FR2538507A1 - Ablation lining for combustion chamber walls - Google Patents

Ablation lining for combustion chamber walls Download PDF

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Publication number
FR2538507A1
FR2538507A1 FR8320374A FR8320374A FR2538507A1 FR 2538507 A1 FR2538507 A1 FR 2538507A1 FR 8320374 A FR8320374 A FR 8320374A FR 8320374 A FR8320374 A FR 8320374A FR 2538507 A1 FR2538507 A1 FR 2538507A1
Authority
FR
France
Prior art keywords
combustion chamber
mat
wall
ablation
spraying
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
FR8320374A
Other languages
French (fr)
Other versions
FR2538507B1 (en
Inventor
Peter Goedtke
Heinz Huber
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Publication of FR2538507A1 publication Critical patent/FR2538507A1/en
Application granted granted Critical
Publication of FR2538507B1 publication Critical patent/FR2538507B1/en
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
    • B23K35/24—Selection of soldering or welding materials proper
    • B23K35/30—Selection of soldering or welding materials proper with the principal constituent melting at less than 1550 degrees C
    • B23K35/3033—Ni as the principal constituent
    • B23K35/304—Ni as the principal constituent with Cr as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/34—Casings; Combustion chambers; Liners thereof
    • F02K9/346—Liners, e.g. inhibitors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • F02K9/974—Nozzle- linings; Ablative coatings

Abstract

A woven or nonwoven mat along the inside of the combustion chamber of aircraft turbines is intermixed with ablation material and is fixed or plasma spraying to the walls. The mat is made of stainless steel mesh with a wire thickness of 20-200 microns. The area where the sprayed jet impinges can be cooled by a cold gas stream. This procedure does not result in such high temperatures that the properties of the wall material are changed. The adhesion of the finished lining withstands the high temperatures of over 2000K.

Description

Procédé pour la fabrication d'une couche
d'ablation traversée par un mat
L'invention se rapporte à un procédé pour la fabrication d'une couche d'ablation traversée par an mat tissé ou non tissé sur la face interne de la paroi d'une chambre de combustion d'un propulseur d'avion, procédé dans lequel on relie le mat à la paroi de la chambre de combustion, après quoi on applique le matériau d'ablation sur la parsi de la chambre de combustion revêtue du mat.Method for manufacturing a layer
ablation crossed by a mat
The invention relates to a method for manufacturing an ablation layer traversed by a woven or non-woven mat on the internal face of the wall of a combustion chamber of an aircraft thruster, method in which the mat is connected to the wall of the combustion chamber, after which the ablation material is applied to the parsi of the combustion chamber coated with the mat.

Un tel procédé figure dans la demande de brevet allemand P 31 20 902.5-45, Dans cette demande de brevet, à travers les mailles du mat, on enfile une spirale de fil métallique que lton met au contact de la paroi de la chambre de combustion et que l'on relie à celle-ci au moyen d'un brasage à point de fusion élevé,
La paroi de la chambre de combustion est réalisée en des matériaux à haute résistance, par exemple en tube d'acier façonné à froid. Un traitement thermique ultérieur de la paroi de la chambre de combustion à des températures telles qu'on les utilise pour le brasage avec une brasure å haut point de fusion, provoque toutefois presque inévitablement une modification des caractéristiques du matériau, c'est-à-dire une certaine diminution de la résistance.Par ailleurs, les températures, en particulier dans la chambre de postcombustion d'un statoréacteur, peuvent dépasser 20000 Kelvin.Such a process appears in the German patent application P 31 20 902.5-45. In this patent application, through the meshes of the mat, a wire spiral is threaded which is brought into contact with the wall of the combustion chamber. and which is connected to it by means of a high melting point brazing,
The wall of the combustion chamber is made of high resistance materials, for example cold formed steel tube. Subsequent heat treatment of the wall of the combustion chamber at temperatures such as are used for brazing with high melting point brazing, however, almost inevitably causes a change in the characteristics of the material, i.e. say a certain decrease in resistance. Furthermore, temperatures, especially in the afterburner chamber of a ramjet, can exceed 20,000 Kelvin.

