverse flow can-type combustor 102 generally including primary and secondary fuel delivery systems which are independently controlled to produce low CO, UHC and NOx emissions at design set point and at conditions other than design set point. The reverse flow can-type combustor 102 generally includes a swirler and mixer assembly 140 within the combustor, wherein each swirler and mixer assembly 140 comprises an array of annularly arranged swirlers and mixers including the primary and secondary fuel delivery systems, and the primary and secondary fuel delivery systems are independently controlled. The can-type combustor including fluid passageways 142, 220 that allow the fluid to perpendicularly impinge on a backside of a heat shield 136, is also disclosed. COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供一种用于燃气涡轮发动机的燃烧器。解决方案：低排放涡轮机包括反向流动罐式燃烧器102，其通常包括主燃料输送系统和辅助燃料输送系统，其独立地被控制以在设计设定点和除设计设定之外的条件下产生低CO，UHC和NOx排放点。反向罐式燃烧器102通常在燃烧器内部包括旋流器和混合器组件140，其中每个旋流器和混合器组件140包括环形布置的旋流器和混合器的阵列，其包括主要和次要燃料输送系统，以及初级和次级燃烧器燃油输送系统是独立控制的。还公开了包括允许流体垂直地撞击隔热板136的背面的流体通道142,220的罐式燃烧器。版权所有（C）2005，JPO＆NCIPI

5. 发明专利

JP3523309B2 Gas turbine combustor 失效
公开(公告)号：JP3523309B2
公开(公告)日：2004-04-26
申请号：JP31668493
申请日：1993-12-16
申请人：アルストム
发明人：シュルテ−ヴェルニングブルクハルト , アルトハウスロルフ
IPC分类号： F23R3/42 , F02C7/18 , F23R3/02 , F23R3/04 , F23R3/54
CPC分类号： F23R3/54 , F05B2240/32 , F05B2260/222 , F05B2260/2241 , F23R3/02

6. 发明专利

JP2000193243A FUEL INJECTOR BAR FOR GAS TURBINE ENGINE COMBUSTOR HAVING TRAPPED VORTEX CAVITY 失效
公开(公告)号：JP2000193243A
公开(公告)日：2000-07-14
申请号：JP29307199
申请日：1999-10-15
申请人： GEN ELECTRIC
发明人： DAVID LEWIS BARRAS , ARTHUR WESLEY JOHNSON
IPC分类号： F23R3/52 , F23R3/12 , F23R3/28 , F23R3/54
摘要： PROBLEM TO BE SOLVED: To supply fuel to cavity sections which can have relatively small spaces and a flow passage through which an air flow is fed to a cavity section by making the fuel to be fed to the flow passages formed in a dome inlet module or the cavities through a fuel injector bar. SOLUTION: Fuel is only fed from the injection nozzle of a fuel injector bar 50 and air is also blown into cavities 40 and 42 through passages 92 and 94 respectively provided at the intersections of a rear wall and external and internal walls and a passage 96 provided at the intersections of a front wall and the external and internal walls. Consequently, the trapped vortexes of the fuel and air are formed in the cavities 40 and 42. Thereafter, the air-fuel mixed gases in the cavities 40 and 42 are ignited by means of, for example, an igniter 100 and combustion gases are produced in the cavities 40 and 42. Thereafter, the combustion gases are discharged from the cavities 40 and 42 across the downstream end of a dome inlet module 20 and interacts with the main-flow air flowing through a flow passage 38.

7. 发明专利

JPH11101436A STRUCTURE OF CERAMIC COMBUSTOR 失效
公开(公告)号：JPH11101436A
公开(公告)日：1999-04-13
申请号：JP26521697
申请日：1997-09-30
申请人： NISSAN MOTOR
发明人： MUNEKIYO MASAYUKI
IPC分类号： F23R3/34 , F23R3/42 , F23R3/54
摘要： PROBLEM TO BE SOLVED: To provide a ceramic combustor capable of raising temperature of air at the inlet of the combustor and enhancing exhausting performance. SOLUTION: A circumferential direction elastic support member 11 (hereinafter, referred to as wave fin) made of a heat resisting metal is formed from a dilution hole 7 in an outer wall of a combustion cylinder to a dome 16. The wave fin 11 has a corrugated shape and the inner diameter of the wave fin 11 is smaller than the outer diameter of the combustion cylinder and larger than the inner diameter of a combustor outer cylinder 2 before being assembled in a passage 5 formed between the combustor outer cylinder 2 and the combustion cylinder. Movement of the combustor in an axial direction is restricted by a stopper 15.

