公开(公告)号：US20140299654A1

公开(公告)日：2014-10-09

申请号：US14274926

申请日：2014-05-12

Applicant: AIRCELLE ,  SNECMA PROPULSION SOLIDE

Inventor： Hélène MALOT ,  Philippe Bienvenu ,  Frédéric Guichard ,  Olivier Drevet

IPC: B23K31/02 ,  B23K37/00

CPC classification number: B23K31/02 ,  B23K1/0014 ,  B23K3/087 ,  B23K37/00 ,  B23K2101/02

Abstract: A setup for assembling, by brazing, a composite panel including at least two parts separated by a filler material and joined together by brazing. The setup includes a furnace to achieve a brazing temperature for brazing the panel, and an assembly device which has a form having a shape similar to the final shape of the panel to be brazed. In particular, the assembly device further includes a pressing device to apply mechanical pressure to at least part of the surface of the panel in a direction allowing the panel to be permanently deformed into a shape which matches that of the form. The pressing device is moved under the action of a spring, and the forces applied by the spring being determined so that, at the brazing temperature, the spring applies the force necessary for deforming the panel against the form.

Abstract translation: 一种用于通过钎焊组装复合板的装置，所述复合板包括由填充材料分隔开并通过钎焊连接在一起的至少两个部分。 该装置包括实现钎焊板的钎焊温度的炉，以及具有与要钎焊的板的最终形状类似的形状的组装装置。 特别地，组装装置还包括一个加压装置，以在允许面板永久变形成与形状相匹配的形状的方向上对面板的至少部分表面施加机械压力。 挤压装置在弹簧的作用下移动，并且由弹簧施加的力被确定为使得在钎焊温度下弹簧施加使面板变形成形成所需的力。

公开(公告)号：US20040221941A1

公开(公告)日：2004-11-11

申请号：US10786409

申请日：2004-02-25

Applicant: SNECMA PROPULSION SOLIDE

Inventor： Eric Bouillon ,  Dominique Coupe ,  Remi Bouvier

IPC: B32B031/00

CPC classification number: B28B7/342 ,  B28B1/44 ,  C04B35/565 ,  C04B35/62863 ,  C04B35/62873 ,  C04B35/62884 ,  C04B35/806 ,  C04B38/0003 ,  C04B2235/5244 ,  C04B2235/5248 ,  F23M2900/05004 ,  F23R3/007 ,  F23R2900/00018 ,  Y02T50/67 ,  C04B35/52 ,  C04B38/068 ,  C04B35/83

Abstract: A fiber preform for constituting the fiber reinforcement of composite material is prepared and then consolidated by depositing sufficient matrix phase therein to bond the fibers together while not completely densifying the preform. Pins of rigid material are put into place through the consolidated preform and densification of the consolidated preform containing the pins is continued by depositing at least a ceramic matrix phase. Thereafter, at least a portion of each pin is eliminated so as to leave a calibrated perforation passing through the resulting part, the pins being made at least in part out of a material that can be eliminated by applying treatment that does not affect the ceramic material of the matrix.

Abstract translation: 制备用于构成复合材料的纤维增强材料的纤维预制件，然后通过在其中沉积足够的基质相来固化，以将纤维粘合在一起，同时不完全致密化预成型体。 通过固结的预成型件将刚性材料的销插入到位，并且通过沉积至少一个陶瓷基体相继续进行包含销的固化的预成型体的致密化。 此后，消除每个销的至少一部分，以便留下通过所得部件的经校准的穿孔，所述销至少部分由通过施加不影响陶瓷材料的处理而被消除的材料制成 的矩阵。

公开(公告)号：US20040194941A1

公开(公告)日：2004-10-07

申请号：US10765416

申请日：2004-01-27

Applicant: Snecma Propulsion Solide

Inventor： Jean-Michel Larrieu ,  Gilles Uhrig ,  Jacques Thebault ,  Clement Bouquet

IPC: F28F003/14

CPC classification number: F28F21/081 ,  F02K9/64 ,  F02K9/972 ,  F02K9/974 ,  F23R3/005 ,  F23R3/007 ,  F28D2021/0078 ,  F28F3/12

Abstract: The active cooling panel comprises a first part and a second part of thermostructural composite material, each having an inside face and an opposite outside face, the parts being assembled together by bonding their inside faces together, and channels being formed by indentations formed in the inside face of at least one of the first and second parts. The panel further includes a sealing layer bonded to at least one of the first and second parts and situated at a distance from the assembled-together inside faces thereof. The invention is applicable to making heat exchanger walls such as the walls for the combustion chambers of aircraft engines, or the diverging portions of rocket engines, or plasma confinement chambers in nuclear fusion reactors.

Abstract translation: 活性冷却板包括第一部分和第二部分的热结构复合材料，每个部分具有内表面和相对的外表面，这些部件通过将它们的内表面粘合在一起而组装在一起，并且通过形成在内部的凹陷形成的通道 第一和第二部分中的至少一个的面。 该面板还包括一个密封层，该密封层粘合到第一和第二部分中的至少一个并且与其组装在一起的内表面一定距离处。 本发明适用于制造热交换器壁，例如用于飞机发动机的燃烧室的壁，或火箭发动机的发散部分或核聚变反应堆中的等离子体限制室。

公开(公告)号：US20040144886A1

公开(公告)日：2004-07-29

申请号：US10648983

申请日：2003-08-27

Applicant: Snecma Propulsion Solide

Inventor： Philippe Le Helley ,  Louis Jacques ,  Christophe Magniere ,  Gilles Uhrig ,  Bernard Bondon ,  Jean-Claude Tricot ,  Didier Boury

IPC: F41G007/00

CPC classification number: F02K9/26 ,  F02K9/32

Abstract: The invention provides a system for passively controlling pressure oscillations of hydrodynamic origin in a solid propellant thruster comprising a body containing a charge of solid propellant, the system comprising at least one insert disposed in the thruster body transversely relative to the flow direction of the combustion gases of the solid propellant. The insert has an opening of non-axisymmetric shape so as to generate a three-dimensional effect on the flow and prevent axisymmetric turbulent modes from forming in the thruster. Thus, the control system of the invention serves to break the symmetry of the flow and thus prevents axisymmetric turbulence forming which is the source of instability that the present invention seeks to control. The present system is applicable to existing thrusters.