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1. 发明授权

US07721545B2 Device for injecting a mixture of air and fuel, combustion chamber and turbomachine both equipped with such a device 有权
标题翻译：用于喷射空气和燃料，燃烧室和涡轮机的混合物的装置，两者都装备有这种装置
公开(公告)号：US07721545B2
公开(公告)日：2010-05-25
申请号：US11692441
申请日：2007-03-28
申请人： Alain Cayre , Michel Andre Albert Desaulty , Nicolas Pommier
发明人： Alain Cayre , Michel Andre Albert Desaulty , Nicolas Pommier
IPC分类号： F23R3/04
CPC分类号： F23R3/60 , F23R3/14 , F23R3/28 , Y02T50/675
摘要： The invention relates to a device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine where the supply of air is improved. The invention relates more particularly to a new type of sliding bushing.
摘要翻译：本发明涉及一种用于将空气和燃料的混合物喷射到提供空气供应的涡轮机的燃烧室中的装置。本发明更具体地涉及一种新型的滑动衬套。

2. 发明授权

US08047777B2 Turbomachine diffuser 有权
标题翻译：涡轮机扩散器
公开(公告)号：US08047777B2
公开(公告)日：2011-11-01
申请号：US12190105
申请日：2008-08-12
申请人： Patrice Andre Commaret , Michel Andre Albert Desaulty , Romain Nicolas Lunel , Pascale Rollet
发明人： Patrice Andre Commaret , Michel Andre Albert Desaulty , Romain Nicolas Lunel , Pascale Rollet
IPC分类号： F04D29/44 , F04D29/54 , F03B1/00 , F03B11/02 , F03B5/00
CPC分类号： F02C3/08 , F02C3/14 , F04D29/444 , F05D2250/71
摘要： A turbomachine comprising an annular combustion chamber (40) with injection orifices (44); a centrifugal compressor (10) having a centrifugal downstream stage and an annular diffuser (20) comprising: a radially-oriented upstream portion (21)with diffusion passages (22) connected to the outlet of the compressor and an elbow-shaped intermediate portion (24)and a downstream portion (25) comprising a series of flow-straightening vanes (26) and inclined relative to the axis (A) of the turbomachine. In the section plane containing the axis (A) of the turbomachine and passing via the center (C) of one of said injection orifices (44), the curvilinear abscissa distance along a flow line (L) between the middle (0) of the flow path at the trailing edges of the flow-straightening vanes (26) and said center (C) is greater than or equal to three times the height (h) of said flow path.
摘要翻译：一种涡轮机，包括具有喷射孔（44）的环形燃烧室（40）; 具有离心下游级的离心式压缩机（10）和环形扩散器（20），包括：径向定向的上游部分（21），其具有连接到压缩机出口的扩散通道（22）和肘形中间部分 24）和包括一系列流动矫直叶片（26）并相对于涡轮机的轴线（A）倾斜的下游部分（25）。在包含涡轮机的轴线（A）并且经过所述喷射孔（44）中的一个的中心（C）的截面中，沿着沿着所述喷嘴的中间（0）之间的流动线（L）的曲线横坐标距离在流动矫正叶片（26）和所述中心（C）的后缘处的流动路径大于或等于所述流动路径的高度（h）的三倍。

3. 发明申请

US20090047127A1 TURBOMACHINE DIFFUSER 有权
标题翻译：涡轮增压器
公开(公告)号：US20090047127A1
公开(公告)日：2009-02-19
申请号：US12190105
申请日：2008-08-12
申请人： Patrice Andre Commaret , Michel Andre Albert Desaulty , Romain Nicolas Lunel , Pascale Rollet
发明人： Patrice Andre Commaret , Michel Andre Albert Desaulty , Romain Nicolas Lunel , Pascale Rollet
IPC分类号： F01D9/02
CPC分类号： F02C3/08 , F02C3/14 , F04D29/444 , F05D2250/71
摘要： A turbomachine comprising: an annular combustion chamber (40) with injection orifices (44); a centrifugal compressor (10) having a centrifugal downstream stage; and an annular diffuser (20) comprising: a radially-oriented upstream portion (21) with diffusion passages (22) connected to the outlet of the compressor; an elbow-shaped intermediate portion (24); and a downstream portion (25) comprising a series of flow-straightening vanes (26) and inclined relative to the axis (A) of the turbomachine. In the section plane containing the axis (A) of the turbomachine and passing via the center (C) of one of said injection orifices (44), the curvilinear abscissa distance along a flow line (L) between the middle (O) of the flow path at the trailing edges of the flow-straightening vanes (26) and said center (C) is greater than or equal to three times the height (h) of said flow path.
摘要翻译：一种涡轮机，包括：具有喷射孔（44）的环形燃烧室（40）; 具有离心下游级的离心式压缩机（10）和环形扩散器（20），包括：径向定向的上游部分（21），其具有连接到压缩机出口的扩散通道（22）肘形中间部分（24）; 以及包括一系列流动整流叶片（26）并相对于涡轮机的轴线（A）倾斜的下游部分（25）。在包含涡轮机的轴线（A）并且经过所述喷射孔（44）中的一个的中心（C）的截面中，沿着沿着所述喷射孔（44）的中间（O）的流线（L）的曲线横坐标距离在流动矫正叶片（26）和所述中心（C）的后缘处的流动路径大于或等于所述流动路径的高度（h）的三倍。

