公开(公告)号：US5592819A

公开(公告)日：1997-01-14

申请号：US400574

申请日：1995-03-08

申请人： Denis R. H. Ansart ,  Patrice A. Commaret ,  Etienne S. R. David ,  Michel A. A. Desaulty ,  Bruno M. M. Quinquenneau ,  Denis Sandelis

发明人： Denis R. H. Ansart ,  Patrice A. Commaret ,  Etienne S. R. David ,  Michel A. A. Desaulty ,  Bruno M. M. Quinquenneau ,  Denis Sandelis

IPC分类号： F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/32 ,  F23R3/34

CPC分类号： F23R3/12 ,  F23R3/286 ,  F23R3/32 ,  Y02T50/675

摘要： A pre-mixing injection system to feed a fuel/air mixture to a combustion zone in a turbojet engine combustion chamber is disclosed having a pre-mixing tube defining a convergent pre-mixing zone and a diverging intermediate zone between the fuel and air injection devices, and the combustion zone of the combustion chamber. The convergent pre-mixing zone has an inlet adjacent to the fuel injector and air swirlers to accept the fuel/air mixture into the pre-mixing tube. The pre-mixing zone converges in a direction from the inlet to an outlet which is in communication with the inlet of the divergent intermediate zone. The divergent intermediate zone has an outlet which is, in turn, in communication with the combustion zone of the turbojet engine combustion chamber. The divergent intermediate zone is defined by an inner wall and an outer wall spaced from the inner wall so as to define a generally frusto-conical chamber between them. The outer wall has a plurality of cooling holes to enable cooling air to pass through the outer wall into cooling contact with the inner wall. The frusto-conical chamber has a downstream evacuation passage to allow cooling air to pass from the frusto-conical chamber.

摘要翻译： 公开了一种用于将燃料/空气混合物供给到涡轮喷气发动机燃烧室中的燃烧区域的预混合喷射系统，其具有限定会聚预混合区域的预混合管和燃料和空气喷射装置之间的发散中间区域 和燃烧室的燃烧区域。 会聚预混合区域具有与燃料喷射器相邻的入口和空气旋流器以将燃料/空气混合物接收到预混合管中。 预混合区在从入口到与发散中间区的入口连通的出口的方向会聚。 发散中间区域具有出口，该出口又与涡轮喷气发动机燃烧室的燃烧区域连通。 发散中间区由内壁和与内壁隔开的外壁限定，以便在它们之间限定一个大致截头圆锥形的室。 外壁具有多个冷却孔，以使冷却空气能够通过外壁与内壁冷却接触。 截头圆锥室具有下游排气通道，以允许冷却空气从截头圆锥室通过。

公开(公告)号：US6029455A

公开(公告)日：2000-02-29

申请号：US919353

申请日：1997-08-28

申请人： Denis Sandelis

发明人： Denis Sandelis

IPC分类号： F23R3/00 ,  F02C1/00 ,  F02G3/00 ,  F23R3/06

CPC分类号： F23R3/002

摘要： A combustion chamber is disclosed for a turbojet engine in which the combustion chamber has a forward intake, a rear exit and a perforated casing extending between the intake and exit. The combustion chamber also has at least two rows of insulating tiles arrayed on the casing in forward and rear rows with both rows extending circumferentially around the inner surface of the casing bounding the combustion chamber. Each rear tile has a forward edge portion with a sloping wall and each forward tile has a tapered rear edge portion overlapping the forward edge portion with a clearance therebetween such that the tampered rear edge portion and the sloping wall bound a slot opening into the combustion chamber and slanting towards the rear of the combustion chamber to facilitate the formation of an air cooling film on inner surfaces of the tiles. The cooling air passes through the perforated casing, into the space between the casing and the tiles, through the clearance between the tiles and through the slot into the combustion chamber.

摘要翻译： 公开了一种用于涡轮喷气发动机的燃烧室，其中燃烧室具有前进气口，后出口和在进气口和出口之间延伸的穿孔壳体。 燃烧室还具有排列在前后两排的壳体上的至少两排绝缘砖，两排沿周向围绕着围绕燃烧室的壳体的内表面延伸。 每个后瓦片具有带有倾斜壁的前边缘部分，并且每个前瓦片具有与前边缘部分重叠的锥形后边缘部分，其间具有间隙，使得被篡改的后边缘部分和倾斜壁限定开口进入燃烧室 并且朝向燃烧室的后部倾斜以便于在瓷砖的内表面上形成空气冷却膜。 冷却空气穿过穿孔的壳体，穿过壳体和瓦片之间的空间，穿过瓦片之间的间隙并通过狭槽进入燃烧室。

