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    Turbojet engine comprising an afterburner duct cooled by a variable-throughput ventilation stream
    1.
    发明授权
    Turbojet engine comprising an afterburner duct cooled by a variable-throughput ventilation stream 有权
    涡轮喷气发动机包括由可变通量通气流冷却的后燃器管道

    公开(公告)号：US07870740B2

    公开(公告)日：2011-01-18

    申请号：US11741400

    申请日：2007-04-27

    申请人： Jacques Marcel Arthur Bunel ,  Thierry Andre Emmanuel Cortes ,  Alain Pierre Page ,  Fabienne Vagner

    发明人： Jacques Marcel Arthur Bunel ,  Thierry Andre Emmanuel Cortes ,  Alain Pierre Page ,  Fabienne Vagner

    IPC分类号： F02K3/10

    CPC分类号： F02K1/822 ,  F01D25/14 ,  F01D25/26 ,  Y02T50/675

    摘要： An afterbody for a turbojet engine is disclosed. The afterbody includes an afterburner casing, a thermal protection liner, and a diaphragm-forming assembly interposed between the liner and the casing. The diaphragm-forming assembly defines a flow area which is traversed by a ventilation stream. The diaphragm-forming assembly includes two annular plates overlapping one another, each being perforated with a plurality of apertures and being mounted on the liner and the casing respectively. The apertures jointly define the flow area of the assembly. Furthermore, the assembly is designed such that the expansion of the liner causes an angular displacement of the plate with respect to the plate, leading to an increase in the size of the flow area.

    摘要翻译： 公开了涡轮喷气发动机的后身。 后箱包括加力套管，热保护衬套和插入在衬套和套管之间的隔膜成形组件。 膜片形成组件限定了由通风流穿过的流动区域。 隔膜成形组件包括彼此重叠的两个环形板，每个环形板分别穿过多个孔并分别安装在衬套和壳体上。 这些孔共同限定了组件的流动面积。 此外，组件被设计成使得衬套的膨胀导致板相对于板的角位移，导致流动面积的大小增加。

    Turbojet with protection means for a fuel injection device, an injection device and a protective plate for the turbojet
    3.
    发明授权
    Turbojet with protection means for a fuel injection device, an injection device and a protective plate for the turbojet 有权
    涡轮喷气发动机，具有用于燃料喷射装置的保护装置，喷射装置和涡轮喷气发动机的保护板

    公开(公告)号：US07600383B2

    公开(公告)日：2009-10-13

    申请号：US11175191

    申请日：2005-07-07

    申请人： Jacques Marcel Arthur Bunel ,  Jacques André Michel Roche ,  Alain Pierre Page

    发明人： Jacques Marcel Arthur Bunel ,  Jacques André Michel Roche ,  Alain Pierre Page

    IPC分类号： F02K3/10

    CPC分类号： F23R3/20 ,  F23D2211/00 ,  F23D2900/00018 ,  F23R3/283 ,  F23R3/30 ,  F23R2900/00017

    摘要： The turbojet of the invention includes a combustion chamber, a channel for heating the gas stream, where the heating channel includes at least one device for injection of fuel into the gas stream, which includes an open chamber, with a U-shaped section, having at least one wall within which extend fuel-injection means, which inject the fuel in at least one direction. It is characterised by the fact that a cooling jacket is provided in the chamber, alongside the wall forming the base of its U-section, and the fuel injection device includes protection means interposed between the fuel-injection means and the wall, in a fuel-injection direction.Thus, as a result of the invention, the fuel injection device, which is bathed in a very hot environment, is protected against thermal shocks due to the projection of colder fuel onto its walls, and its life expectancy is therefore increased.

    摘要翻译： 本发明的涡轮喷气发动机包括燃烧室，用于加热气流的通道，其中加热通道包括用于将燃料喷射到气流中的至少一个装置，其包括具有U形截面的开放室，其具有U形截面， 至少一个壁，其中延伸燃料喷射装置，其在至少一个方向上喷射燃料。 其特征在于，在所述腔室中设置有冷却套管，所述冷却套管与形成其U形部分的基部的壁相连，并且所述燃料喷射装置包括插入在所述燃料喷射装置和所述壁之间的燃料中的保护装置 注射方向。 因此，作为本发明的结果，在非常炎热的环境中沐浴的燃料喷射装置由于将更冷的燃料投射到其壁上而受到热冲击的保护，因此其预期寿命增加。

    METHOD FOR PERFORATING A WALL OF A COMBUSTION CHAMBER
    4.
    发明申请
    METHOD FOR PERFORATING A WALL OF A COMBUSTION CHAMBER 审中-公开
    用于执行燃烧室的方法

