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1. 发明专利

JP4608360B2 Device for supplying air and fuel to the burner ring of the afterburner chamber 有权
公开(公告)号：JP4608360B2
公开(公告)日：2011-01-12
申请号：JP2005125997
申请日：2005-04-25
申请人：スネクマ
发明人：ジヤツク・ビユネル , ジヤツク・ロツシユ
IPC分类号： F02K3/11 , F23R3/18 , F23R3/20
CPC分类号： F23R3/20 , F02K3/11

2. 发明专利

JP3167232B2 失效
公开(公告)号：JP3167232B2
公开(公告)日：2001-05-21
申请号：JP25616493
申请日：1993-10-13
IPC分类号： F02K3/10 , F02K3/11

3. 发明专利

JP2001132541A JET ENGINE FOR SUPERSONIC AIRCRAFT 失效
公开(公告)号：JP2001132541A
公开(公告)日：2001-05-15
申请号：JP31938999
申请日：1999-11-10
申请人： NAT AEROSPACE LAB
发明人： FUTAMURA HISAO , TAGUCHI HIDEYUKI
IPC分类号： F02K3/11 , F02C6/02 , F02K3/12
摘要： PROBLEM TO BE SOLVED: To provide a jet engine for a supersonic aircraft capable of flying with supersonic speed while suppressing noise generated in taking-off at a low level, and capable of realizing high combustion efficiency. SOLUTION: A device is composed of a fore placed engine 2 consisting of a turbo fan engine, and an aft placed engine 4 consisting of a turbo fan or a turbo jet disposed backward the fore placed engine, bypass air of the fore placed engine 2 is boosted up by the aft placed engine 4 at the time of supersonic speed flight, and its temperature is raised so as to obtain large driving force. In taking-off, the bypass air is exhausted without boosting up and raising its temperature, and thereby, the taking-off can be operated with low noise.

4. 发明专利

JP3120113B1 失效
公开(公告)号：JP3120113B1
公开(公告)日：2000-12-25
申请号：JP31938999
申请日：1999-11-10
IPC分类号： F02K3/11 , F02C6/02 , F02K3/12

5. 发明专利

JPH0315651A DEVICE AND METHOD TO REDUCE DIFFERENTIAL PRESSURE LOAD TO GAS TURBINE ENGINE EQUIPPED WITH AUGMENTER 失效
公开(公告)号：JPH0315651A
公开(公告)日：1991-01-24
申请号：JP10321790
申请日：1990-04-20
申请人： GEN ELECTRIC
发明人： JIEFURII KAARU MEIYAA
IPC分类号： F02K3/06 , F02K3/10 , F02K3/11 , F23R3/16 , F23R3/18
摘要： PURPOSE: To improve buckling resistance of an augmenter liner by accelerating bypass air flow supplied to an augmenter as an after burner for cooling the augmenter, and leading the accelerated bypass air flow to an annular plenum by decelerating the bypass air flow. CONSTITUTION: A gas turbine engine 10 is provided with an augmenter 50 having a plurality of fuel injectors 58, which is extendedly arranged downstream a core engine and a bypass duct 44 in an outside casing 12. The augmenter 50 is composed of a combustion liner 52 for defining an annular plenum 54 between an outer casing 12 and the augmenter 50, the plenum 54 receives bypass air flow 46 for cooling. In this case, an annular flow guide 68 is formed, which is extendedly arranged from the outer casing 12 to a bypass duct 44 and the plenum 54. The guide 68 is composed of a first part 70 for defining a conversing nozzle 74 for accelerating bypass air flow 46 between an outer surface 64 of a mixer 62 and the first part 70, and a second part 76 for defining an exhale channel 80 between the guide 68 and the second part 76.

6. 发明专利

JP5375433B2 Afterburner and aircraft engine 有权
公开(公告)号：JP5375433B2
公开(公告)日：2013-12-25
申请号：JP2009192312
申请日：2009-08-21
申请人：株式会社Ihi
发明人：幸樹北川 , 潤細井
IPC分类号： F23R3/18 , F02K3/08 , F02K3/10 , F02K3/11
摘要： PROBLEM TO BE SOLVED: To suppress increase in the weight of a flame holder 37 while enhancing combustion efficiency of an afterburner 23 to reduce the weight of an aircraft engine 1. SOLUTION: A pair of tubular annulus gutters 41 capable of transmitting flame to the circumferential direction are provided on both sides of a projecting portion of each radial gutter 39 so as to nip it. The base end side of each annulus gutter 41 is partitioned by the radial gutter 39 into a flame introduction part 43 capable of introducing flame to the inner side of the annulus gutter 41 and a gas introduction part 45 capable of introducing mixed gas to the inner side of the annulus gutter 41. COPYRIGHT: (C)2011,JPO&INPIT

7. 发明专利

JP4477539B2 Apparatus for fixing the afterburner combustion chamber of the burner ring of the turbo-jet engine 有权
公开(公告)号：JP4477539B2
公开(公告)日：2010-06-09
申请号：JP2005125998
申请日：2005-04-25
申请人：スネクマ
发明人：ジヤツク・ビユネル , ジヤツク・ロツシユ
IPC分类号： F23R3/20 , F01D25/24 , F01D25/26 , F02K3/10 , F02K3/11
CPC分类号： F01D25/246 , F02K3/10 , F23R3/20