公开(公告)号：US20070068166A1

公开(公告)日：2007-03-29

申请号：US11527498

申请日：2006-09-27

申请人： Claude Gautier ,  Denis Sandelis

发明人： Claude Gautier ,  Denis Sandelis

IPC分类号： F23R3/02

CPC分类号： F02C3/14 ,  F23R3/002 ,  F23R3/283 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00012

摘要： Device (48) for guiding an element in an orifice in a wall of a turbomachine combustion chamber (10), comprising a ring (50) and a bush (52), the ring being traversed axially by the element and comprising an external annular rim (60) guided transversely in an internal annular channel (52) of the bush, the ring and the bush delimiting around the element a cylindrical annular passage (76) opening into the chamber, air circulation means being formed in the ring and/or in the bush and distributed about their axis so as to establish an air circulation in the cylindrical passage from the outside of the combustion chamber toward the inside.

摘要翻译： 用于引导涡轮机燃烧室（10）的壁中的孔中的元件的装置（48），包括环（50）和衬套（52），所述环由所述元件轴向地横向包括外部环形边缘 （60）在衬套的内部环形通道（52）中横向引导，所述环和衬套围绕所述元件限定通向所述室的圆柱形环形通道（76），空气循环装置形成在所述环中和/ 衬套并围绕其轴线分布，以便在从燃烧室的外部朝向内部的圆柱形通道中建立空气循环。

公开(公告)号：US20070125085A1

公开(公告)日：2007-06-07

申请号：US11566330

申请日：2006-12-04

申请人： Patrice Commaret ,  Denis Sandelis ,  Denis Trahot

发明人： Patrice Commaret ,  Denis Sandelis ,  Denis Trahot

IPC分类号： F23R3/14

CPC分类号： F23R3/283 ,  F23R3/14 ,  Y02T50/675

摘要： The invention applies to the field of turbomachines and relates to a novel device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine. The injection device has symmetry of revolution about an axis (33) and comprises, arranged from upstream to downstream in the gas flow direction, radial swirl inducers (42, 43) of outside diameter D2, a bowl (30) spaced axially from the radial swirl inducers (42, 43), and a support ring (50) for supporting the injection device, which is arranged around the bowl (30). The bowl (30) has a cylindrical wall (32) extended by a flared wall (31), the flared wall (31) being provided with air intake holes (34). This novel device is noteworthy in that the support ring (50) comprises, arranged from upstream to downstream in the gas flow direction, a first cylindrical portion (51) of outside diameter D3, connected to a second cylindrical portion (52) of outside diameter D4 spaced axially from the first cylindrical portion (51), the first cylindrical portion (51) being connected to the cylindrical wall (32) of the bowl (30) by a plurality of support tabs (55).

摘要翻译： 本发明适用于涡轮机领域，涉及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新型装置。 注射装置具有围绕轴线（33）的旋转对称性，并且包括从气流方向的上游到下游设置的外径为D 2的径向涡流引导器（42,43），与所述外径径向轴向间隔开的碗（30） 径向涡旋诱导器（42,43）和用于支撑注射装置的支撑环（50），其布置在所述碗（30）周围。 碗（30）具有由扩口壁（31）延伸的圆柱形壁（32），扩口壁（31）设有进气孔（34）。 这种新颖的装置是值得注意的，因为支撑环（50）包括从气流方向的上游到下游布置的外径D 3的第一圆柱形部分（51），其连接到外部的第二圆柱形部分（52） 直径D 4与第一圆柱形部分（51）轴向间隔开，第一圆柱形部分（51）通过多个支撑凸片（55）连接到碗状物（30）的圆柱形壁（32）。

公开(公告)号：US5941076A

公开(公告)日：1999-08-24

申请号：US898403

申请日：1997-07-22

申请人： Denis Sandelis

发明人： Denis Sandelis

IPC分类号： F02C7/00 ,  F02C7/18 ,  F23R3/00 ,  F23R3/10 ,  F23R3/26 ,  F23R3/42

CPC分类号： F23R3/10 ,  F23R3/002 ,  F23R3/26 ,  Y02T50/67 ,  Y02T50/675

摘要： A combustion chamber is disclosed for a gas turbine engine having a feederowl interposed between the forward end wall of the combustion chamber and an associated air and fuel injection device, the feeder bowl having a generally annular configuration with spaced apart outer and inner walls forming a chamber. A baffle is formed integrally with the feeder bowl and extends outwardly from a merging zone in a direction generally parallel to the forward end wall of the combustion chamber. The outer wall of the feeder bowl has a plurality of air intake orifices communicating with the chamber and located adjacent to the merging zone. The inner wall of the feeder bowl has a plurality of first and second air outlet orifices, both communicating with the chamber and the second air outlet orifices being spaced from the first air outlet orifices.

