Availableonlineatwww.sciencedirect.com BCIENGE DIRECT ACTA ASTRONAUTUGA PERGAMON Acta Astronautica 55(2004)409-420 www.elsevier.comlocate/actaastro Advanced ceramic matrix composite materials for current and future propulsion technology applications S Schmidt,*, S. Beyer, H. Knabe, H. Immicha, R. Meistring, A Gessler- a EADS-Space T ation, Munich, German EADS Domier Research and Technology, Friedrichshafen, Germany eEADS Corporate Research Centre, Munich, Germany Abstract Current rocket engines, due to their method of construction, the materials used and the extreme loads to which they are subjected, feature a limited number of load cycles. Various technology programmes in Europe are concerned, besides developing reliable and rugged, low cost, throwaway equipment, with preparing for future reusable propulsion technologies. One of the key roles for realizing reusable engine omponents is the use of modern and innovative materials. One of the key technologies which concern various engine manufacturers worldwide is the development of fibre-reinforced ceramics--ceramic matrix composites. The advantages for the developers are obvious--the low specific weight, the high specific strength over a large temperature range, and their great damage tolerance compared to monolithic ceramics make this material class extremely interesting as a construction material. Over the past years, the Astrium company(formerly DASA)has, together with various partners, worked intensively on developing components for hypersonic engines and liquid rocket propulsion systems. In the year 2000, various hot-firing ests with subscale(scale 1: 5)and full-scale nozzle extensions were conducted. In this year, a further decisive milestone was achieved in the sector of small thrusters, and long-term tests served to demonstrate the extraordinary stability of the C/sic material Besides developing and testing radiation-cooled nozzle components and small-thruster combustion chambers, Astrium worked on the preliminary development of actively cooled structures for future reusable propulsion systems. In order to get one step nearer to this objective, the development of a new fibre composite was commenced within the framework of a regionally sponsored programme. The objective here is to create multidirectional (3D) textile structures combined with a cost-effective infiltration process. Besides material and process development, the project also encompasses the development of special metal/ceramic and ceramic/ceramic joining techniques as well as studying and verifying non destructive investigation processes for the purpose of testing components c 2004 Published by Elsevier Ltd 1. Introduction diflerent propulsion concepts, the advanced develop- ment of reliable"throwaway items"paying special Within the scope of the national technology pro- attention to the main aspect of low cost, and prepa gramme ASTRA, work is being carried out on two ration for future reusable propulsion technologies for multiple use(30-50 launches). Apart from cutting manufacturing times and costs for" throwaway items for commercial launcher propulsion systems, one of 0094-5765/S-see front matter 2004 Published by Elsevier Ltd. doi:10.1016 ]. actaastro.200405.052
Acta Astronautica 55 (2004) 409 – 420 www.elsevier.com/locate/actaastro Advanced ceramic matrix composite materials for current and future propulsion technologyapplications S. Schmidta;∗, S. Beyera, H. Knabeb, H. Immicha, R. Meistringc, A. Gesslerc aEADS-Space Transportation, Munich, Germany bEADS Dornier Research and Technology, Friedrichshafen, Germany cEADS Corporate Research Centre, Munich, Germany Abstract Current rocket engines, due to their method of construction, the materials used and the extreme loads to which theyare subjected, feature a limited number of load cycles. Various technologyprogrammes in Europe are concerned, besides developing reliable and rugged, low cost, throwaway equipment, with preparing for future reusable propulsion technologies. One of the keyroles for realizing reusable engine components is the use of modern and innovative materials. One of the keytechnologies which concern various engine manufacturers worldwide is the development of 3bre-reinforced ceramics—ceramic matrix composites. The advantages for the developers are obvious—the low speci3c weight, the high speci3c strength over a large temperature range, and their great damage tolerance compared to monolithic ceramics make this material class extremelyinteresting as a construction material. Over the past years, the Astrium company(formerlyDASA) has, together with various partners, worked intensivelyon developing components for hypersonic engines and liquid rocket propulsion systems. In the year 2000, various hot-3ring tests with subscale (scale 1:5) and full-scale nozzle extensions were conducted. In this year, a further decisive milestone was achieved in the sector of small thrusters, and long-term tests served to demonstrate the extraordinarystabilityof the C/SiC material. Besides developing and testing radiation-cooled nozzle components and small-thruster combustion chambers, Astrium worked on the preliminarydevelopment of activelycooled structures for future reusable propulsion systems. In order to get one step nearer to this objective, the