8. 发明专利

JPH1163500A COMBUSTOR 失效
公开(公告)号：JPH1163500A
公开(公告)日：1999-03-05
申请号：JP22950297
申请日：1997-08-26
申请人： ISHIKAWAJIMA HARIMA HEAVY IND
发明人： NARISAWA MICHINORI
IPC分类号： F23R3/42 , F23C99/00 , F23R3/54 , F23C11/00
摘要： PROBLEM TO BE SOLVED: To reduce the size of a combustor by burning a fuel completely through heavy load lean combustion thereby suppressing generation of NOx and increasing the combustion load. SOLUTION: The egg type combustor 1 has double shell structure of inner and outer shells 2, 3 where the inside of the outer shell 3 is a combustion chamber 4 and the space between the inner and outer shells 2, 3 is an air supply path 5. The outer shell 3 is coupled, at one longitudinal end thereof, with an air supply pipe 6 and provided, at the other end thereof with a combustion gas exhaust nozzle 7. The air supply path 5 is coupled with a plurality of fuel supply pipes 10 and the air 13 is mixed with a fuel 14 in the air supply path 5. The air supply path 5 is bent inward, on the other side thereof, to surround the combustion gas exhaust nozzle 7 and a plurality of mixed gas ejection ports 6a are made, at the forward end thereof, in order to eject a mixed gas 15 toward one end side of the combustion chamber 4 arranged with a spark plug 12.

9. 发明专利

JPH10160162A NITROGEN OXIDE REDUCTION STRUCTURE OF GAS TURBINE COMBUSTOR 失效
公开(公告)号：JPH10160162A
公开(公告)日：1998-06-19
申请号：JP32772696
申请日：1996-11-22
申请人： ISHIKAWAJIMA HARIMA HEAVY IND
发明人： FUJIMORI TOSHIRO , SAITO TSUKASA
IPC分类号： F23R3/28 , F23C99/00 , F23D11/12 , F23R3/32 , F23R3/54 , F23C11/00
摘要： PROBLEM TO BE SOLVED: To suppress the production of nitrogen oxides by supplying the combustor of a gas turbine with fuel and air through an inserted preevaporating and premixing pipe member of specified length. SOLUTION: In a gas turbine combustor 10, liquid fuel such as kerosene or the like injected from a fuel injection valve 31 is mixed with the swirling air current through a swirler 32 inside a preevaporating and premixing pipe 20, and is supplied into a liner 11 from the tip of the preevaporating and premixing pipe 20 and then combusted. Here, the flame turns about between the preevaporating and premixing pipe 20 and the inner face of the liner 11, and preheats the preevaporating and premixing pipe 20. Therefore, the evaporation of the liquid fuel is accelerated, and also the mixed gas is heated, and it is supplied to the liner 11 in condition that it is easy to combust. Moreover, a recirculating current which returns to the side of this mixing pipe 20 is made at the center in front of the preevaporating and premixing pipe 20, whereby the combustion gas circulates to the combustion region, and the combustion becomes stable. Hereby, eve if it is thin mixed gas, the stable combustion becomes possible, and the production of nitrogen oxides is suppressed.

10. 发明专利

JPH094844A COMBUSTION APPARATUS 失效
公开(公告)号：JPH094844A
公开(公告)日：1997-01-10
申请号：JP80003889
申请日：1989-09-28
申请人： UNITED TECHNOLOGIES CORP
发明人： TOOMASU ERU DOUBERU , JIEEMUZU ETSUCHI SHIYADOUEN
IPC分类号： F23C7/02 , F23R3/04 , F23R3/10 , F23R3/26 , F23R3/28 , F23R3/50 , F23R3/52 , F23R3/54
摘要： PURPOSE: To stabilize the operation of an annular combustor for a gas turbine in the environment of high temperature rise by reducing the length of the combustor, and combining the air intake through constitution of regions on the circumference. CONSTITUTION: An air intake is of one stage, and a combustor is divided into a primary region and a dilution region 30. Air passages 44, 46 are provided on each of a plurality of fuel nozzles 20, and a vortex flow chamber to give the vortex flow to the air in sucking the air in the normal combustion region is provided. The fuel nozzles 20 are arranged with intervals on the circumference flitted in a dome. The air passages 40, 42 in the fuel nozzles, and the air passages 44, 46 in an outer annular wall, i.e., a liner 48 and in an inner annular wall, i.e., a liner 50 are of different dimensions so as to demarcate the space in the combustor to which the air flow is fed. That means, the air intake openings 42, 44, 46 to make the air flow smaller than the air flow to be sucked in other spaces on the circumference are included in the specified spaces on the circumference.

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