Des températures aussi élevées entraînent cependant une détérioration des joints brasés.However, such high temperatures cause deterioration of the brazed joints.

Pour la fixation sur la paroi de la chambre de combustion d'un mat traversant la couche d'ablation, la présente invention a par conséquent pour objet de mettre au point un procédé dans lequel il n'intervienne aucune température entrainant une modification des caractéristiques du matériau de la paroi de la chambre de combustion et qui assure eiitre le mat #et la paroi de la chambre de combustion une liaison qui résiste aux très hautes températures,
L'invention sera mieux comprise à l'aide de la deacription d'un mode de réalisation pris comme exemple, mais non limitatif, et illustré schématiquement par le dessin annexé, sur lequel
la figure 1 est une vue en coupe d'une couche d'ablation
la figure 2 représente à une échelle agrandie un détail de la couche selon la figure 1 pendant la pulvérisation au pistolet et avant l'application du matériau d'ablation.For the attachment to the wall of the combustion chamber of a mat passing through the ablation layer, the present invention therefore aims to develop a process in which there is no temperature intervention leading to a modification of the characteristics of the material of the wall of the combustion chamber which provides the mat # and the wall of the combustion chamber a bond which resists very high temperatures,
The invention will be better understood using the description of an embodiment taken as an example, but not limiting, and illustrated diagrammatically by the appended drawing, in which
Figure 1 is a sectional view of an ablation layer
Figure 2 shows on an enlarged scale a detail of the layer according to Figure 1 during spraying with a spray gun and before the application of the ablation material.

Selon la figure 1, sur la face interne de la paroi 1 de la chambre de combustion est disposé un mat 2 qui traverse la section, tournée vers la paroi i de la chambre de combustion, d'une couche d'ablation 3. According to FIG. 1, on the internal face of the wall 1 of the combustion chamber is disposed a mat 2 which crosses the section, facing the wall i of the combustion chamber, of an ablation layer 3.

La paroi 1 de la chambre de combustion est réalisée en acier à haute résistance. Le mat 2 est réalisé en un tissu lâche de fil métallique qui est constitué par un réseau 2' à partir duquel des boucles 2" relativement longues s'écartent' des deux côtés radialement vers l'intérieur et vers l'extérieur. The wall 1 of the combustion chamber is made of high-strength steel. The mat 2 is made of a loose fabric of metal wire which is constituted by a network 2 ′ from which relatively long loops 2 ″ separate from the two sides radially inward and outward.

De préférence, le mat 2 est en acier inoxydable qui présente une conductibilité thermique relativement faible de façon que le transfert de chaleur du mat -2 à la paroi 1 de la chambre de combustion soit réduit lors de la pulvérisation au pistolet. La hauteur du tissu ou du mat 2 doit être aussi grande que possible et est par exemple d'environ 2 à 5 mm. Preferably, the mat 2 is made of stainless steel which has a relatively low thermal conductivity so that the heat transfer from the mat -2 to the wall 1 of the combustion chamber is reduced during spraying with a spray gun. The height of the fabric or the mat 2 should be as large as possible and is for example about 2 to 5 mm.

L'épaisseur du fil dont est fabriqué le mât 2 est de 20 à 200 item. En cas d'épaisseur trop faible du fil métallique, le tissu est détruit lors de la pulvérisation de plasma,
lu lieu d'acier, le mat 2 peut aussi etre réalisé en un autre matériau, par exemple en fibres céramiques. Ces dernières sont même particulièrement intéressantes on raison de leur faible conductibilité thermique.The thickness of the wire from which mast 2 is made is 20 to 200 items. If the metal wire is too thin, the tissue is destroyed when plasma is sprayed,
lu place of steel, the mat 2 can also be made of another material, for example ceramic fibers. The latter are even particularly interesting due to their low thermal conductivity.