development of a new 3bre composite was commenced within the framework of a regionallysponsored programme. The objective here is to create multidirectional (3D) textile structures combined with a cost-e;ective in3ltration process. Besides material and process development, the project also encompasses the development of special metal/ceramic and ceramic/ceramic joining techniques as well as studying and verifying non destructive investigation processes for the purpose of testing components. c 2004 Published byElsevier Ltd. 1. Introduction Within the scope of the national technologyprogramme ASTRA, work is being carried out on two ∗ Corresponding author. di;erent propulsion concepts, the advanced development of reliable “throwawayitems” paying special attention to the main aspect of low cost, and preparation for future reusable propulsion technologies for multiple use (30–50 launches). Apart from cutting manufacturing times and costs for “throwawayitems” for commercial launcher propulsion systems, one of 0094-5765/$ - see front matter c 2004 Published byElsevier Ltd. doi:10.1016/j.actaastro.2004.05.052
410 S. Schmidt et al./Acta Astronautica 55(2004)409-420 RLIO, built by Pratt Whitney, for the American launcher Delta ll Tarbert ear relaforredt Relics ICRP) System studies undertaken at Astrium as well as structural and thermal analyses promise, thanks to the use of CMCs in thrust chambers of liquid-propellant rocket engines, substantial advantages compared to metal materials, which are currently utilized for Cerami campsites most launcher propulsion systems for the cooled combustion-chamber structures and nozzle extensions The main advantages comprise on the one hand the possible weight reduction and on the other hand the 20040060080010001200140016001800IC high resistance to thermoshocks as well as the stability to chemical attack versus the liquid propellants used. A further significant advantage is the high creep re- Fig. 1. Ratio of strength to weight as a function of temperature [1]. sistance and the extraordinary resistance to high tem- multiaxis states of stress occurring in actively cooled the main challenges comprises implementing a high thrust chambers necessitate a fibre composite that fea- hrust-to-mass ratio, i. e. high thrust (performance) tures sufficient shear strength in as many directions with a low engine mass-kN/kg; this applies to isotropic behaviour. The currently G owaway items as well as to future propulsion sys- available 2-directional fibre composites would proba- ns. In particular, against the backdrop of reusable bly only have a very limited lifetime. For this reason, propulsion system components, modern and efficient some years ago the development of a new material materials for realizing new construction concepts will system and manufacturing process, respectively, was play a decisive role commenced, with the objective of combining multidi Since the early 1990s, the Astrium company has rectional(3D)textile structures with a cost-effective been working on a pacesetting key technology, filtration method. Besides material and process amely ceramic matrix composites(CMCs).An development, the focus is on the development of ive of of cmcs prises carbonfibre-reinforced silicon carbide(C/SiC), concepts as well as the verification of non-destructive which is made using the liquid polymer infiltration test methods (LPI) Process. Fig. I illustrate the excellent ratio of Due to the above advantages inherent in ceramic rength to weight, in particular at high temperatures, fibre composites, currently engine manufacturers and compared to currently utilized metal materials, is research institutes are stepping up their activities just one special feature that makes it attractive as a geared towards the use of ceramics in rocket-engine construction material [1] thrust-chamber components In view of the extreme In the sector of space propulsion systems, to date thermomechanical loads in the combustion chamber ceramic fibre composites have been used primarily of liquid-propellant rocket engines, previous devel for radiation-cooled nozzle extensions and combustion opments concentrated above all on the use of ceramic chambers for small thrusters; the advantage here lies fibre composites in the less thermally loaded noz n the low specific weight (lightweight construction), zle extensions [1]. At Astrium, nozzle extensions dispensing with active cooling and at the same time have been developed to date made of C/Sic for the high service temperatures upper-stage engine AESTUS and successfully tested To date, the high temperature, lightweight mate- on the altitude test bench P4. 1 at DLR in Lampold rial has become an established material in particular hausen. A subscale nozzle on the scale of 1: 5 for the for nozzle extensions. Currently, commercial car- Ariane 5 main engine Vulcain was made of C/SiC and bon/carbon nozzles, manufactured by Snecma in also successfully tested on the research test bench P8 France, are being used for the upper-stage engine at DLR in Lampoldshausen at combustion-chamber
