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Active cooling panel of thermostructural composite material and method for its manufacture

a composite material and active cooling technology, applied in the direction of engine cooling apparatus, combustion process, lighting and heating apparatus, etc., can solve the problems of limiting the capacity to cool the exposed surface, residual porosity of the thermostructural composite material, and unsuitable for use on its own

Inactive Publication Date: 2004-10-07
SNECMA PROPULSION SOLIDE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

0014] In one of its aspects, the invention seeks to provide an active cooling panel of thermostructural composite material that presents leaktightness which is effective and durable relative to a fluid flowing in internal passages of the panel.

Problems solved by technology

Whatever the densification method used, thermostructural composite materials present residual porosity so they are unsuitable for use on their own in forming cooling panels having internal fluid-conveying passages, since the walls of such passages are not leakproof.
In addition, the length of the path along which heat travels through the graphite plate and the metal plate puts a limit on capacity to cool the exposed surface.
The second and third solutions are satisfactory in terms of mass and of shortening heat flow path length, but leakage problems can arise due to the metal lining or the brazing cracking following repeated exposure to very high temperatures and excess stresses induced by the shape of the channels.

Method used

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  • Active cooling panel of thermostructural composite material and method for its manufacture
  • Active cooling panel of thermostructural composite material and method for its manufacture
  • Active cooling panel of thermostructural composite material and method for its manufacture

Examples

Experimental program
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Effect test

first embodiment

[0045] an active cooling panel 10 is shown in FIGS. 1 to 3.

[0046] The panel 10 comprises two parts 20 and 30 that are generally in the form of rectangular parallelepipeds and that are assembled to each other via their inside faces 21 and 31. In this example, assembly is performed by brazing 12. The part 20 whose outside face 22 opposite from its face 21 defines the front face of the panel that is to be exposed to high temperatures or to intense heat flow is made of a thermostructural composite material. Channels 24 for circulating a cooling fluid are formed by indentations formed in the inside face 21. A plurality of channels 24 parallel to two opposite sides of the panel 10 extend between two manifolds 40, 42 that are internal to the panel 10 and that are situated close to two other opposite sides thereof.

[0047] The part 30 comprises two portions 34 and 36 in the form of plates made of thermostructural composite material. The portions 34 and 36 are assembled via facing faces 35, 37...

example

[0099] A part 20 and portions 34, 36 of the kind shown for the embodiment of FIGS. 1 to 3 have been made out of C / SiC thermostructural composite material, with the channels and the manifolds being formed by machining.

[0100] The porosity of the inside surfaces 21, 31 was reduced by brushing thereon a composition containing an SiC powder of mean grain size equal to about 9 microns (.mu.m) in a solution of PCS in xylene. After drying in air, the PCS was cross-linked at about 350.degree. C. and then transformed into SiC by raising the temperature to about 900.degree. C. A thin coating of SiC having thickness equal to about 100 .mu.m was then deposited by chemical vapor infiltration, said coating then being formed over the entire outside surface of the part 20 and the portion 34, and not only on the inside faces 21 and 31. In combination with the residue of ceramizing the PCS in association with the SiC powder, the SiC coating contributes to effective reduction of porosity.

[0101] The fac...

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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.

Description

[0001] The present invention relates to an active cooling panel of thermostructural composite material.[0002] The term "active cooling panel" is used herein to mean a panel having a cooling fluid passing therethrough for the purpose of taking away the heat received by the panel being exposed to high temperature or high heat flux.[0003] The term "thermostructural composite material" is used herein to mean a composite material having mechanical properties which make it suitable for constituting structural elements and having the ability to conserve these mechanical properties at high temperature. Thermostructural composite materials are typically carbon-carbon (C / C) type composite material comprising a reinforcing structure made of carbon fibers densified by a matrix of carbon, and ceramic matrix composite (CMC) materials comprising a reinforcing structure of refractory fibers (in particular carbon fibers or ceramic fibers) densified by a ceramic matrix.[0004] Applications of the inve...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D5/28B23K20/00B23K103/16C04B37/00C04B41/88F02C7/00F02C7/18F02C7/28F02K9/34F02K9/64F02K9/97F23R3/00F23R3/42F28F3/12F28F21/08
CPCF02K9/64F02K9/972F02K9/974F23R3/005F23R3/007F28D2021/0078F28F3/12F28F21/081Y02E30/10
Inventor LARRIEU, JEAN-MICHELUHRIG, GILLESTHEBAULT, JACQUESBOUQUET, CLEMENT
Owner SNECMA PROPULSION SOLIDE
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