Comme matériau pour la couche d'abla#tion 3, on peut utiliser des résines silicones mélangées à des matériaux de remplissage en forme Je fibres et de poudre, par exemple du méthylphénylsilicone mélangé de poudre ou de fibres de quartz, de même que des résines phénoliques ou autres matériaux d'ablation usuels. As the material for the ablation layer 3, silicone resins mixed with fiber and powdered filler materials, for example methylphenylsilicone mixed with quartz powder or fibers, as well as resins can be used. phenolics or other common ablation materials.

La liaison du mat 2 sur la paroi 1 de la chambre de combustion s'effectue par pulvérisation au pistolet. La pulvérisation de plasma s'est révélée particulièrement avantageuse à cet égard. Un pistolage à la flamme ou un autre procédé de pulvérisation au pistolet est toutefois également possible. The mat 2 is connected to the wall 1 of the combustion chamber by spraying with a gun. Plasma spraying has been found to be particularly advantageous in this regard. However, flame spraying or another spraying method is also possible.

La pulvérisation de plasma s'effectue dans des conditions normales. Comme poudre de pulvérisation de plasma, on peut envisager par exemple des alliages nickel-chrome ou d'autres alliages à haute caractéristique d'adhérence. Comme gaz de plasma on peut par exemple utiliser un mélange hydrogène azote ou hydrogène-argon. The plasma spraying is carried out under normal conditions. As plasma spraying powder, it is possible, for example, to consider nickel-chromium alloys or other alloys with a high adhesion characteristic. As plasma gas, it is possible, for example, to use a hydrogen nitrogen or hydrogen-argon mixture.

La pulvérisatiou au pistolet, c'est-a-dire en particulier la pulvérisation de plasma,présente l'avantage que la paroi de la chambre de combustion n'est pas chaufféeà des températures suffisamment élevées pour que des modifications des caractéristiques du matériau soient à craindre. Spraying with a spray gun, that is to say in particular plasma spraying, has the advantage that the wall of the combustion chamber is not heated to sufficiently high temperatures that changes in the characteristics of the material are possible. to fear.

Les différentes particules pulvérisées 5 ne renferment en-effet qu'une petite quantité de chaleur grâce à leur faible masse. On peut même commander le chauffage de la paroi 1 de la chambre de combustion de façon simple par un mouvement de va-et-vient exécuté à une vitesse appropriée du pistolet de pulvérisation de plasma. The various pulverized particles 5 in fact contain only a small amount of heat due to their low mass. It is even possible to control the heating of the wall 1 of the combustion chamber in a simple manner by a back-and-forth movement executed at an appropriate speed of the plasma spray gun.

Sur le pistolet de pulvérisation, on peut en plus prévoir des buses-disposées dans le sens de la pulvérisation et par lesquelles un courant de gaz froid est projeté lors de la pulvérisation. On the spray gun, it is also possible to provide nozzles-arranged in the direction of spraying and through which a stream of cold gas is projected during spraying.

Les particules pulvéri#s 5 forment une couche 4 qui adhère à la paroi 1 de la chambre de combustion et qui lie d'une certaine façon la zone des fils métalliques du mat 2, qui est voisine de la paroi 1 de la chambre de combustion (figure 2). The pulverized particles # s 5 form a layer 4 which adheres to the wall 1 of the combustion chamber and which in a certain way binds the zone of the metallic wires of the mat 2, which is close to the wall 1 of the combustion chamber (figure 2).

La partie des particules 5, qui lors de la pulvérisation n'atteint pas la paroi 1 de la chambre de combustion et reste suspendue dans le mat 2 à distance de cette paroi 1, assure un raidissement du mat 2 et par conséquent une augmentation de la rigidité de la couche d'ablation 3.  The part of the particles 5, which during spraying does not reach the wall 1 of the combustion chamber and remains suspended in the mat 2 at a distance from this wall 1, ensures a stiffening of the mat 2 and therefore an increase in the stiffness of the ablation layer 3.

