公开(公告)号：US09982603B2

公开(公告)日：2018-05-29

申请号：US15106162

申请日：2014-11-26

Applicant: Snecma

Inventor： Pierre-François Simon Paul Pireyre ,  Francois Leglaye ,  David Gino Stifanic

IPC: F02C7/266 ,  H01T13/08 ,  F23R3/60 ,  F02C3/14 ,  F23R3/00 ,  F23R3/10 ,  F23R3/28

CPC classification number: F02C7/266 ,  F02C3/14 ,  F05D2220/32 ,  F05D2240/35 ,  F23D2207/00 ,  F23D2209/00 ,  F23D2211/00 ,  F23R3/002 ,  F23R3/10 ,  F23R3/28 ,  F23R3/60 ,  F23R2900/00005 ,  F23R2900/00012 ,  H01T13/08

Abstract: Assembly comprising, on a turbomachine:—a combustion chamber (30) having a longitudinal axis (30a) and comprising: internal and external longitudinal walls (90) having a first opening (90a) substantially transverse to said axis (30a), an outer casing (110) having a second opening (110a) likewise substantially transverse to said axis (30a),—a turbomachine sparkplug (150),—a device (130) for radially securing the sparkplug (150), which device (130) comprises a sparkplug adapter (160) fixed toward a first end to the outer casing (110), facing the second opening (110a) and through which adapter and casing the sparkplug (150) in question passes, and a sparkplug guide (190) kept in contact with the external longitudinal wall (90), facing the first opening (90a) and through which the sparkplug (150) passes to emerge in the combustion chamber (30), the sparkplug (150) and the sparkplug guide (190) each having a screw thread (103, 105), the screw threads (103, 105) being screwed together so as to stabilize the sparkplug (150) radially to the axis (30a) of the combustion chamber (30) with respect to said external longitudinal wall (90), and—in this condition, the sparkplug (150) and the sparkplug guide (190) are mounted freely with respect to the outer casing (110) in a direction substantially radial to the axis of the second opening (110a).

公开(公告)号：US09995219B2

公开(公告)日：2018-06-12

申请号：US14716020

申请日：2015-05-19

Applicant: SNECMA

Inventor： Francois Leglaye ,  Sylvain Oblaza ,  Patrick Lutz

IPC: F02C3/04 ,  F02C7/18 ,  F01D5/18 ,  F02K1/82 ,  F02K9/40 ,  F02K9/64 ,  F23R3/00 ,  F23R3/04 ,  F23R3/06

CPC classification number: F02C7/18 ,  F01D5/186 ,  F02K1/822 ,  F02K9/40 ,  F02K9/64 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/04 ,  F23R3/06 ,  F23R2900/00019 ,  F23R2900/03041 ,  F23R2900/03042

Abstract: A turbine engine wall having a cold side and a hot side and including a plurality of cooling orifices for enabling air flowing on the cold side of the wall to penetrate to the hot side at least some of the cooling orifices being plugged by a plugging material so as to define a minimum level of porosity for the wall corresponding to putting the turbine engine into service, and the plugged cooling orifices being suitable for being unplugged progressively throughout the lifetime of the turbine engine in order to define a maximum level of porosity for the wall corresponding to an end of lifetime for the turbine engine, the plugging being performed by alternating at least one of the following rows or lines: circumferential rows, axial rows, diagonal lines, so as to lie in the range one-third to one-half of the maximum porosity.

公开(公告)号：US20150047356A1

公开(公告)日：2015-02-19

申请号：US14385867

申请日：2013-04-09

Applicant: SNECMA

Inventor： Francois Leglaye ,  Emeric D'Herbigny

IPC: F01D11/00 ,  F23R3/00

CPC classification number: F01D11/005 ,  F01D9/023 ,  F05D2240/57 ,  F05D2250/37 ,  F23R3/002 ,  Y02T50/671 ,  Y02T50/675

Abstract: A turbine engine, a turbojet, or a turboprop engine, including an annular combustion chamber defined by an inner shell and an outer shell, a turbine distributor arranged downstream of the combustion chamber, with a downstream end of the outer shell and/or of the inner shell of the chamber including a radial rim arranged opposite a radial rim of an upstream end of the distributor, a sealing mechanism including at least one strip extending between the rims to provide a seal between the combustion chamber and the distributor. The sealing strip extends axially and circumferentially between the rims and bears sealingly against free ends of the rims.

