公开(公告)号：US08408009B2

公开(公告)日：2013-04-02

申请号：US12489844

申请日：2009-06-23

Applicant: Stephane Pierre Guillaume Blanchard ,  Mathieu Dakowski ,  Thomas Daris ,  Romain Nicolas Lunel

Inventor： Stephane Pierre Guillaume Blanchard ,  Mathieu Dakowski ,  Thomas Daris ,  Romain Nicolas Lunel

IPC: F02C6/04

CPC classification number: F01D9/06 ,  F01D25/12 ,  F02C6/08 ,  F02C7/18 ,  F02K1/822 ,  Y02T50/675 ,  Y10T137/7891

Abstract: Air bleed device for cooling components in a turbine engine, including an annular conduit (18) having a radially internal portion swept by an airflow (22) and which comprises at least one air inlet orifice (20) formed in an upstream radial wall (38) of the conduit (18), a flap valve (40) for controlling the airflow entering through the orifice (20) and of which the flapper (41) includes a plate (42) applied against the wall (38) and capable of being moved by sliding on said wall (38) by a maneuvering member (50) mobile in translation parallel to the wall (38) between a position in which the plate (42) closes off the orifice (20) and a position in which the plate (42) opens said orifice.

Abstract translation: 用于在涡轮发动机中冷却部件的排气装置，包括具有由气流（22）扫掠的径向内部的环形导管（18），并且包括形成在上游径向壁（38）中的至少一个进气口（20） ），用于控制通过所述孔口（20）进入的气流的瓣阀（40），并且所述挡板（41）包括施加在所述壁（38）上的板（42），并且能够 通过在所述板（42）关闭所述孔（20）的位置与所述板（20）之间平行于所述壁（38）平移的位置移动的操纵构件（50）在所述壁（38）上滑动而移动， （42）打开所述孔口。

公开(公告)号：US08397513B2

公开(公告)日：2013-03-19

申请号：US12603943

申请日：2009-10-22

Applicant: Stephane Pierre Guillaume Blanchard ,  Mathieu Dakowski ,  Thomas Daris ,  Romain Nicolas Lunel

Inventor： Stephane Pierre Guillaume Blanchard ,  Mathieu Dakowski ,  Thomas Daris ,  Romain Nicolas Lunel

IPC: F02K1/00

CPC classification number: F02C9/18 ,  F01D17/141 ,  Y10T137/7891

Abstract: Device (10) for the tapping of air for the cooling of flaps of a turbojet nozzle, comprising an annular duct (18) having a radially internal wall (22) swept by a stream of air (24) and which comprises at least one air inlet orifice (20), a flap valve (40) for controlling the flow rate of air entering through the orifice (20), formed of an elastically deformable metal plate (42) of which a downstream end is fixed on an edge of the orifice (20), and of which an upstream end can be displaced by a manoeuvring member (46) mobile in translation parallel to the axis (52) of the orifice between a position where the plate (42) seals this orifice and a position where the plate (42) opens this orifice.

Abstract translation: 用于抽出用于冷却涡轮喷气喷嘴的翼片的空气的装置（10），包括具有由空气流（24）扫过的径向内壁（22）的环形管道（18），并且包括至少一个空气 入口孔口（20），用于控制通过孔口（20）进入的空气的流量的瓣阀（40），其由可弹性变形的金属板（42）形成，其下游端固定在孔口的边缘 （20），并且其中上游端可以通过平行于孔口的轴线（52）平移移动的操纵构件（46）移位，该位置在板（42）密封该孔口的位置和 板（42）打开该孔。

公开(公告)号：US20110250061A1

公开(公告)日：2011-10-13

申请号：US13059790

申请日：2009-08-25

Applicant: Stéphane Pierre, Guillaume Blanchard ,  Fabrice Marcel Nëel Garin ,  Laurent Pierre, Joseph Ricou ,  Mathieu Dakowski

Inventor： Stéphane Pierre, Guillaume Blanchard ,  Fabrice Marcel Nëel Garin ,  Laurent Pierre, Joseph Ricou ,  Mathieu Dakowski

IPC: F01D1/02

CPC classification number: F01D9/023 ,  F01D9/04 ,  F01D9/042 ,  F05D2230/64 ,  F05D2260/30 ,  Y02T50/671

Abstract: A stationary vane assembly of a turbine engine including an inner casing and a high-pressure turbine guide vane assembly including at least two angular sectors including blades, the angular sectors being fixed on the casing, each angular sector including a platform and a fastening tab. The fastening tab protrudes from the platform radially inwardly. The casing includes a first annular groove receiving the fastening tabs, radial retaining pins for the angular sectors being introduced into bores made in the casing and the fastening tabs, the axial retaining pins being axially stopped by a ring mounted in a second annular groove of the casing.