4. 发明授权

US5937653A Reduced pollution combustion chamber having an annular fuel injector 失效
标题翻译：减少污染燃烧室具有环形燃料喷射器
公开(公告)号：US5937653A
公开(公告)日：1999-08-17
申请号：US884668
申请日：1997-06-27
申请人： Jean-Paul Daniel Alary , Stephane Jean-Marie Courtet , Michel Andre Albert Desaulty
发明人： Jean-Paul Daniel Alary , Stephane Jean-Marie Courtet , Michel Andre Albert Desaulty
IPC分类号： F23R3/10 , F23R3/28 , F23R3/50 , F02C3/06
CPC分类号： F23R3/10 , F23R3/28 , F23R3/50 , Y02T50/675
摘要： An annular combustion chamber is disclosed for use in a gas turbine engine, the combustion chamber having an axis of symmetry, an inner annular wall, an outer annular wall, and a forward end extending between the inner and outer wall to form boundaries for the combustion chamber. The forward end of the combustion chamber has an inner ring member extending about the axis of symmetry and an outer ring member extending about the axis of symmetry and radially spaced from the inner ring member, the inner and outer ring members forming inner and outer boundaries of an annular chamber that diverges in a rearward direction. The inner and outer ring members are interconnected by a plurality of circumferentially spaced apart spacers so as to form a plurality of arcuate openings between adjacent spacers. A plurality of fuel injector assemblies are associated with the forward end of the combustion chamber, each fuel injector assembly comprising an arcuate injection manifold located in an arcuate member, in turn, located in one of the plurality of arcuate openings so as to divide the arcuate opening into an inner annular space and an outer annular space, the injection manifold having an inner array of injection orifices to inject fuel into the inner annular space, and an outer array of injection orifices to inject fuel into the outer annular space. The inner and outer ring members have a plurality of air swirlers located forwardly of the fuel injection orifices to direct air flows into the inner and outer annular spaces in counter-rotation directions around the axis of symmetry. The injection orifices are oriented so as to direct fuel into the inner and outer annular spaces generally in the same direction as the air flow in the respective annular space.
摘要翻译：公开了一种用于燃气涡轮发动机的环形燃烧室，燃烧室具有对称轴线，内部环形壁，外部环形壁和在内壁和外壁之间延伸以形成燃烧边界的前端房间。燃烧室的前端具有围绕对称轴延伸的内环构件和围绕对称轴线延伸并且与内环构件径向间隔开的外环构件，内圈和外圈构件形成内圈和外边界环形室沿向后方向分叉。内圈和外圈构件通过多个周向间隔开的间隔件相互连接，以便在相邻间隔件之间形成多个弧形开口。多个燃料喷射器组件与燃烧室的前端相关联，每个燃料喷射器组件包括位于弧形构件中的弓形喷射歧管，其又位于多个弓形开口中的一个中，以便将弧形开口到内部环形空间和外部环形空间中，所述注入歧管具有注入孔的内部阵列以将燃料喷射到内部环形空间中，以及外部阵列的注入孔以将燃料喷射到外部环形空间中。内圈和外圈构件具有位于燃料喷射孔前方的多个空气旋流器，用于引导空气流绕围绕对称轴线的反向旋转方向的内外环形空间流动。喷射孔被定向成将燃料引导到内外环形空间中，大体上与相应的环形空间中的空气流相同。