摘要翻译： 公开了一种用于燃气涡轮发动机的燃烧室，其具有插入在燃烧室的前端壁和相关联的空气和燃料喷射装置之间的进料碗，所述进料碗具有大致环形的构造，其间隔开的外壁和内壁形成 房间。 挡板与进料碗一体地形成，并且在大致平行于燃烧室的前端壁的方向上从合流区向外延伸。 进料碗的外壁具有多个与室连通并位于合并区附近的进气口。 进料碗的内壁具有多个第一和第二空气出口孔，两个第一和第二空气出口孔都与室连通，而第二空气出口孔与第一空气出口孔隔开。

公开(公告)号：US20070113556A1

公开(公告)日：2007-05-24

申请号：US11560151

申请日：2006-11-15

申请人： Romain Biebel ,  Claude Gautier ,  Denis Sandelis

发明人： Romain Biebel ,  Claude Gautier ,  Denis Sandelis

IPC分类号： F23R3/14 ,  F23R3/28

CPC分类号： F23R3/60 ,  F23R3/10 ,  F23R3/283 ,  F23R2900/00012 ,  F23R2900/03044 ,  Y02T50/675

摘要： The invention relates to the field of combustion chambers for aviation turbomachines. It relates to a combustion chamber having a chamber end wall that presents a plurality of air and fuel injector devices, each of the devices comprising a bowl and a deflector mounted on a main axis forming a heat shield disposed around the bowl which flares in the gas flow direction and possesses an annular portion, the interface between the bowl and the deflector being situated on this annular portion, at least a portion of said interface being situated towards the end of the annular portion that is downstream in the gas flow direction, such that an annular cavity is defined between the deflector and the downstream annular portion of the interface. First bowl holes are formed in the annular portion to open out in register with the edge of the chamber end wall that is in contact with the deflector in order to sustain a flow of air from upstream to downstream in the annular cavity.

摘要翻译： 本发明涉及用于航空涡轮机的燃烧室领域。 它涉及具有腔室端壁的燃烧室，其具有多个空气和燃料喷射器装置，每个装置包括安装在主轴上的碗和偏转器，所述导流板设置在围绕碗状物放置在气体中的隔热罩 流动方向并且具有环形部分，碗和偏转器之间的界面位于该环形部分上，所述界面的至少一部分朝向在气流方向下游的环形部分的端部定位，使得 在导流器和界面的下游环形部分之间限定了环形空腔。 第一碗孔形成在环形部分中，以与腔室端壁的与导流板接触的边缘对齐地开口，以便在环形空腔中从上游到下游维持空气流。

公开(公告)号：US07328582B2

公开(公告)日：2008-02-12

申请号：US10529583

申请日：2004-06-18

申请人： Denis Sandelis ,  Yves Salan

发明人： Denis Sandelis ,  Yves Salan

IPC分类号： F23R3/04

CPC分类号： F23R3/50 ,  F23R3/002 ,  F23R3/10 ,  F23R2900/03041 ,  F23R2900/03042

摘要： An annular turbine engine combustion chamber configured so that in an axial half-section, values of first acute angles formed between a line that is effectively the median of the half-section located between an external axial wall and an internal axial wall, and the principal directions, in this half-section, of the holes in an external portion of a chamber base, decrease as a function of the distance between the holes and this line that is effectively the median. Further, values of second acute angles formed between the line that is effectively the median and the principal directions, in this half-section, of the holes in an internal portion of the chamber base, decrease as a function of the distance between the holes and this line that is effectively the median.

摘要翻译： 环形涡轮发动机燃烧室被构造成使得在轴向半部分中，形成在实际上位于外部轴向壁和内部轴向壁之间的半部分的中间的线之间的第一锐角值与主体 在该半部分中，腔室底部的外部部分中的孔的方向作为孔和该线之间的距离的函数而减小，该线实际上是中间值。 此外，在该基部的内部部分中的孔的该半部分中的实际上是中间的线和主要方向之间形成的第二锐角的值作为孔与第二锐角之间的距离的函数而减小， 这条线实际上是中位数。

公开(公告)号：US20070056289A1

公开(公告)日：2007-03-15

申请号：US10529583

申请日：2004-06-18

申请人： Denis Sandelis ,  Yves Salan

发明人： Denis Sandelis ,  Yves Salan

IPC分类号： F23R3/00

CPC分类号： F23R3/50 ,  F23R3/002 ,  F23R3/10 ,  F23R2900/03041 ,  F23R2900/03042

摘要： An annular turbine engine combustion chamber configured so that in an axial half-section, values of first acute angles formed between a line that is effectively the median of the half-section located between an external axial wall and an internal axial wall, and the principal directions, in this half-section, of the holes in an external portion of a chamber base, decrease as a function of the distance between the holes and this line that is effectively the median. Further, values of second acute angles formed between the line that is effectively the median and the principal directions, in this half-section, of the holes in an internal portion of the chamber base, decrease as a function of the distance between the holes and this line that is effectively the median.