410 S. Schmidt et al. /Acta Astronautica 55 (2004) 409 – 420 Fig. 1. Ratio of strength to weight as a function of temperature [1]. the main challenges comprises implementing a high thrust-to-mass ratio, i.e. high thrust (performance) with a low engine mass—kN/kg; this applies to throwawayitems as well as to future propulsion systems. In particular, against the backdrop of reusable propulsion system components, modern and eIcient materials for realizing new construction concepts will playa decisive role. Since the early1990s, the Astrium companyhas been working on a pacesetting keytechnology, namelyceramic matrix composites (CMCs). An interesting representative of the group of CMCs comprises carbon3bre-reinforced silicon carbide (C/SiC), which is made using the liquid polymer in3ltration (LPI) Process. Fig. 1 illustrate the excellent ratio of strength to weight, in particular at high temperatures, compared to currentlyutilized metal materials, is just one special feature that makes it attractive as a construction material [1]. In the sector of space propulsion systems, to date ceramic 3bre composites have been used primarily for radiation-cooled nozzle extensions and combustion chambers for small thrusters; the advantage here lies in the low speci3c weight (lightweight construction), dispensing with active cooling and at the same time high service temperatures. To date, the high temperature, lightweight material has become an established material in particular for nozzle extensions. Currently, commercial carbon/carbon nozzles, manufactured bySnecma in France, are being used for the upper-stage engine RL10, built byPratt & Whitney, for the American launcher Delta III. System studies undertaken at Astrium as well as structural and thermal analyses promise, thanks to the use of CMCs in thrust chambers of liquid-propellant rocket engines, substantial advantages compared to metal materials, which are currentlyutilized for most launcher propulsion systems for the cooled combustion-chamber structures and nozzle extensions. The main advantages comprise on the one hand the possible weight reduction and on the other hand the high resistance to thermoshocks as well as the stability to chemical attack versus the liquid propellants used. A further signi3cant advantage is the high creep resistance and the extraordinaryresistance to high temperatures compared to metal materials. However, the multiaxis states of stress occurring in activelycooled thrust chambers necessitate a 3bre composite that features suIcient shear strength in as manydirections as possible, i.e. isotropic behaviour. The currently available 2-directional 3bre composites would probablyonlyhave a verylimited lifetime. For this reason, some years ago the development of a new material system and manufacturing process, respectively, was commenced, with the objective of combining multidirectional (3D) textile structures with a cost-e;ective in3ltration method. Besides material and process development, the focus is on the development of metal/ceramic joining techniques, engine analyses and concepts as well as the veri3cation of non-destructive test methods. Due to the above advantages inherent in ceramic 3bre composites, currentlyengine manufacturers and research institutes are stepping up their activities geared towards the use of ceramics in rocket-engine thrust-chamber components. In view of the extreme thermomechanical loads in the combustion chamber of liquid-propellant rocket engines, previous developments concentrated above all on the use of ceramic 3bre composites in the less thermallyloaded nozzle extensions [1]. At Astrium, nozzle extensions have been developed to date made of C/SiC for the upper-stage engine AESTUS and successfullytested on the altitude test bench P4.1 at DLR in Lampoldshausen. A subscale nozzle on the scale of 1:5 for the Ariane 5 main engine Vulcain was made of C/SiC and also successfullytested on the research test bench P8 at DLR in Lampoldshausen at combustion-chamber
S. Schmidt et al./ Acta Astronautica 55(2004)409-420 411 ==冒 Fig. 3. 5-axis winding machines. Fig. 2. CMC production by infiltration and pyrolysis of polymers 2. 2. Production capabilities pressures of up to 80 bars. Further, very success- ful test campaigns with radiation-cooled combustion Based on the current production by EADS in chambers were carried out in the small-thruster sec Friedrichshafen of carbon fibre reinforced plastics tor, whereby the material was able to demonstrate its (CFRP)for the protective payload fairing of Ariane 5 (Speldra and Syldra), liquid-polymer infiltration was versus the propellants and combustion products developed by DaimlerChrysler Research for, amongst other things, space components, hot structures, and 2. Manufacturing, process technique and non re-entry technologies destructive investigation (NDD) methods In order to build axisymmetric components such as nozzle extensions. combustion chambers, etc 2. LP- two 5-axis winding machines with dimensions 3200×10,000mm2and2000×5000mm2(Fig.3) mer route. The coated C-fibre bundle is impregnated sions 500/800 x 5000 mm? machines with dimen- The C/SiC is made as shown in Fig. 2 via the poly- as well as two 4-axis windi with a powder-filled polymer and laminated to form are available, in particular for 3D components prepregs Analogously to the manufacturing technique For the autoclave hardening of the components for fibre-reinforced plastics, the structure is laminated, order to provide them with the so-called