5. 发明授权

US5797266A Device for actively controlling combustion instabilities and for decoking a fuel injector 失效
标题翻译：用于主动控制燃烧不稳定性和用于对燃料喷射器进行除焦的装置
公开(公告)号：US5797266A
公开(公告)日：1998-08-25
申请号：US552015
申请日：1995-11-02
申请人： Jean-Marie Brocard , Jean-Yves Capelle , Michel Andre Albert Desaulty , Jean-Paul Perrin , Alain Michel Varizat
发明人： Jean-Marie Brocard , Jean-Yves Capelle , Michel Andre Albert Desaulty , Jean-Paul Perrin , Alain Michel Varizat
IPC分类号： G01L9/08 , F02C7/22 , F02C7/232 , F02C9/26 , F02C9/28 , F02D11/10 , F02M65/00 , F23D11/38 , F23M99/00 , F23N5/16
CPC分类号： F23D11/386 , F02C7/22 , F02C9/26 , F23M20/005 , F23N5/16 , F23R2900/00013 , F23R2900/00014 , Y02T50/677
摘要： A device for actively controlling combustion instabilities and for decokinguel injectors comprises at least one detector for measuring pressure fluctuations in a combustion or afterburner chamber, means for processing the signal output by the detector and providing, in turn, a control voltage, and at least one piezoelectric device which is disposed in a hydraulic line including a fuel injector for the supply of fuel to the combustion or afterburner chamber and which is responsive to the control voltage to generate pulses in the flow of fuel from the outlet of the fuel injector.
摘要翻译：用于主动控制燃烧不稳定性和用于对燃料喷射器进行除焦的装置包括至少一个用于测量燃烧室或后燃室中的压力波动的检测器，用于处理由检测器输出的信号的装置，以及至少提供一个控制电压一个压电装置，其设置在包括燃料喷射器的液压管线中，用于向燃烧室或后燃室提供燃料，并且响应于控制电压在燃料喷射器的出口处产生燃料流中的脉冲。

6. 发明授权

US07805943B2 Shroud for a turbomachine combustion chamber 有权
标题翻译：用于涡轮机燃烧室的护罩
公开(公告)号：US07805943B2
公开(公告)日：2010-10-05
申请号：US11275859
申请日：2006-02-01
申请人： Michel Andre Albert Desaulty , Michel Pierre Cazalens , Olivier Kreder , Alain Cayre
发明人： Michel Andre Albert Desaulty , Michel Pierre Cazalens , Olivier Kreder , Alain Cayre
IPC分类号： F02C7/20
CPC分类号： F23R3/10 , F23R3/002
摘要： A shroud for a combustion chamber bottom designed to cover fuel injectors is provided with drillings on at least one of its sides to open up the cavity within the shroud and reduce noise that it produces and combustion instabilities. The drillings also have the effect of reducing instabilities and non-uniformity of the airflow around the shroud.
摘要翻译：设计用于覆盖燃料喷射器的用于燃烧室底部的护罩在其至少一侧上设置有钻孔，以打开护罩内的空腔并减少其产生的噪音和燃烧不稳定性。钻孔还具有减少护罩周围气流的不稳定性和不均匀性的效果。

7. 发明授权

US6035645A Aerodynamic fuel injection system for a gas turbine engine 失效
标题翻译：用于燃气涡轮发动机的气动燃料喷射系统
公开(公告)号：US6035645A
公开(公告)日：2000-03-14
申请号：US939084
申请日：1997-09-26
申请人： Mehdi Bensaadi , Michel Andre Albert Desaulty , Sebastien Pierre Jean Pitrou , Pierre Marie Victor Emile Schroer
发明人： Mehdi Bensaadi , Michel Andre Albert Desaulty , Sebastien Pierre Jean Pitrou , Pierre Marie Victor Emile Schroer
IPC分类号： F02C7/232 , F02C7/22 , F23R3/14 , F23R3/22 , F23R3/26 , F23R3/28
CPC分类号： F23R3/14 , Y02T50/675
摘要： A fuel injection system is disclosed for a gas turbine engine having a fuel injector issuing a primary fuel flow during all operating modes of the gas turbine engine and a secondary fuel flow when operating parameters of the gas turbine engine exceed predetermined values. The fuel injection system includes a first air swirler, a second air swirler located rearwardly of the first air swirler and a venturi having a wall with a converging-diverging inner wall surface forming a venturi throat, the venturi being located such that the wall separates first and second air flows issuing from the first and second air swirlers and such that the primary fuel flow emanating from the fuel injector in a conical configuration does not impact against the inner wall surface of the venturi.
摘要翻译：公开了一种用于燃气涡轮发动机的燃料喷射系统，其具有在燃气涡轮发动机的所有运行模式期间发出主燃料流的燃料喷射器和当燃气涡轮发动机的运行参数超过预定值时的次级燃料流。燃料喷射系统包括第一空气旋流器，位于第一空气旋流器后方的第二空气旋流器和具有形成文丘里喉部的会聚发散内壁表面的壁的文氏管，文丘里管被定位成使得壁分隔开以及从第一和第二空气旋流器发出的第二空气流，并且使得以锥形构造从燃料喷射器发出的主燃料流不会冲击文丘里管的内壁表面。

