公开(公告)号：US08864458B2

公开(公告)日：2014-10-21

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 ,  F01D5/08 ,  F01D9/04 ,  F02C7/28

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：US08858169B2

公开(公告)日：2014-10-14

申请号：US13059350

申请日：2009-08-24

Applicant: Mathieu Dakowski ,  Alain Dominique Gendraud

Inventor： Mathieu Dakowski ,  Alain Dominique Gendraud

IPC: F01D1/02 ,  F01D25/24

CPC classification number: F02C3/045 ,  F01D9/042 ,  F01D25/246 ,  F05D2250/41 ,  F05D2270/114 ,  Y02T50/671

Abstract: An assembling of a guide vane assembly of a turbomachine turbine, formed by an annular row of stationary flow-stabilizing vanes. An outer edge of the guide vane assembly is axially bearing on a line of an external casing of the turbine and an inner edge of the guide vane assembly is in axial sliding connection with the line of the internal casing of the turbine, the axial sliding connection allowing the inner edge to be free along the motor axis with the axial stop being achieved by the axial bearing of the outer edge of the vane.

Abstract translation: 一种涡轮机涡轮机的导叶组件的组装，由一组固定的流动稳定叶片形成。 导向叶片组件的外边缘轴向地轴承在涡轮机的外壳的一条线上，并且导向叶片组件的内边缘与涡轮机的内壳线的轴向滑动连接，轴向滑动连接 允许内边缘沿着马达轴线自由，其中轴向止动通过叶片的外边缘的轴向轴承来实现。

公开(公告)号：US08133018B2

公开(公告)日：2012-03-13

申请号：US12038604

申请日：2008-02-27

Applicant: Mathieu Dakowski ,  Claire Dorin ,  Alain Dominique Gendraud ,  Vincent Philippot

Inventor： Mathieu Dakowski ,  Claire Dorin ,  Alain Dominique Gendraud ,  Vincent Philippot

IPC: F01D9/00

CPC classification number: F01D25/246 ,  F01D9/042

Abstract: A high-pressure turbine of a turbomachine, including at least one upstream guide vane element and an impeller mounted so as to rotate inside ring sectors attached to an annular support which is suspended from an outer casing, the upstream guide vane element including, at its radially inner end, a mechanism for attachment to an inner casing and, at its radially outer end, a mechanism for pressing axially on a fixed element of the turbine that is suspended from the outer casing independently of the annular support for attachment of the ring sectors.

Abstract translation: 涡轮机的高压涡轮机，包括至少一个上游引导叶片元件和叶轮，其安装成在附接到从外壳悬挂的环形支撑件的环形部分内旋转，所述上游引导叶片元件包括在其上 径向内端，用于附接到内壳体的机构，并且在其径向外端处具有用于轴向地按压在涡轮机的固定元件上的机构，所述机构与所述环形支撑件独立于所述环形支撑件悬挂， 。

公开(公告)号：US20080267768A1

公开(公告)日：2008-10-30

申请号：US12038604

申请日：2008-02-27

Applicant: Mathieu Dakowski ,  Claire Dorin ,  Alain Dominique Gendraud ,  Vincent Philippot

Inventor： Mathieu Dakowski ,  Claire Dorin ,  Alain Dominique Gendraud ,  Vincent Philippot

IPC: F01D5/02

CPC classification number: F01D25/246 ,  F01D9/042

Abstract: High-pressure turbine of a turbomachine A high-pressure turbine (10) of a turbomachine, comprising at least one upstream guide vane element (16) and an impeller (18) mounted so as to rotate inside ring sectors (20) attached to an annular support (24) which is suspended from an outer casing (22), the upstream guide vane element comprising, at its radially inner end, means of attachment to an inner casing and, at its radially outer end, means (102, 104) for pressing axially on a fixed element (90) of the turbine that is suspended from the outer casing independently of the annular support for attachment of the ring sectors.