green body, compacted in an autoclave and cross linked, and then various autoclaves are available for smaller compo- pyrolized without pressure and without moulding nents(1000 x 3000 mm")as well as for large-space tools at temperatures of 1300-1900 K in inert ga structures(3500 x 8500 mm2)in the Friedrichshafen For further compacting(depending on the desired production centre(Fig 4) porosity ) re-impregnation is effected with a suitable For high-temperature treatment, two pyrolysis polymer followed by pyrolysis. The component may furnaces for component sizes of up to 2.5 m in diame- then be coated optionally with an protection layer ter and 3 m in height are available(the Munich-based hanks to the consistent advanced development ECM company ) of the LPI Route over the past years, using a ew reinfiltration polymer permitted reducing the 2.3. NDI methods re-impregnation cycles by 50% while retaining the mechanical strength characteristics. Conse- In view of, compared to metals, significantly ly, it was possible to cut the production costs, in anisotropic ceramic composite structure, the non- icular for large-scale structures, by approx. 25% destructive testing of C/SiC components already
S. Schmidt et al. /Acta Astronautica 55 (2004) 409 – 420 411 Fig. 2. CMC production by in3ltration and pyrolysis of polymers. pressures of up to 80 bars. Further, verysuccessful test campaigns with radiation-cooled combustion chambers were carried out in the small-thruster sector, wherebythe material was able to demonstrate its long-term stabilityand high chemical compatibility versus the propellants and combustion products. 2. Manufacturing, process technique and non destructive investigation (NDI) methods 2.1. LPI-process The C/SiC is made as shown in Fig. 2 via the polymer route. The coated C-3bre bundle is impregnated with a powder-3lled polymer and laminated to form prepregs. Analogouslyto the manufacturing technique for 3bre-reinforced plastics, the structure is laminated, compacted in an autoclave and cross linked, and then pyrolized without pressure and without moulding tools at temperatures of 1300–1900 K in inert gas. For further compacting (depending on the desired porosity), re-impregnation is e;ected with a suitable polymer followed by pyrolysis. The component may then be coated optionallywith an protection layer. Thanks to the consistent advanced development of the LPI Route over the past years, using a new rein3ltration polymer permitted reducing the re-impregnation cycles by 50% while retaining the same mechanical strength characteristics. Consequently, it was possible to cut the production costs, in particular for large-scale structures, byapprox. 25%. Fig. 3. 5-axis winding machines. 2.2. Production capabilities Based on the current production byEADS in Friedrichshafen of carbon 3bre reinforced plastics (CFRP) for the protective payload fairing of Ariane 5 (Speldra and Syldra), liquid-polymer in3ltration was developed byDaimlerChrysler Research for, amongst other things, space components, hot structures, and re-entrytechnologies. In order to build axisymmetric components such as nozzle extensions, combustion chambers, etc., two 5-axis winding machines with dimensions 3200 × 10; 000 mm2 and 2000 × 5000 mm2 (Fig. 3) as well as two 4-axis winding machines with dimensions 500=800×5000 mm2 and 200=800×2000 mm2 are available, in particular for 3D components. For the autoclave hardening of the components in order to provide them with the so-called green body, various autoclaves are available for smaller components (1000 × 3000 mm2) as well as for large-space structures (3500 × 8500 mm2) in the Friedrichshafen production centre (Fig. 4). For high-temperature treatment, two pyrolysis furnaces for component sizes of up to 2:5 m in diameter and 3 m in height are available (the Munich-based ECM company). 2.3. NDI methods In view of, compared to metals, signi3cantly anisotropic ceramic composite structure, the nondestructive testing of C/SiC components already
412 S. Schmidt et al./ Acta Astronautica 55(2004)409-420 Fig. 5. Testing various specimen plates by means of thermography and ct Fig. 4. Autoclave hardening of huge space structures. CT measurement lies here in the exact localization in particular the visualization of the depth position during production is a decisive criterion as regards the of the defect, as well as in the simple estimation of lifetime and reliability of highly stressed components In particular defect interpretation and the correla the size of the defect in all three spatial directions by tion of the various methods are not yet completel means of the reconstructed images understood. Currently, at Astrium diverse standard procedures for the non-destructive testing of C/Sic 2.3.1. Impulse thermography components, such as thermography, X-ray technology A mobile and proven method for determining com- and ultrasonic technology, are in use. With the aid of ponent qualities is impulse thermography, which has the NDI methods, possible production defects such already been very successfully tried and tested in the as delaminations, pores, and cavities, etc. as well as development of nozzles and combustion chambers.In component conditions before and after testing are to the case of impulse thermography, the