Abstract translation: 包括涡轮发动机的固定叶片组件，其包括内壳和包括至少两个包括叶片的角扇区的高压涡轮导叶组件，角扇区固定在壳体上，每个角扇区包括平台和紧固翼片。 紧固片从平台径向向内突出。 壳体包括容纳紧固突片的第一环形凹槽，用于角部分的径向保持销引入到壳体和紧固突片中形成的孔中，轴向保持销由安装在第二环形凹槽 套管。

公开(公告)号：US20110206504A1

公开(公告)日：2011-08-25

申请号：US13059242

申请日：2009-08-25

Applicant: Stephane Pierre Guillaume Blanchard ,  Mathieu Dakowski ,  Fabrice Marcel, Noel Garin ,  Maurice Guy Judet

Inventor： Stephane Pierre Guillaume Blanchard ,  Mathieu Dakowski ,  Fabrice Marcel, Noel Garin ,  Maurice Guy Judet

IPC: F01D1/02

CPC classification number: F01D5/081 ,  F01D9/042 ,  F02C7/28 ,  F05B2260/301 ,  F05D2230/64 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49323

Abstract: A stationary vane assembly for a turbine engine including an inner casing and at least two angular sectors forming a high-pressure guide vane assembly, each angular sector including a fastening tab for fastening the angular sector on the casing. The stationary vane assembly including a ring of abradable material fixed on the casing, on the side of a mobile vane assembly using a plurality of screw-nut assemblies, the stationary vane assembly also including radial retaining pins for the angular sectors introduced into first bores formed in the fastening tabs and in the mounting clip, the bores having axes substantially parallel to the longitudinal axis, the mounting clip being fixed on the casing by the same screw-nut assemblies as those fixing the ring of abradable material support on the casing.

Abstract translation: 一种用于涡轮发动机的固定叶片组件，其包括内壳体和形成高压导叶组件的至少两个角扇形区，每个角扇区包括用于将角扇区紧固在壳体上的紧固翼片。 固定叶片组件包括固定在壳体上的可磨损材料环，在使用多个螺母 - 螺母组件的可动叶片组件的侧面上，固定叶片组件还包括形成于第一孔中的角扇形的径向固定销 在紧固突片和安装夹中，孔具有基本上平行于纵向轴线的轴线，安装夹具通过与将可磨损材料支撑环固定在外壳上的相同的螺母组件固定在壳体上。

公开(公告)号：US20100104429A1

公开(公告)日：2010-04-29

申请号：US12603943

申请日：2009-10-22

Applicant: Stephane Pierre Guillaume Blanchard ,  Mathieu Dakowski ,  Thomas Daris ,  Romain Nicolas Lunel

Inventor： Stephane Pierre Guillaume Blanchard ,  Mathieu Dakowski ,  Thomas Daris ,  Romain Nicolas Lunel

IPC: F01D25/12

CPC classification number: F02C9/18 ,  F01D17/141 ,  Y10T137/7891

Abstract: Device (10) for the tapping of air for the cooling of flaps of a turbojet nozzle, comprising an annular duct (18) having a radially internal wall (22) swept by a stream of air (24) and which comprises at least one air inlet orifice (20), a flap valve (40) for controlling the flow rate of air entering through the orifice (20), formed of an elastically deformable metal plate (42) of which a downstream end is fixed on an edge of the orifice (20), and of which an upstream end can be displaced by a manoeuvring member (46) mobile in translation parallel to the axis (52) of the orifice between a position where the plate (42) seals this orifice and a position where the plate (42) opens this orifice.

Abstract translation: 用于抽出用于冷却涡轮喷气喷嘴的翼片的空气的装置（10），包括具有由空气流（24）扫过的径向内壁（22）的环形管道（18），并且包括至少一个空气 入口孔口（20），用于控制通过孔口（20）进入的空气的流量的瓣阀（40），其由可弹性变形的金属板（42）形成，其下游端固定在孔口的边缘 （20），并且其中上游端可以通过平行于孔口的轴线（52）平移移动的操纵构件（46）移位，该位置在板（42）密封该孔口的位置和 板（42）打开该孔。

公开(公告)号：US20090320497A1

公开(公告)日：2009-12-31

申请号：US12489844

申请日：2009-06-23

Applicant: Stephane Pierre Guillaume BLANCHARD ,  Mathieu Dakowski ,  Thomas Daris ,  Romain Nicolas Lunel

Inventor： Stephane Pierre Guillaume BLANCHARD ,  Mathieu Dakowski ,  Thomas Daris ,  Romain Nicolas Lunel

IPC: F02C7/18 ,  F16K1/18

CPC classification number: F01D9/06 ,  F01D25/12 ,  F02C6/08 ,  F02C7/18 ,  F02K1/822 ,  Y02T50/675 ,  Y10T137/7891

Abstract: Air bleed device for cooling components in a turbine engine, including an annular conduit (18) having a radially internal portion swept by an airflow (22) and which comprises at least one air inlet orifice (20) formed in an upstream radial wall (38) of the conduit (18), a flap valve (40) for controlling the airflow entering through the orifice (20) and of which the flapper (41) includes a plate (42) applied against the wall (38) and capable of being moved by sliding on said wall (38) by a maneuvering member (50) mobile in translation parallel to the wall (38) between a position in which the plate (42) closes off the orifice (20) and a position in which the plate (42) opens said orifice.