    公开(公告)号：US20130299472A1

    公开(公告)日：2013-11-14

    申请号：US13981237

    申请日：2012-01-24

    申请人： Jacques Marcel Arthur Bunel ,  Mario César De Sousa ,  Fabrice Dominguez

    发明人： Jacques Marcel Arthur Bunel ,  Mario César De Sousa ,  Fabrice Dominguez

    IPC分类号： B23K26/38 ,  F23R3/06

    摘要： A method for perforating a wall, includes calculating mechanical stresses applied on the wall for a use of the wall. The method further includes perforating an orifice in a first determined zone of the wall, the perforation being made using a tool with a cross-section dependent on the mechanical stresses calculated in the first determined zone.

    摘要翻译： 用于穿孔墙壁的方法包括计算施加在墙壁上的用于壁的应用的机械应力。 该方法还包括在壁的第一确定区域中穿孔，穿孔使用具有取决于在第一确定区域中计算的机械应力的横截面的工具来制造。

    Diffuser-guide vane connection for a centrifugal compressor
    5.
    发明授权
    Diffuser-guide vane connection for a centrifugal compressor 有权
    用于离心式压缩机的扩散器导叶连接

    公开(公告)号：US09291171B2

    公开(公告)日：2016-03-22

    申请号：US13522854

    申请日：2011-01-19

    申请人： Jacques Marcel Arthur Bunel ,  Sandrine Gandelot ,  Guy Vieillefond

    发明人： Jacques Marcel Arthur Bunel ,  Sandrine Gandelot ,  Guy Vieillefond

    IPC分类号： F04D29/44 ,  F04D29/62 ,  F01D9/04 ,  F01D25/24

    CPC分类号： F04D29/624 ,  F01D9/04 ,  F01D25/246 ,  F04D29/441 ,  F05D2250/52

    摘要： An assembly including a diffuser and an airflow rectifier at an outlet of a centrifugal compressor of a turbine engine, the diffuser being substantially in a shape of a radially positioned double annular disc, and the rectifier being a double toroidal part, arranged as an extension of the double disc of the diffuser and curved such as to divert the airflow in the downstream direction of the engine. The rectifier is attached to the diffuser by a connection positioned immediately adjacent to the contact surface of the two parts and is removable using a standard tool, excluding any other supporting mechanism.

    摘要翻译： 一种在涡轮发动机的离心式压缩机的出口处包括扩散器和气流整流器的组件，扩散器基本上是径向定位的双环形盘的形状，并且整流器是双环形部分，被布置为 扩散器的双盘并弯曲，以便在发动机的下游方向上转动气流。 整流器通过紧邻两个部件的接触表面的连接件附接到扩散器，并且使用标准工具可拆卸，不包括任何其他支撑机构。

    ANNULAR COMBUSTION CHAMBER FOR A TURBINE ENGINE INCLUDING IMPROVED DILUTION OPENINGS
    6.
    发明申请
    ANNULAR COMBUSTION CHAMBER FOR A TURBINE ENGINE INCLUDING IMPROVED DILUTION OPENINGS 有权
    涡轮发动机的环形燃烧室，包括改进的泄油口

    公开(公告)号：US20130333387A1

    公开(公告)日：2013-12-19

    申请号：US14001429

    申请日：2012-02-20

    申请人： Nicolas Christian Raymond Leblond ,  Jacques Marcel Arthur Bunel ,  Dominique Maurice Jacques Lains

    发明人： Nicolas Christian Raymond Leblond ,  Jacques Marcel Arthur Bunel ,  Dominique Maurice Jacques Lains

    IPC分类号： F23R3/00

    CPC分类号： F23R3/002 ,  F23R3/06 ,  F23R3/50 ,  F23R2900/03041 ,  F23R2900/03042 ,  Y02T50/675

    摘要： An annular wall for an annular turbine engine combustion chamber, including one annular row of dilution orifices including larger area orifices and smaller area orifices, and a multi-perforation formed from micro-perforations distributed as an upstream row, a downstream row, and at least one intermediate row interrupted by the orifices, a geometric ratio being defined as the quotient obtained by dividing the maximum spacing L between any two points on the edge of the orifice measured along a direction parallel to an axis of the wall by the maximum spacing 1 between any two points on the edge of this orifice measured along a direction perpendicular to the axis, the geometric ratio of the larger area orifices being greater than or equal to 1, and the geometric ratio of the smaller area orifices being greater than the geometric ratio of the larger area orifices.