摘要翻译： 环形涡轮发动机燃烧室被构造成使得在轴向半部分中，形成在实际上位于外部轴向壁和内部轴向壁之间的半部分的中间的线之间的第一锐角值与主体 在该半部分中，腔室底部的外部部分中的孔的方向作为孔和该线之间的距离的函数而减小，该线实际上是中间值。 此外，在该基部的内部部分中的孔的该半部分中的实际上是中间的线和主要方向之间形成的第二锐角的值作为孔与第二锐角之间的距离的函数而减小， 这条线实际上是中位数。

公开(公告)号：US06820425B2

公开(公告)日：2004-11-23

申请号：US10300817

申请日：2002-11-21

申请人： Etienne David ,  Marion Michau ,  José Rodrigues ,  Denis Sandelis ,  Alain Tiepel

发明人： Etienne David ,  Marion Michau ,  José Rodrigues ,  Denis Sandelis ,  Alain Tiepel

IPC分类号： F02C722

CPC分类号： F23R3/286 ,  F23D11/107 ,  F23R3/14

摘要： A system for injecting an air/fuel mixture into a combustion chamber of a turbomachine, the system having an injector comprising: an axial internal volume opening out at one end via an axial outlet for the air/fuel mixture; a first fuel feed stage having a plurality of first fuel feed orifices which open out into the internal volume, which are distributed around an axis of the injector, and which are connected by fuel feed channels to an inlet for admitting fuel into the injector; and at least one air feed channel which opens out into the internal volume and which is connected to an inlet for admitting air into the injector. The injector further comprises at least one second fuel feed stage with a plurality of second fuel feed orifices which open out into the internal volume, which are distributed around the axis of the injector, and which are connected to said inlet for admitting fuel into the injector via fuel feed channels which coincide at least in part with the fuel feed channels of said first stage.

摘要翻译： 一种用于将空气/燃料混合物喷射到涡轮机的燃烧室中的系统，所述系统具有喷射器，所述喷射器包括：轴向内部容积，其一端通过空气/燃料混合物的轴向出口开口; 第一燃料供给台具有多个第一燃料供给孔，该第一燃料供给孔向内部容积开放，该第一燃料供给孔分布在喷射器的轴线周围，并且通过燃料供给通道连接到用于将燃料引入喷射器的入口; 以及至少一个通向内部容积的空气供给通道，并连接到用于将空气引入喷射器的入口。 喷射器还包括至少一个第二燃料供给台，其具有多个第二燃料供给孔，该多个第二燃料供给孔开放到内部容积中，该第二燃料供给孔分布在喷射器的轴线周围，并且连接到所述入口，以将燃料引入喷射器 通过至少部分地与所述第一级的燃料供给通道重合的燃料供给通道。

公开(公告)号：US5577386A

公开(公告)日：1996-11-26

申请号：US493206

申请日：1995-06-20

申请人： Jean-Paul D. Alary ,  Guy D'Agostino ,  Henry R. Leclerc ,  Denis Sandelis ,  Pierre M. V. E. Schroer

发明人： Jean-Paul D. Alary ,  Guy D'Agostino ,  Henry R. Leclerc ,  Denis Sandelis ,  Pierre M. V. E. Schroer

IPC分类号： F02C7/16 ,  F23D11/36 ,  F23R3/28 ,  F23R3/34 ,  B05B15/00 ,  F02C3/14

CPC分类号： F23D11/36

摘要： The present invention relates to a system for cooling a high power fuel injector of a dual fuel injector wherein the system comprises a first fuel supply circuit having a first conduit connecting a fuel feed supply and the high power fuel injector, the first conduit having a terminal end adjacent to a distal end of the high power fuel injector, and a second conduit connecting the terminal end of the first conduit to the low power fuel injector such that all of the fuel supplied to the low power injector first passes through the high power fuel injector. The system also has a second fuel supply circuit, separate from the first fuel supply circuit, which comprises a third conduit connecting the fuel feed supply and the fuel injection orifices of the high power fuel injector so as to supply fuel to the fuel injection orifices.

摘要翻译： 本发明涉及一种用于冷却双燃料喷射器的大功率燃料喷射器的系统，其中该系统包括第一燃料供应回路，该第一燃料供应回路具有连接燃料供给源和大功率燃料喷射器的第一管道，该第一管道具有一个终端 并且连接第一导管的末端与低功率燃料喷射器的第二导管，使得供应到低功率喷射器的所有燃料首先通过高功率燃料 注射器。 该系统还具有与第一燃料供应回路分开的第二燃料供应回路，该第二燃料供应回路包括连接燃料供给供应源和大功率燃料喷射器的燃料喷射孔的第三管道，以向燃料喷射孔供应燃料。