公开(公告)号：US09599342B2

公开(公告)日：2017-03-21

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 ,  F23R3/06 ,  F23R3/50

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 l 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.

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。

公开(公告)号：US08875484B2

公开(公告)日：2014-11-04

申请号：US12949375

申请日：2010-11-18

申请人： Dominique Maurice Jacques Lains ,  Nicolas Christian Raymond Leblond ,  Christophe Pieussergues

发明人： Dominique Maurice Jacques Lains ,  Nicolas Christian Raymond Leblond ,  Christophe Pieussergues

IPC分类号： F02C7/266 ,  F23R3/06 ,  F23R3/60

CPC分类号： F23R3/06 ,  F02C7/266 ,  F23D2207/00 ,  F23R3/60 ,  F23R2900/00012 ,  F23R2900/03042 ,  F23R2900/03043 ,  Y02T50/675

摘要： A turbomachine combustion chamber including at least one ignition plug carried by an outer casing and extending within guide means carried by a wall of the chamber, the wall forming a body of revolution. The guide means includes a tubular guide having the plug passing axially therethrough and mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out into the chamber, the guide extending at least in part in an air flow stream outside the chamber. The guide means includes a deflector surrounding the portion of the guide that is situated in the air flow stream so as to reduce the aerodynamic pressure on the guide and reduce the contact pressure of the guide on the plug.

摘要翻译： 一种涡轮机燃烧室，包括至少一个火花塞，该火花塞由外壳承载并且在由腔的壁承载的引导装置内延伸，壁形成旋转体。 引导装置包括管状引导件，该引导件具有塞子，其轴向穿过其中，并且在固定到腔室的壁上的烟囱上以轴向和横向间隙安装并且打开到腔室中，引导件至少部分地延伸到外部的气流流中 房间。 引导装置包括围绕引导件的位于空气流动流中的部分的偏转器，以便减小引导件上的空气动力学压力，并降低引导件在插头上的接触压力。

公开(公告)号：US08490402B2

公开(公告)日：2013-07-23

申请号：US12694622

申请日：2010-01-27

申请人： Dominique Maurice Jacques Lains ,  Nicolas Leblond ,  Denis Jean Maurice Sandelis

发明人： Dominique Maurice Jacques Lains ,  Nicolas Leblond ,  Denis Jean Maurice Sandelis

IPC分类号： F02K3/10

CPC分类号： F02K3/11 ,  F02C7/266 ,  F05D2260/20 ,  F23D2207/00 ,  F23R3/20 ,  Y02T50/676

摘要： An afterburner chamber includes a burner ring having housed therein an annular fuel strip that is pierced by orifices and that is mounted inside an annular thermal protection tube, and an ignition spark plug penetrating into the inside of the burner ring. The protection tube and the burner ring have orifices for passing air. The chamber also includes a device for ventilating the orifices of the fuel strip that are situated in the immediate vicinity of the spark plug.

摘要翻译： 后燃室包括燃烧器环，其中容纳有由孔刺穿并且安装在环形热保护管内的环形燃料条和安装在燃烧器环内部的点火火花塞。 保护管和燃烧器环具有用于通过空气的孔。 该室还包括用于使位于火花塞附近的燃料带的孔通风的装置。

公开(公告)号：US08505275B2

公开(公告)日：2013-08-13

申请号：US12687354

申请日：2010-01-14

申请人： Dominique Maurice Jacques Lains ,  Denis Jean Maurice Sandelis

发明人： Dominique Maurice Jacques Lains ,  Denis Jean Maurice Sandelis

IPC分类号： F02C7/266

CPC分类号： F23R3/28 ,  F02C7/266 ,  F23R3/50

摘要： A turbomachine including a combustion chamber provided with systems for injecting fuel into the chamber, and with at least one spark plug is disclosed. The injection system located as close as possible to the spark plug is configured in order to produce a pool of fuel having an angle of opening of a greater value than that of the pools produced by the other injection systems, and having a flow of fuel greater than that of the other injection systems.

摘要翻译： 公开了一种涡轮机，其包括燃烧室，其设置有用于将燃料喷射到室中的系统，以及至少一个火花塞。 配置为尽可能靠近火花塞的喷射系统被配置以产生具有比由其它喷射系统产生的池的开启角更大的开度角的燃料池，并且具有更大的燃料流 比其他注射系统。