Abstract translation: 涡轮机的高压涡轮机涡轮机的高压涡轮机（10），包括至少一个上游引导叶片元件（16）和叶轮（18），所述至少一个上游引导叶片元件（16）和叶轮（18）安装成在环形部分（20）内旋转， 环形支撑件（24），其从外壳（22）悬挂，所述上游引导叶片元件在其径向内端包括附接到内壳的装置，并且在其径向外端处包括装置（102,104） 用于轴向地压在涡轮机的固定元件（90）上，所述固定元件（90）独立于环形支撑件从外壳悬挂以附接环形部分。

公开(公告)号：US20060225427A1

公开(公告)日：2006-10-12

申请号：US11236576

申请日：2005-09-28

Applicant: Daniel Bainachi ,  Mathieu Dakowski ,  Olivier Kreder ,  Romain Lunel ,  Daniel Plona

Inventor： Daniel Bainachi ,  Mathieu Dakowski ,  Olivier Kreder ,  Romain Lunel ,  Daniel Plona

IPC: F02K1/06

CPC classification number: F02K1/12 ,  F05D2240/128 ,  F05D2240/50 ,  F05D2250/241 ,  F05D2250/411 ,  F05D2260/30

Abstract: The jet engine of the invention comprises an exhaust nozzle of variable section, comprising at least one flap pivot mounted about a pin, the pin being joined to the fixed structure of the jet engine via two braces each comprising a bore for housing the pin, the flap being pivot commanded by an actuating cylinder, connected to two fasteners which each comprise a bore through which the pin passes and about which they rotate. The jet engine is characterized by the fact that the pin, the bores of the braces and bores of the fasteners are arranged so that the contacts between the pin with the bore walls of the braces and with the bore walls of the fasteners are made over convex surfaces. Therefore, when in operation, in the event of pin bending the contact surfaces follow this convex shape and are suitably distributed.

公开(公告)号：US08100635B2

公开(公告)日：2012-01-24

申请号：US12254518

申请日：2008-10-20

Applicant: Mathieu Dakowski ,  Claire Dorin ,  Alain Dominique Gendraud ,  Nicolas Pommier

Inventor： Mathieu Dakowski ,  Claire Dorin ,  Alain Dominique Gendraud ,  Nicolas Pommier

IPC: F01D5/14 ,  F03D11/00 ,  F04D29/38

CPC classification number: F01D11/005 ,  F01D11/24 ,  F05D2240/11 ,  Y02T50/671

Abstract: A turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring held by a casing of the turbine, and an annular thermal protection sheet mounted between the casing and the sealing ring is disclosed. The annular thermal protection sheet is formed by a plurality of curved plates mounted end-to-end and attached by pins to the casing.

Abstract translation: 公开了一种涡轮发动机中的涡轮级，包括在由涡轮机的壳体保持的密封环内旋转的叶片的叶片，以及安装在壳体和密封环之间的环形热保护片。 环形热保护片由端对端安装的多个弯曲板形成，并通过销附接到壳体。

公开(公告)号：US07533533B2

公开(公告)日：2009-05-19

申请号：US11236576

申请日：2005-09-28

Applicant: Daniel Olivier Bainachi ,  Mathieu Dakowski ,  Olivier Kreder ,  Romain Lunel ,  Daniel Georges Plona

Inventor： Daniel Olivier Bainachi ,  Mathieu Dakowski ,  Olivier Kreder ,  Romain Lunel ,  Daniel Georges Plona

IPC: F02K1/00

CPC classification number: F02K1/12 ,  F05D2240/128 ,  F05D2240/50 ,  F05D2250/241 ,  F05D2250/411 ,  F05D2260/30

Abstract: The jet engine of the invention comprises an exhaust nozzle of variable section, comprising at least one flap pivot mounted about a pin, the pin being joined to the fixed structure of the jet engine via two braces each comprising a bore for housing the pin, the flap being pivot commanded by an actuating cylinder, connected to two fasteners which each comprise a bore through which the pin passes and about which they rotate. The jet engine is characterized by the fact that the pin, the bores of the braces and bores of the fasteners are arranged so that the contacts between the pin with the bore walls of the braces and with the bore walls of the fasteners are made over convex surfaces. Therefore, when in operation, in the event of pin bending the contact surfaces follow this convex shape and are suitably distributed.