On introduit le matériau d'ablation par centri fugation sous forme de dispersion dans la chambre de combustion tournante raccordée au màt 2 par pulvérisation au pistolet, puis on le laisse durcir. The ablation material is introduced by centrifugation in the form of a dispersion into the rotary combustion chamber connected to the mast 2 by spraying with a gun, then it is left to harden.

Comme on l'a constaté par des essais, la force d'adhérence de la couche 4 de pulvérisation de plasma sur la paroi 1 de la chambre de combustion est de 30-40 N/m2.  As has been observed by tests, the adhesive strength of the plasma spraying layer 4 on the wall 1 of the combustion chamber is 30-40 N / m2.

Claims (4)

REVENDICATIONS 1. Procédé pour la fabrication d'une couche d'ablation traversée par un mat tissé ou non tissé sur la face interne de la paroi d'une chambre de combustion d'un propulseur d'avion, procédé dans lequel on relie le-mat à la paroi de la chambre de combustion, après quoi on applique le matériau d'ablation sur la paroi de la chambre de combustion revêtue du mat, carat trissé par le fait que l'on relie le mat à la paroi de la chambre de combustion par pulvérisation au pistolet. 1. Method for the manufacture of an ablation layer traversed by a woven or nonwoven mat on the internal face of the wall of a combustion chamber of an aircraft thruster, method in which the mat is connected to the wall of the combustion chamber, after which the ablation material is applied to the wall of the combustion chamber coated with the mat, carat woven by the fact that the mat is connected to the wall of the combustion chamber by spraying with a spray gun. 2. Procédé selon la revendication 1, caractérisé par le fait que la pulvérisation au pistolet est une pulvérisation de plasma. 2. Method according to claim 1, characterized in that the spraying with a spray gun is a plasma spraying. 3. Procédé selon la revendication 1 ou 2, caractérisé par le fait quellors de la pulvérisation, on refroidit par un courant de gaz la zone de la paroi de la chambre de combustion, qui est atteinte par le jet de particules. 3. Method according to claim 1 or 2, characterized in that during the spraying, the area of the wall of the combustion chamber is cooled by a stream of gas, which is reached by the jet of particles. 4. Procédé selon l'une quelconque des revendications 1 à 3, caractérisé par le fait que le mat est réalisé en un tissu de fil métallique en acier inoxydable d'une épaisseur de 20 à 200 pm.  4. Method according to any one of claims 1 to 3, characterized in that the mat is made of a wire fabric of stainless steel with a thickness of 20 to 200 µm.
FR8320374A 1982-12-22 1983-12-20 PROCESS FOR THE MANUFACTURE OF AN ABLATION LAYER CROSSED BY A MAT Expired FR2538507B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE3247414A DE3247414C2 (en) 1982-12-22 1982-12-22 Process for the production of an ablation layer interspersed with a mat

Publications (2)

Publication Number Publication Date
FR2538507A1 true FR2538507A1 (en) 1984-06-29
FR2538507B1 FR2538507B1 (en) 1988-10-14

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2569237A1 (en) * 1984-08-14 1986-02-21 Aerospatiale THERMAL PROTECTION DEVICE RESISTANT TO ABLATION AND VIBRATION, AND METHOD OF MANUFACTURE
EP0769363A1 (en) * 1995-10-20 1997-04-23 AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE, Société Anonyme Thermal protection article made of low density reinforced material and process for its manufacture
DE19750517A1 (en) * 1997-11-14 1999-05-20 Asea Brown Boveri Heat shield
CN100547237C (en) * 2006-03-24 2009-10-07 陈世钟 Plasma recombination boosting turbine fan jet aerial engine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4132415C1 (en) * 1991-09-28 1993-03-04 Deutsche Aerospace Ag, 8000 Muenchen, De Ablate layer for combustion chamber walls of rocket propulsion appts. - comprises silicone resin with phenyl gp(s) as matrix, high melting filler and alkaline earth carbonate
DE19805402C2 (en) * 1998-02-11 2002-09-19 Deutsch Zentr Luft & Raumfahrt Method for the integral connection of components by means of a seam formed from connection material
CN109161889B (en) * 2018-07-19 2020-05-22 西安交通大学 Anti-sintering dual-mode composite structure thermal barrier coating and preparation process thereof