8. 发明授权

US07908865B2 Device for injecting a mixture of air and fuel, and combustion chamber and turbomachine provided with such a device 有权
标题翻译：用于喷射空气和燃料的混合物的装置，以及具有这种装置的燃烧室和涡轮机
公开(公告)号：US07908865B2
公开(公告)日：2011-03-22
申请号：US11768556
申请日：2007-06-26
申请人： Alain Cayre , Michel Andre Albert Desaulty , Denis Jean Maurice Sandelis
发明人： Alain Cayre , Michel Andre Albert Desaulty , Denis Jean Maurice Sandelis
IPC分类号： F23R3/14 , F23R3/50
CPC分类号： F23R3/14 , Y02T50/675
摘要： A device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine is disclosed. The injection device includes a novel sliding bushing and a novel annular cup for retaining the sliding bushing, making it possible to improve the air feed of the injection device.
摘要翻译：公开了一种用于将空气和燃料的混合物喷射到涡轮机的燃烧室中的装置。注射装置包括新颖的滑动衬套和用于保持滑动衬套的新型环形杯，使得可以改善注射装置的空气供给。

9. 发明授权

US07823387B2 Gas turbine engine diffuser and combustion chamber and gas turbine engine comprising same 有权
标题翻译：燃气涡轮发动机扩散器和包括其的燃烧室和燃气涡轮发动机
公开(公告)号：US07823387B2
公开(公告)日：2010-11-02
申请号：US12018585
申请日：2008-01-23
申请人： Patrice Andre Commaret , Michel Andre Albert Desaulty , Romain Nicolas Lunel , Denis Jean Maurice Sandelis
发明人： Patrice Andre Commaret , Michel Andre Albert Desaulty , Romain Nicolas Lunel , Denis Jean Maurice Sandelis
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/26 , F02C3/14 , F23R3/04 , F23R3/50 , Y02T50/675
摘要： A gas turbine engine diffuser defined between an external casing and an internal casing of the engine and supplied with air via an upstream annular diffuser duct is disclosed. The diffuser includes a combustion chamber of the convergent type, forming an external annular duct with the external casing and an internal annular duct with the internal casing, and a cowling partially closing off the external annular duct. The cowling is positioned toward the closed end of the combustion chamber.
摘要翻译：公开了一种燃气涡轮发动机扩散器，其限定在发动机的外部壳体和内部壳体之间，并且经由上游环形扩散器管道供给空气。扩散器包括会聚型的燃烧室，形成具有外部壳体的外部环形管道和具有内部壳体的内部环形管道，并且整流罩部分地封闭外部环形管道。整流罩朝向燃烧室的封闭端。

10. 发明申请

US20080245053A1 GAS TURBINE ENGINE DIFFUSER AND COMBUSTION CHAMBER AND GAS TURBINE ENGINE COMPRISING SAME 有权
标题翻译：气体涡轮发动机发动机和燃烧室和包含其的燃气涡轮发动机
公开(公告)号：US20080245053A1
公开(公告)日：2008-10-09
申请号：US12018585
申请日：2008-01-23
申请人： Patrice Andre COMMARET , Michel Andre Albert Desaulty , Romain Nicolas Lunel , Denis Jean Maurice Sandelis
发明人： Patrice Andre COMMARET , Michel Andre Albert Desaulty , Romain Nicolas Lunel , Denis Jean Maurice Sandelis
IPC分类号： F02K3/02
CPC分类号： F23R3/26 , F02C3/14 , F23R3/04 , F23R3/50 , Y02T50/675
摘要： The present invention relates to a gas turbine engine diffuser (30) defined between an external casing (32) and an internal casing (34) of said engine and supplied with air via an upstream annular diffuser duct (36), comprising a combustion chamber (10) of the convergent type, forming an external annular duct (28) with the external casing (32) and an internal annular duct with the internal casing (34), which diffuser comprises a cowling partially closing off the external annular duct. More specifically, the cowling is positioned toward the closed end of the combustion chamber.
摘要翻译：本发明涉及一种限定在所述发动机的外壳（32）和内壳（34）之间的燃气轮机发动机扩散器（30），并且经由上游环形扩散器管道（36）供应空气，所述上游环形扩散器管道包括燃烧室形成会聚型的10），与外部壳体（32）形成外部环形管道（28）和具有内部壳体（34）的内部环形管道，该扩散器包括部分地封闭外部环形管道的整流罩。更具体地，整流罩定位成朝向燃烧室的封闭端。

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