Abstract translation: 本发明的喷气发动机包括可变部分的排气喷嘴，包括至少一个围绕销安装的挡板枢轴，该销通过两个支架连接到喷气发动机的固定结构，每个支架包括用于容纳销的孔， 翼片由致动筒指示，连接到两个紧固件，每个紧固件包括销穿过的孔，并且它们绕它们旋转。 喷气式发动机的特征在于，销，支架的孔和孔的孔被布置成使得销与支架的孔壁之间的接触以及紧固件的孔壁被制成凸起 表面。 因此，当操作时，在销弯曲的情况下，接触表面遵循该凸形并且适当地分布。

公开(公告)号：US20090104026A1

公开(公告)日：2009-04-23

申请号：US12254518

申请日：2008-10-20

Applicant: Mathieu DAKOWSKI ,  Claire DORIN ,  Alain Dominique GENDRAUD ,  Nicolas POMMIER

Inventor： Mathieu DAKOWSKI ,  Claire DORIN ,  Alain Dominique GENDRAUD ,  Nicolas POMMIER

IPC: F01D11/18 ,  F02C7/24 ,  F01D25/14

CPC classification number: F01D11/005 ,  F01D11/24 ,  F05D2240/11 ,  Y02T50/671

Abstract: Turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring (22) held by a casing (24) of the turbine, and an annular thermal protection sheet mounted between the casing (24) and the ring (22), wherein the annular thermal protection sheet is formed by a plurality of curved plates (54, 56) mounted end-to-end and attached by pins (70) to the casing (24).

Abstract translation: 涡轮发动机中的涡轮级，包括在由涡轮机的壳体（24）保持的密封环（22）内旋转的叶片的轮和安装在壳体（24）和环（22）之间的环形热保护片， ，其中所述环形热保护片由端对端安装并通过销（70）附接到所述壳体（24）的多个弯曲板（54,56）形成。

公开(公告)号：US20080206047A1

公开(公告)日：2008-08-28

申请号：US12038422

申请日：2008-02-27

Applicant: Mathieu DAKOWSKI ,  Claire Dorin ,  Alain Dominique Gendraud ,  Vincent Philippot

Inventor： Mathieu DAKOWSKI ,  Claire Dorin ,  Alain Dominique Gendraud ,  Vincent Philippot

IPC: F01D25/24 ,  F01D25/26

CPC classification number: F01D11/12 ,  F01D9/04 ,  F01D25/246 ,  F05D2240/11

Abstract: A turbine stage in a turbomachine comprising ring sectors (20) arranged about a turbine impeller (18), and an annular support (50) supporting the ring sectors and attached to a turbine casing (22), this annular support being able to be deformed elastically in the radial direction to cushion at least a portion of the deformations of the turbine casing in operation.

Abstract translation: 涡轮机中的涡轮机级包括围绕涡轮机叶轮（18）布置的环形部分（20），以及环形支撑件（50），其支撑所述环形部分并附接到涡轮机壳体（22），所述环形支撑件能够变形 在径向方向上弹性地运动，以缓冲涡轮机壳体的至少一部分变形。

公开(公告)号：US20060090470A1

公开(公告)日：2006-05-04

申请号：US11248330

申请日：2005-10-13

Applicant: Mathieu Dakowski ,  Guy Lapergue ,  Romain Lunel ,  Guillaume Sevi

Inventor： Mathieu Dakowski ,  Guy Lapergue ,  Romain Lunel ,  Guillaume Sevi

IPC: F02K1/12

CPC classification number: F02K1/1207

Abstract: A variable-section turbomachine nozzle comprises a plurality of moving flaps, and a moving flap control system comprising control levers each associated with a respective moving flap, the control levers comprising both controlled levers that are actuated directly by actuators, and follower levers that are actuated by the controlled levers via transmission links. When the nozzle is at rest, the flaps associated with the follower levers present a radial offset relative to the flaps associated with the controlled levers.