Abstract translation: 用于在涡轮发动机中冷却部件的排气装置，包括具有由气流（22）扫掠的径向内部的环形导管（18），并且包括形成在上游径向壁（38）中的至少一个进气口（20） ），用于控制通过所述孔口（20）进入的气流的瓣阀（40），并且所述挡板（41）包括施加在所述壁（38）上的板（42），并且能够 通过在所述板（42）关闭所述孔（20）的位置与所述板（20）之间平行于所述壁（38）平移的位置移动的操纵构件（50）在所述壁（38）上滑动而移动， （42）打开所述孔口。

公开(公告)号：US20090097971A1

公开(公告)日：2009-04-16

申请号：US12247462

申请日：2008-10-08

Applicant: Mathieu DAKOWSKI ,  Sandrine Gandelot ,  Eric Jacques Lefebvre

Inventor： Mathieu DAKOWSKI ,  Sandrine Gandelot ,  Eric Jacques Lefebvre

IPC: F03B11/02

CPC classification number: F01D5/081 ,  F01D5/26 ,  F01D11/001 ,  F05D2260/6022 ,  F05D2260/96 ,  Y02T50/676

Abstract: This invention relates to a turbine stator (5) for an aircraft turbine engine, comprising: a stator wall (46) supporting a high pressure air injector (50) fixed on the downstream side; an annular abradable element support (54) the lower radial end (54a) of which is fixed to said high pressure air injector and its upper radial end (54b) is fixed to said stator wall, such that they jointly delimit a cavity (58) under pressure. According to the invention, it also comprises at least one vibration damping device (74) located in said cavity (58) under pressure, said vibration damping device being in contact with each of the two elements taken among said stator wall (46) and said annular support (54).

Abstract translation: 本发明涉及一种用于飞行器涡轮发动机的涡轮机定子（5），包括：定子壁（46），其支撑固定在下游侧的高压空气喷射器（50）; 环形可磨损元件支撑件（54），其下径向端部（54a）固定到所述高压空气喷射器，并且其上部径向端部（54b）固定到所述定子壁上，使得它们共同限定空腔（58） 在压力之下。 根据本发明，它还包括在压力下位于所述空腔（58）中的至少一个减振装置（74），所述减振装置与所述定子壁（46）和所述 环形支撑件（54）。

公开(公告)号：US20080104941A1

公开(公告)日：2008-05-08

申请号：US11765173

申请日：2007-06-19

Applicant: Stephane Pierre Guillaume BLANCHARD ,  Laurent Bernard Cameriano ,  Mathieu Dakowski ,  Alain Pierre Page

Inventor： Stephane Pierre Guillaume BLANCHARD ,  Laurent Bernard Cameriano ,  Mathieu Dakowski ,  Alain Pierre Page

IPC: F02K1/04

CPC classification number: F02K1/04 ,  F05D2230/642 ,  F05D2260/96 ,  F05D2300/603 ,  Y02T50/672

Abstract: Mounting an exhaust cone of composite material. The exhaust cone is mounted to extend an adapter ring and it is held in particular by elastic stress means that act axially.

Abstract translation: 安装复合材料的排气锥。 安装排气锥以延伸适配环，并且其特别地通过轴向作用的弹性应力装置来保持。

公开(公告)号：US20060086093A1

公开(公告)日：2006-04-27

申请号：US11248329

申请日：2005-10-13

Applicant: Mathieu Dakowski ,  Sylvain Duval ,  Olivier Kreder ,  Romain Lunel ,  Emmanuel Mandet ,  Guillaume Sevi

Inventor： Mathieu Dakowski ,  Sylvain Duval ,  Olivier Kreder ,  Romain Lunel ,  Emmanuel Mandet ,  Guillaume Sevi

IPC: F02K1/12

CPC classification number: F02K1/1207 ,  F02K1/80

Abstract: A variable-section nozzle for a turbomachine, the nozzle comprising a plurality of moving flaps mounted on the downstream end of an annular casing of the turbomachine, a moving flap control system comprising control levers each associated with a respective moving flap and at least one actuator for actuating the control levers, and a plurality of pairs of arms each forming a control lever support, the arms of each support being secured both to the casing and to a control lever, each pair of arms forming a control lever support being formed as a single piece.

Abstract translation: 一种用于涡轮机的可变截面喷嘴，所述喷嘴包括安装在所述涡轮机的环形壳体的下游端的多个可动翼片，包括控制杆的移动挡板控制系统，每个控制杆与相应的活动挡板和至少一个致动器 用于致动控制杆和多个成对的臂，每对臂形成控制杆支撑件，每个支撑件的臂固定到壳体和控制杆上，形成控制杆支撑件的每对臂形成为 单件