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FR1051405A (en) * 1950-11-07 1954-01-15 Birmingham Small Arms Co Ltd Porous metal objects
FR1186710A (en) * 1957-11-25 1959-08-31 Acetylene Dissous Du Sud Est Metal plastic compound
DE1160696B (en) * 1959-08-08 1964-01-02 Rheinmetall Gmbh Solid propellant for rockets
US3187503A (en) * 1962-05-01 1965-06-08 Bell Aerospace Corp Rocket engine construction
US3311013A (en) * 1963-01-09 1967-03-28 Aerojet General Co Propellant liner
US3427185A (en) * 1964-02-19 1969-02-11 United Aircraft Corp Composite structural material incorporating metallic filaments in a matrix,and method of manufacture
USB468330I5 (en) * 1974-05-09 1976-03-16
FR2506901A1 (en) * 1981-05-26 1982-12-03 Messerschmitt Boelkow Blohm ABLATION LAYER AND METHOD AND DEVICE FOR THE PRODUCTION THEREOF

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1051405A (en) * 1950-11-07 1954-01-15 Birmingham Small Arms Co Ltd Porous metal objects
FR1186710A (en) * 1957-11-25 1959-08-31 Acetylene Dissous Du Sud Est Metal plastic compound
DE1160696B (en) * 1959-08-08 1964-01-02 Rheinmetall Gmbh Solid propellant for rockets
US3187503A (en) * 1962-05-01 1965-06-08 Bell Aerospace Corp Rocket engine construction
US3311013A (en) * 1963-01-09 1967-03-28 Aerojet General Co Propellant liner
US3427185A (en) * 1964-02-19 1969-02-11 United Aircraft Corp Composite structural material incorporating metallic filaments in a matrix,and method of manufacture
USB468330I5 (en) * 1974-05-09 1976-03-16
FR2506901A1 (en) * 1981-05-26 1982-12-03 Messerschmitt Boelkow Blohm ABLATION LAYER AND METHOD AND DEVICE FOR THE PRODUCTION THEREOF

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Title
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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2569237A1 (en) * 1984-08-14 1986-02-21 Aerospatiale THERMAL PROTECTION DEVICE RESISTANT TO ABLATION AND VIBRATION, AND METHOD OF MANUFACTURE
EP0174886A1 (en) * 1984-08-14 1986-03-19 AEROSPATIALE Société Nationale Industrielle Thermal protecting device resistant to ablation and vibration, and production method therefor
US4655866A (en) * 1984-08-14 1987-04-07 Aerospatiale Societe Nationale Industrielle Device for thermal protection from ablation and vibrations and manufacturing method
EP0769363A1 (en) * 1995-10-20 1997-04-23 AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE, Société Anonyme Thermal protection article made of low density reinforced material and process for its manufacture
FR2740068A1 (en) * 1995-10-20 1997-04-25 Aerospatiale REINFORCED LOW DENSITY THERMAL PROTECTION MATERIAL AND METHOD OF OBTAINING SAME
US5882765A (en) * 1995-10-20 1999-03-16 Aerospatiale Societe Nationale Industrielle Element made of a reinforced low density heat protective material and method to obtain said element
DE19750517A1 (en) * 1997-11-14 1999-05-20 Asea Brown Boveri Heat shield
US6492034B1 (en) 1997-11-14 2002-12-10 Alstom Heat shield
CN100547237C (en) * 2006-03-24 2009-10-07 陈世钟 Plasma recombination boosting turbine fan jet aerial engine

Also Published As

Publication number Publication date
DE3247414A1 (en) 1984-06-28
FR2538507B1 (en) 1988-10-14
DE3247414C2 (en) 1986-10-23

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