component re- be detected. In order to improve the prediction poten mains stationary, and the surface of the component to tial and minimize risks, a comprehensive investigation be tested is warmed very homogeneously with sp programme was launched a short while ago at As cial flashbulb heat in the milli-to microsecond range trium. The focus and objective of such investigation by some few degrees. If no diflerences in material or is to prepare a so-called defect catalogue which is to tructural damage such as, for instance, delaminations serve as a reference for the application of the differ- occur, this thermal impulse penetrates uniformly into the material. If for instance. there are delaminations or procedures, alternative methods such as computer other defects in the composite material, at this spot the and neutron tomography were studied. With respect thermal conductivity is disturbed and visualized via a to the later qualification of the individual methods, special software by means of differing colour codings first of all various C/SiC specimen plates with de- fined, built-in defects at different depth positions and 2.3.2. Computer tomography with different production statuses were made and CT makes it possible to visualize the interior struc- then tested applying the NDI methods thermography, ture of objects non-destructively and without contact. ultrasonic testing and computer tomography(CT). By applying the latest technologies and faster alge ig. 5 shows as an example the test result of two rithms, a spatial resolution of up to l um and less difterent plates measured on the one hand using ther is achieved. As. for instance. the C/SiC combustion mography (left-hand image )and CT(right-hand im- chambers represent 3D axisymmetric bodies, the in- age). In the thermography image (left-hand image ), dustrial 3D CT method is extremely advantageous the differing depth position of the artificial defects is The system permits detecting changes in density as also clearly to be seen. a decisive advantage of the well as defects, together with a characterization with
412 S. Schmidt et al. /Acta Astronautica 55 (2004) 409 – 420 Fig. 4. Autoclave hardening of huge space structures. during production is a decisive criterion as regards the lifetime and reliabilityof highlystressed components. In particular defect interpretation and the correlation of the various methods are not yet completely understood. Currently, at Astrium diverse standard procedures for the non-destructive testing of C/SiC components, such as thermography, X-ray technology and ultrasonic technology, are in use. With the aid of the NDI methods, possible production defects such as delaminations, pores, and cavities, etc. as well as component conditions before and after testing are to be detected. In order to improve the prediction potential and minimize risks, a comprehensive investigation programme was launched a short while ago at Astrium. The focus and objective of such investigation is to prepare a so-called defect catalogue which is to serve as a reference for the application of the di;erent methods. Besides the above-mentioned standard procedures, alternative methods such as computer and neutron tomographywere studied. With respect to the later quali3cation of the individual methods, 3rst of all various C/SiC specimen plates with de- 3ned, built-in defects at di;erent depth positions and with di;erent production statuses were made and then tested applying the NDI methods thermography, ultrasonic testing and computer tomography(CT). Fig. 5 shows as an example the test result of two di;erent plates measured on the one hand using thermography(left-hand image) and CT (right-hand image). In the thermographyimage (left-hand image), the di;ering depth position of the arti3cial defects is also clearlyto be seen. A decisive advantage of the Fig. 5. Testing various specimen plates bymeans of thermography and CT. CT measurement lies here in the exact localization, in particular the visualization of the depth position of the defect, as well as in the simple estimation of the size of the defect in all three spatial directions by means of the reconstructed images. 2.3.1. Impulse thermography A mobile and proven method for determining component qualities is impulse thermography, which has alreadybeen verysuccessfullytried and tested in the development of nozzles and combustion chambers. In the case of impulse thermography, the component remains stationary, and the surface of the component to be tested is warmed veryhomogeneouslywith special Oashbulb heat in the milli- to microsecond range bysome few degrees. If no di;erences in material or structural damage such as, for instance, delaminations, occur, this thermal impulse penetrates uniformlyinto the material. If, for instance, there are delaminations or other defects in the composite material, at this spot the thermal conductivityis disturbed and visualized via a special software bymeans of di;ering colour codings. 2.3.2. Computer tomography CT makes it possible to visualize the interior structure of objects non-destructivelyand without contact. Byapplying the latest technologies and faster algorithms, a spatial resolution of up to 1 m and less is achieved. As, for instance, the C/SiC combustion chambers represent 3D axisymmetric bodies, the industrial 3D CT method is extremelyadvantageous. The system permits detecting changes in density as well as defects, together with a characterization with
