中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

6 records (took 0.008 seconds)

    Method of mixing between a primary flow and a secondary flow in a turbine engine, corresponding device and turbine engine
    3.
    发明授权
    Method of mixing between a primary flow and a secondary flow in a turbine engine, corresponding device and turbine engine 有权

    公开(公告)号：US09709002B2

    公开(公告)日：2017-07-18

    申请号：US14178584

    申请日：2014-02-12

    Applicant: SNECMA

    Inventor： Guillaume Pouyau ,  Nicolas Sirvin

    IPC: F02K1/38

    CPC classification number: F02K1/386 ,  F05D2260/2212 ,  Y02T50/675

    Abstract: A method of mixing in a discharge conduit, in a turbine engine with two or more flows, of a primary flow and a secondary flow, the two flows emerging in the discharge conduit by two coaxial ducts, separated by an internal housing which has an end downstream relative to the flow direction of the flows, the two coaxial ducts each being defined between an internal wall and an external wall, upstream of the downstream end of the internal housing, and the secondary flow surrounding the primary flow, is provided. The method includes disposing a divergent radial deflection device in the primary duct, spaced apart from the walls of the primary duct. A turbine engine including the deflection device is also provided.

    Turbine engine nozzle having confluent streams and including a core cowl with overlapping flaps
    4.
    发明授权
    Turbine engine nozzle having confluent streams and including a core cowl with overlapping flaps 有权

    公开(公告)号：US10167814B2

    公开(公告)日：2019-01-01

    申请号：US15023952

    申请日：2014-09-16

    Applicant: SNECMA

    Inventor： Romain Ferrier ,  Alexandre Couilleaux ,  Jackie Raymond Julien Prouteau ,  Nicolas Sirvin

    IPC: F02K1/46 ,  F02K1/38 ,  F02K1/40

    Abstract: A turbine engine nozzle having confluent streams, the nozzle including a core cowl arranged around an annular central body and co-operating therewith to define a core annular channel for passing a flow of a core stream, the core stream on entry into the nozzle possessing an azimuth component driving residual gyratory movement of the core stream in two opposite gyratory flow directions corresponding to two operating speeds of the engine, the core cowl having an annular upstream portion that is extended downstream by an annular terminal portion having longitudinal cuts forming a plurality of flaps that overlap radially in pairs via their respective side edges in such a manner that, for each flap, one of the two side edges of the flap is positioned internally relative to the corresponding side edge of one of the adjacent flaps, while the other side edge of the flap is positioned externally relative to the corresponding side edge of the other adjacent flap.

    METHOD OF MIXING BETWEEN A PRIMARY FLOW AND A SECONDARY FLOW IN A TURBINE ENGINE, CORRESPONDING DEVICE AND TURBINE ENGINE
    5.
    发明申请
    METHOD OF MIXING BETWEEN A PRIMARY FLOW AND A SECONDARY FLOW IN A TURBINE ENGINE, CORRESPONDING DEVICE AND TURBINE ENGINE 有权
    涡轮发动机，相应装置和涡轮发动机中的主流与二次流之间的混合方法

    公开(公告)号：US20140234074A1

    公开(公告)日：2014-08-21

    申请号：US14178584

    申请日：2014-02-12

    Applicant: SNECMA

    Inventor： Guillaume Pouyau ,  Nicolas Sirvin

    IPC: F02K1/38

    CPC classification number: F02K1/386 ,  F05D2260/2212 ,  Y02T50/675

    Abstract: The invention relates to a method of mixing in a discharge conduit, in a turbine engine with two or more flows, of a primary flow and a secondary flow, the two flows emerging in said discharge conduit by two coaxial ducts, separated by an internal housing which has an end downstream relative to the flow direction of the flows, the two coaxial ducts each being defined between an internal wall and an external wall, upstream of the downstream end of the internal housing, and the secondary flow surrounding the primary flow, characterised in that it consists of disposing at least one divergent radial deflection means in primary duct, spaced apart from the walls of said primary duct.It likewise relates to the deflection means capable of implementing the method, the fixing means of said deflection means being capable of positioning them in the primary duct; as well as a turbine engine equipped with these means, comprising at least one primary flow and one secondary flow, the two flows emerging in a discharge conduit by two coaxial ducts, the secondary flow surrounding the primary flow.

    Abstract translation: 本发明涉及一种在具有主流和二次流的两个或多个流动的涡轮发动机的排放管道中混合的方法，所述两个流体由两个同轴管道排出，所述两个同轴管道由内部壳体 其相对于流动的流动方向具有下游的端部，两个同轴管道各自被限定在内部壁和外部壁之间，在内部壳体的下游端的上游以及围绕主要流动的次级流动，其特征在于 因为它包括在主管道中设置至少一个发散的径向偏转装置，与主管道的壁间隔开。 它同样涉及能够实现该方法的偏转装置，所述偏转装置的固定装置能将它们定位在主导管中; 以及配备有这些装置的涡轮发动机，包括至少一个主流和一个二次流，两个流体通过两个同轴管道排出在排放管道中，二次流围绕主流。

    EXHAUST CENTERBODY FOR A TURBINE ENGINE
    6.
    发明申请
    EXHAUST CENTERBODY FOR A TURBINE ENGINE 有权
    用于涡轮发动机的排气中心

    公开(公告)号：US20150101338A1

    公开(公告)日：2015-04-16

    申请号：US14339846

    申请日：2014-07-24

    Applicant: SNECMA

    Inventor： Guillaume POUYAU ,  Nicolas Sirvin

    IPC: F02K1/04 ,  B21D53/84 ,  B23P23/00 ,  F02K1/82

    CPC classification number: F02K1/04 ,  B21D53/84 ,  B23P23/00 ,  B64D33/04 ,  F01D5/143 ,  F01D17/10 ,  F01D17/141 ,  F01D17/145 ,  F01D25/04 ,  F01D25/30 ,  F02K1/82 ,  Y02T50/671 ,  Y02T50/673 ,  Y10T29/49323

    Abstract: Exhaust centerbody (12″) for a turbine engine, comprising a truncated downstream part (26), which is connected to an upstream part (24) by an annular ridge (22) marking a discontinuity between the outer surfaces of the upstream and downstream parts, the outer surface of the downstream part having a substantially conical general shape, of which the tip (29) is oriented downstream and is positioned in the region of the axis A, the axial half-section of this outer surface defining a line of which the upstream end part is substantially tangential to a straight line (28) passing through the above-mentioned ridge and forming a non-zero angle α with a tangent (30) to the outer surface of the upstream part, in the region of the ridge, and of which the downstream end part is substantially tangential to a straight line (32) passing through the above-mentioned tip and forming a non-zero angle β with the axis A.

    Abstract translation: 一种用于涡轮发动机的排气中心体（12“），包括截短的下游部分（26），其通过环形脊（22）连接到上游部分（24），所述环形脊（22）标记上游部分和下游部分的外表面之间的不连续性 下游部分的外表面具有基本上圆锥形的大致形状，其顶端（29）定向在下游并位于轴线A的区域中，该外表面的轴向半部分限定一条线 上游端部与穿过上述脊的直线（28）基本上相切，并且在脊的区域中与上游部分的外表面形成具有切线（30）的非零角度α ，并且其下游端部与穿过上述尖端的直线（32）基本相切，并形成非零角度＆bgr; 与轴A.

Patent Agency Ranking