8. 发明专利

JP2006029325A Method and device for generating gas turbine engine thrust 有权
标题翻译：用于产生气体涡轮发动机的方法和装置
公开(公告)号：JP2006029325A
公开(公告)日：2006-02-02
申请号：JP2005147519
申请日：2005-05-20
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： HENRY JOHN L
IPC分类号： F02C5/02 , F02C5/12 , F02K3/06 , F02K3/11
CPC分类号： F02C5/12 , F02C5/02 , F02K3/11
摘要： PROBLEM TO BE SOLVED: To provide a method and a device for generating thrust from a gas turbine engine 10 using a pulse detonation system 100.
SOLUTION: This gas turbine engine includes a fan assembly 12, and a bypass duct 36 to send air to a core engine 23 and the pulse detonation system. This method includes a step of injecting fuel charge quantity into a pulse detonation tube 102 coupled on the radially outward from the core engine, and a step of controlling air supply quantity to flow from the fan into the pulse detonation tube through an opening 112 at an inlet end 104 of the pulse detonation tube using a rotary valve 124 disposed radially outward from the core engine.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供一种用于使用脉冲爆震系统100从燃气涡轮发动机10产生推力的方法和装置。解决方案：该燃气涡轮发动机包括风扇组件12和旁通管道 36将空气送到核心发动机23和脉冲爆震系统。该方法包括将燃料喷射量喷射到从核心发动机径向向外耦合的脉冲爆管102中的步骤，以及控制空气供给量通过开口112从风扇流入脉冲爆管的步骤脉冲爆震管的入口端104使用从核心发动机径向向外设置的旋转阀124。版权所有（C）2006，JPO＆NCIPI

9. 发明专利

JP2005320966A Device to feed air and fuel to burner ring in afterburner chamber 有权
标题翻译：在燃烧室中向燃烧器供给空气和燃料的装置
公开(公告)号：JP2005320966A
公开(公告)日：2005-11-17
申请号：JP2005125997
申请日：2005-04-25
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： BUNEL JACQUES , ROCHE JACQUES
IPC分类号： F23R3/18 , F02K3/11 , F23R3/20
CPC分类号： F23R3/20 , F02K3/11
摘要： PROBLEM TO BE SOLVED: To provide a method to solve a problem regarding an afterburner system for a turbojet in a simple, inexpensive, and effective manner.
SOLUTION: A device to feed air and fuel to a burner ring in an afterburner chamber is provided with: a plurality of flame stabilizers radially extending from an outside casing to the surroundings of the axis of the afterburner chamber; a burner ring consisting of a ring sector mounted such that the one end is substantially attached to the other end by a flame stabilizer arm; and a means to feed air and fuel to the burner ring sector. The means is extended between the burner ring and the outside casing of the afterburner chamber situated at the inside of the flame stabilizer arm.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供一种以简单，便宜和有效的方式解决涡轮喷气加燃器系统的问题的方法。解决方案：在后燃室中将空气和燃料供给到燃烧器环的装置设置有：从外壳径向延伸到加力室的轴线周围的多个火焰稳定器; 燃烧器环，其由安装成环形部件组成，使得其一端通过火焰稳定器臂基本上附接到另一端; 以及向燃烧器环部供应空气和燃料的方法。燃烧器环与位于火焰稳定器臂内侧的后燃室之间的外壳之间延伸。版权所有（C）2006，JPO＆NCIPI

10. 发明专利

JP2003206806A TURBO FAN ENGINE OF CORE ENGINE SEPARATION TYPE 审中-公开
公开(公告)号：JP2003206806A
公开(公告)日：2003-07-25
申请号：JP2002008072
申请日：2002-01-16
申请人： NAT AEROSPACE LAB
发明人： SAITO YOSHIO , ENDO MASANORI , MATSUDA YUKIO , SUGIYAMA SHICHIKEI , TAGASHIRA TAKESHI
IPC分类号： B64C29/00 , F02C1/02 , F02C3/10 , F02C3/13 , F02C3/14 , F02C6/08 , F02C7/36 , F02K3/06 , F02K3/075 , F02K3/077 , F02K3/11 , F02K3/12
摘要： PROBLEM TO BE SOLVED: To provide a silent turbo fan engine of a core engine separation type allowing reduction of noise generated by a control propelling device by using high pressure air as working fluid of a turbine for driving a control fan for controlling a body attitude. SOLUTION: The control fan 17 constituting the control propelling device 4 disposed for controlling the body attitude of the turbo fan engine 1 of the core engine separation type is driven by an air turbine 19 using as the working fluid the high pressure air compressed by a compressor 6 of the core engine 2 and supplied through a duct 10. Speed of the working fluid discharged from the control fan 17 and the air turbine 19 is lower than that of the working fluid discharged from the propelling device 3 for propelling, and is as low as that required for attitude control, so that the noise occurring from the control propelling device 4 is reduced. COPYRIGHT: (C)2003,JPO

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