公开(公告)号：US09599344B2

公开(公告)日：2017-03-21

申请号：US14070698

申请日：2013-11-04

Applicant: SNECMA

Inventor： Jacques Marcel Arthur Bunel ,  Gilles Ulryck

IPC: F23R3/60 ,  F23R3/28 ,  F23R3/00

CPC classification number: F23R3/60 ,  F23R3/002 ,  F23R3/283 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A combustion chamber (110) for a turbine engine, such as an airplane turboprop or turbojet, the combustion chamber comprising two coaxial annular walls, respectively an inner wall and an outer wall, that are connected together at their upstream ends by a chamber end wall (118) having an annular row of openings (119) for mounting fuel injection devices (120), the combustion chamber being characterized in that an annular metal sheet (130) is mounted upstream from the end wall and includes mounting orifices for receiving the above-mentioned injection devices, the sheet being substantially parallel to the end wall and co-operating therewith to define an annular air flow cavity (140).

公开(公告)号：US20150059346A1

公开(公告)日：2015-03-05

申请号：US14378211

申请日：2013-02-08

Applicant: SNECMA

Inventor： Jacques Marcel Arthur Bunel ,  Frederic Marius Mathieu ,  Gilles Ulryck

IPC: F23R3/28 ,  F02C7/22

CPC classification number: F23R3/286 ,  F02C7/22 ,  F23D2211/00 ,  F23R3/14 ,  F23R3/283 ,  F23R2900/00005 ,  F23R2900/00017

Abstract: A device for injecting air and fuel into a combustion chamber of a turbine engine, the device including a fuel injector, at least one first element mounted on the fuel injector, and at least one second element mounted on an end wall of the combustion chamber. The first element includes a radial rim that is movable in a radial groove of the second element, which groove is defined by a sheath and by a closure ring welded to an inside of the sheath. The closure ring includes a radial wall and a cylindrical rim extending from the radially outer periphery of the radial wall towards a radial wall of the sheath and bearing via its corresponding free end against the radial wall of the sheath.

Abstract translation: 一种用于将空气和燃料喷射到涡轮发动机的燃烧室中的装置，该装置包括燃料喷射器，安装在燃料喷射器上的至少一个第一元件和安装在燃烧室的端壁上的至少一个第二元件。 第一元件包括可在第二元件的径向凹槽中移动的径向边缘，该凹槽由护套和通过焊接到护套内侧的封闭环限定。 闭合环包括径向壁和从径向壁的径向外周向径向壁延伸的圆柱形边缘，并且经由其相应的自由端抵靠护套的径向壁。

公开(公告)号：US09410703B2

公开(公告)日：2016-08-09

申请号：US13836510

申请日：2013-03-15

Applicant: SNECMA

Inventor： Jacques Marcel Arthur Bunel ,  Gilles Ulryck

IPC: F23R3/14 ,  F23R3/28 ,  F23R3/60

CPC classification number: F23R3/286 ,  F23D2211/00 ,  F23R3/14 ,  F23R3/283 ,  F23R3/60 ,  F23R2900/00017

Abstract: A device for injecting a mixture of air and fuel into a turbine engine combustion chamber, the device including a mechanism for centering a fuel injector, which mechanism is movable radially in a support mechanism fastened to a wall of the chamber, the support mechanism carrying a retaining mechanism for axially retaining the centering mechanism on a side opposite from the chamber wall, the retaining mechanism being fastened in releasable manner to the support mechanism.

Abstract translation: 一种用于将空气和燃料的混合物喷射到涡轮发动机燃烧室中的装置，该装置包括用于使燃料喷射器居中的机构，该机构可在固定到腔室的壁的支撑机构中径向移动，支撑机构承载 保持机构用于将定心机构轴向保持在与腔壁相对的一侧上，保持机构以可释放的方式紧固到支撑机构。

公开(公告)号：US20140318138A1

公开(公告)日：2014-10-30

申请号：US14070698

申请日：2013-11-04

Applicant: SNECMA

Inventor： Jacques Marcel Arthur Bunel ,  Gilles Ulryck

IPC: F23R3/60 ,  F23R3/00

CPC classification number: F23R3/60 ,  F23R3/002 ,  F23R3/283 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A combustion chamber (110) for a turbine engine, such as an airplane turboprop or turbojet, the combustion chamber comprising two coaxial annular walls, respectively an inner wall and an outer wall, that are connected together at their upstream ends by a chamber end wall (118) having an annular row of openings (119) for mounting fuel injection devices (120), the combustion chamber being characterized in that an annular metal sheet (130) is mounted upstream from the end wall and includes mounting orifices for receiving the above-mentioned injection devices, the sheet being substantially parallel to the end wall and co-operating therewith to define an annular air flow cavity (140).

Abstract translation: 一种用于诸如飞机涡轮螺旋桨或涡轮喷气发动机的涡轮发动机的燃烧室（110），所述燃烧室包括分别为内壁和外壁的两个同轴的环形壁，所述内壁和外壁在其上游端通过腔室端壁 （118），其具有用于安装燃料喷射装置（120）的环形排开口（119），所述燃烧室的特征在于，环形金属片（130）安装在所述端壁的上游，并且包括用于接收上述的安装孔 所述片材基本上平行于端壁并与之配合以限定环形空气流动空腔（140）。

公开(公告)号：US09500371B2

公开(公告)日：2016-11-22

申请号：US14378211

申请日：2013-02-08

Applicant: SNECMA

Inventor： Jacques Marcel Arthur Bunel ,  Frederic Marius Mathieu ,  Gilles Ulryck

IPC: F23R3/28 ,  F02C7/22 ,  F23R3/14

CPC classification number: F23R3/286 ,  F02C7/22 ,  F23D2211/00 ,  F23R3/14 ,  F23R3/283 ,  F23R2900/00005 ,  F23R2900/00017

Abstract: A device for injecting air and fuel into a combustion chamber of a turbine engine, the device including a fuel injector, at least one first element mounted on the fuel injector, and at least one second element mounted on an end wall of the combustion chamber. The first element includes a radial rim that is movable in a radial groove of the second element, which groove is defined by a sheath and by a closure ring welded to an inside of the sheath. The closure ring includes a radial wall and a cylindrical rim extending from the radially outer periphery of the radial wall towards a radial wall of the sheath and bearing via its corresponding free end against the radial wall of the sheath.

Abstract translation: 一种用于将空气和燃料喷射到涡轮发动机的燃烧室中的装置，该装置包括燃料喷射器，安装在燃料喷射器上的至少一个第一元件和安装在燃烧室的端壁上的至少一个第二元件。 第一元件包括可在第二元件的径向凹槽中移动的径向边缘，该凹槽由护套和通过焊接到护套内侧的封闭环限定。 闭合环包括径向壁和从径向壁的径向外周向径向壁延伸的圆柱形边缘，并且经由其相应的自由端抵靠护套的径向壁。