    摘要翻译： 一种用于环形涡轮发动机燃烧室的环形壁，包括一个环形排的稀释孔，其包括较大的面积孔和较小的面积孔，以及由作为上游排，下游排和至少分布的微穿孔形成的多孔 一个由孔中断的中间行，几何比率被定义为通过将沿着平行于壁的轴线的方向测量的孔口边缘上的任何两个点之间的最大间隔L除以最大间距L而获得的商， 沿着垂直于轴线的方向测量该孔口的边缘上的任何两个点，较大面积孔口的几何比率大于或等于1，并且较小面积孔口的几何比率大于 较大面积的孔。

    COMBUSTION CHAMBER FOR AN AIRCRAFT ENGINE, AND METHOD FOR ATTACHING AN INJECTION SYSTEM IN A COMBUSTION CHAMBER OF AN AIRCRAFT ENGINE
    7.
    发明申请
    COMBUSTION CHAMBER FOR AN AIRCRAFT ENGINE, AND METHOD FOR ATTACHING AN INJECTION SYSTEM IN A COMBUSTION CHAMBER OF AN AIRCRAFT ENGINE 有权
    用于飞机发动机的燃烧室和用于在飞机发动机的燃烧室中连接喷射系统的方法

    公开(公告)号：US20130152603A1

    公开(公告)日：2013-06-20

    申请号：US13819113

    申请日：2011-08-12

    申请人： Jacques Marcel Arthur Bunel ,  Brice Arnaud Demoulin ,  Mario César De Sousa ,  Guillaume Sevi

    发明人： Jacques Marcel Arthur Bunel ,  Brice Arnaud Demoulin ,  Mario César De Sousa ,  Guillaume Sevi

    IPC分类号： F23R3/60 ,  F23R3/28

    CPC分类号： F23R3/60 ,  F23R3/14 ,  F23R3/28 ,  F23R3/283 ,  F23R2900/00017 ,  Y10T29/49323

    摘要： A combustion chamber in which the injection system is attached so as to prevent any axial motion of the injection system, the combustion chamber includes: a baffle including a tubular portion having a first upstream end surrounded by a first radially projecting collar; and an injection system including a bowl which includes a cylindrical portion inserted into the tubular portion, the cylindrical portion including a second upstream end surrounded by a second radially projecting collar, the second collar axially bearing against the first collar, wherein the combustion chamber includes a clamp which axially clamps the first and the second collars against one another, and a fastener which retains the clamp clamped on either side of the first and second collars.

    摘要翻译： 一种燃烧室，其中所述注射系统被附接以便防止所述注射系统的任何轴向运动，所述燃烧室包括：挡板，其包括管状部分，所述管状部分具有由第一径向突出的套环包围的第一上游端; 以及包括碗的注射系统，所述注射系统包括插入到所述管状部分中的圆柱形部分，所述圆柱形部分包括被第二径向突出的套环包围的第二上游端，所述第二套环轴向地抵靠所述第一套环，其中所述燃烧室包括 将第一和第二套环彼此轴向夹紧的夹具以及将夹具夹紧在第一和第二套环的任一侧上的紧固件。

    Fairing for a combustion chamber end wall
    9.
    发明授权
    Fairing for a combustion chamber end wall 有权
    用于燃烧室端壁的整流罩

    公开(公告)号：US07861531B2

    公开(公告)日：2011-01-04

    申请号：US12053091

    申请日：2008-03-21

    申请人： Jacques Marcel Arthur Bunel ,  Mario Cesar De Sousa ,  Stephane Henri Guy Touchaud

    发明人： Jacques Marcel Arthur Bunel ,  Mario Cesar De Sousa ,  Stephane Henri Guy Touchaud

    IPC分类号： F02C1/00

    CPC分类号： F23R3/10 ,  F23R3/50 ,  F23R3/60

    摘要： An annular fairing for covering the annular chamber end wall of a turbomachine combustion chamber, and in particular of an airplane turbojet. The fairing presents openings for passing fuel injectors that are supported by the chamber end wall. The fairing is subdivided into a plurality of adjacent sectors, each sector presenting inner and outer fastener edges capable of being fastened on either side of said chamber end wall. Each sector includes a lip on one of its side edges, which lip is connected to the remainder of the sector by a step, said lip being designed to over the side edge of the adjacent sector.

    摘要翻译： 用于覆盖涡轮机燃烧室的环形室端壁的环形整流罩，特别是飞机涡轮喷气发动机。 整流罩提供用于通过由腔室端壁支撑的燃料喷射器的开口。 整流罩细分为多个相邻的扇区，每个扇区呈现能够紧固在所述腔室端壁两侧的内部和外部紧固件边缘。 每个扇区在其一个侧边缘上包括唇缘，该唇缘通过台阶连接到扇形的其余部分，所述唇缘设计成在相邻扇区的侧边缘之上。