Abstract translation: 涡轮发动机，涡轮喷气发动机或涡轮螺旋桨发动机，包括由内壳和外壳限定的环形燃烧室，布置在燃烧室下游的涡轮分配器，外壳的下游端和/ 所述室的内壳包括与所述分配器的上游端的径向边缘相对的径向边缘，密封机构，包括在所述边缘之间延伸的至少一个条，以在所述燃烧室和所述分配器之间提供密封。 密封条在轮缘之间轴向和周向延伸，并且密封地抵靠轮缘的自由端。

公开(公告)号：US20160369701A1

公开(公告)日：2016-12-22

申请号：US15106162

申请日：2014-11-26

Applicant: Snecma

Inventor： Pierre-Francois Simon Paul Pireyre ,  Francois Leglaye ,  David Gino Stifanic

IPC: F02C7/266 ,  H01T13/08 ,  F02C3/14 ,  F23R3/00 ,  F23R3/28 ,  F23R3/10

CPC classification number: F02C7/266 ,  F02C3/14 ,  F05D2220/32 ,  F05D2240/35 ,  F23D2207/00 ,  F23D2209/00 ,  F23D2211/00 ,  F23R3/002 ,  F23R3/10 ,  F23R3/28 ,  F23R3/60 ,  F23R2900/00005 ,  F23R2900/00012 ,  H01T13/08

Abstract: Assembly comprising, on a turbomachine:—a combustion chamber (30) having a longitudinal axis (30a) and comprising: internal and external longitudinal walls (90) having a first opening (90a) substantially transverse to said axis (30a), an outer casing (110) having a second opening (110a) likewise substantially transverse to said axis (30a),—a turbomachine sparkplug (150),—a device (130) for radially securing the sparkplug (150), which device (130) comprises a sparkplug adapter (160) fixed toward a first end to the outer casing (110), facing the second opening (110a) and through which adapter and casing the sparkplug (150) in question passes, and a sparkplug guide (190) kept in contact with the external longitudinal wall (90), facing the first opening (90a) and through which the sparkplug (150) passes to emerge in the combustion chamber (30), the sparkplug (150) and the sparkplug guide (190) each having a screw thread (103, 105), the screw threads (103, 105) being screwed together so as to stabilize the sparkplug (150) radially to the axis (30a) of the combustion chamber (30) with respect to said external longitudinal wall (90), and—in this condition, the sparkplug (150) and the sparkplug guide (190) are mounted freely with respect to the outer casing (110) in a direction substantially radial to the axis of the second opening (110a).

Abstract translation: 在涡轮机上包括： - 具有纵向轴线（30a）的燃烧室（30），并且包括：具有基本上横向于所述轴线（30a）的第一开口（90a）的内部和外部纵向壁（90） 壳体（110）具有同样基本上横向于所述轴线（30a）的第二开口（110a）， - 涡轮机火花塞（150）， - 用于径向固定所述火花塞（150）的装置（130），所述装置 面向第二开口（110a）的朝向第一端固定到外壳（110）的火花塞适配器（160）以及通过其中的火花塞（150）的适配器和壳体通过的火花塞引导件（190）保持在 与外部纵向壁（90）接触，面向第一开口（90a）并且火花塞（150）通过其在燃烧室（30）中出现，火花塞（150）和火花塞引导件（190）各自具有 一个螺纹（103,105），螺纹（103,105）被拧在一起 以便相对于所述外部纵向壁（90）将所述火花塞（150）径向地稳定到所述燃烧室（30）的轴线（30a），并且在该状态下，所述火花塞（150）和所述火花塞引导件 190）相对于外壳（110）沿与第二开口（110a）的轴线基本上径向的方向自由地安装。

公开(公告)号：US09413141B2

公开(公告)日：2016-08-09

申请号：US13861825

申请日：2013-04-12

Applicant: SNECMA

Inventor： Francois Leglaye ,  Jean-Francois Cabre ,  David Gino Stifanic

IPC: F02C7/266 ,  H01T13/16 ,  H01T13/20

CPC classification number: H01T13/16 ,  F02C7/266 ,  H01T13/20

Abstract: A spark plug for combustion chamber of a gas turbine engine including: an external body forming ground electrode, intended to be received mainly in a bypass of the combustion chamber; an internal central electrode; and an interposed insulator with clearance between the external body and the internal electrode, is provided. The spark plug terminates in a nose forming portion to be received in the flame tube of the chamber of the combustion chamber, and a semi-conductor element being interposed between the central electrode and the ground electrode at the level of said nose forming portion. The external body includes at least one cooling air inlet which communicates inside the spark plug with at least one outlet arranged at the level of the nose forming portion.

Abstract translation: 一种燃气涡轮发动机的燃烧室用火花塞，其特征在于，具有主要形成在所述燃烧室的旁路中的接地电极的外部主体， 内部中心电极; 并且提供了在外部主体和内部电极之间具有间隙的插入绝缘体。 火花塞终止在鼻部形成部分中，以容纳在燃烧室的腔室的火焰管中，并且在所述鼻部形成部分的水平处插入在中心电极和接地电极之间的半导体元件。 外部主体包括至少一个在火花塞内部连通的冷却空气入口和布置在鼻部形成部分的高度处的至少一个出口。