S. Schmidt et al./ Acta Astronautica 55(2004)409-420 separation, side load) Qualification of measurement technology(pressure sensors at wall) e Investigation into material behaviour under extreme thermal-mechanical conditions Film/ Detector Manufacturing of complex contours with adapted Radiation Holder stifFener rings for buckling loads Demonstration and verification of the metallic/ Fig. 6. Measurement principle of 3D CT. ceramic joining technique 3.1.. Manufacturing and design respect to their type, geometry and position in the com Based on the thermal and structu ponent. It is therefore possible to visualize material analyses, two Vulcain scaled nozzles were made ap- defects in the component volume, to effect local reso- plying the LPI method. The required fibre angle and lution and hence to make a comprehensive statement the wall-thickness progression of the nozzle compo- as regards quality. In addition, a dimensional measure- nent were set via the winding technique so as to be ment,i.ea complete, quantitative coverage of the con- tailor made. Due to the side loads calculated, special tour, can be effected Downstream data processing can stiffener elements were necessary in order to pre- thus serve to determine wall thicknesses and represent vent buckling of the nozzle. By laminating on ring nominal-actual contour comparisons. Fig. 6 illustrates elements and subsequent ageing and pyrolysis, an this principle. Through the continuous advanced de- integral positive compound between nozzle and stiff- elopment of the industrial CT systems, in particular ening element was generated For mant facture of the detectors, components that are 800 X 800 mm two nozzles, a newly developed polymer system was in size can be tested used which permitted reducing the manufacturing time by approx. 30% compared to the old polymer Both nozzles were coated for the hot-firing tests with 3. Development and test of CMc components a CVD-SiC layer. One of the challenges involved the interface design between ceramic nozzle and metal 3. Vulcain subscale nozzle extension combustion chamber. In particular the high tempera- tures occurring at the interface in the case of an area Within the framework of the tekan and astra ratio of 5 represented a particular challenge. Thanks Programme, two Vulcain subscale nozzles on the scale to an angular flange design, the use of flexible high of 1: 5 and with an area ratio of s=5-45 were de- ure seals and special clamping ring problem could be solved. Fig. 7 shows the two coated igned, made using the LPI technique and subjected C/Sic nozzle extensions to hot-firing testing on the Astrium test bench F3 (Ottobrunn )as well as on the dlr test bench P& The development and test objectives of the C/Sic 3. 1.2. Hot-firing tests nozzle extension were The Vulcain subscale nozzle extension was tested in two test se he with a maximum cham To study the compatibility and function of oxida- ber pressure of Pc =40 bars, and a se tion/erosion protection coatings for different mix- quence which comprised one single load point, with ture ratios(O/F=5-8) Pe=80 bars and O/F=6, for the entire test duration of Investigation into nozzle flow, flow separation 32 s, which was suficient to have full-flowing condi- (transient, steady) tions in the nozzle extension installed the 40-bar load Comparison with Vulcain (full-scale lateral case was specially performed to visualize the transi- loads/separation data. tion process from free to restricted shock separation
S. Schmidt et al. /Acta Astronautica 55 (2004) 409 – 420 413 Fig. 6. Measurement principle of 3D CT. respect to their type, geometry and position in the component. It is therefore possible to visualize material defects in the component volume, to e;ect local resolution and hence to make a comprehensive statement as regards quality. In addition, a dimensional measurement, i.e. a complete, quantitative coverage of the contour, can be e;ected. Downstream data processing can thus serve to determine wall thicknesses and represent nominal-actual contour comparisons. Fig. 6 illustrates this principle. Through the continuous advanced development of the industrial CT systems, in particular of the detectors, components that are 800 × 800 mm2 in size can be tested. 3. Development and test of CMC components 3.1. Vulcain subscale nozzle extension Within the framework of the TEKAN and ASTRA Programme, two Vulcain subscale nozzles on the scale of 1:5 and with an area ratio of = 5–45 were designed, made using the LPI technique and subjected to hot-3ring testing on the Astrium test bench F3 (Ottobrunn) as well as on the DLR test bench P8. The development and test objectives of the C/SiC nozzle extension were: • To studythe compatibilityand function of oxidation/erosion protection coatings for di;erent mixture ratios (O=F = 5–8). • Investigation into nozzle Oow, Oow separation (transient, steady). • Comparison with Vulcain (full-scale) lateral loads/separation data. • Upgrading/verifying of design tools (heat transition, separation, side load). • Quali3cation of measurement technology(pressure sensors at wall). • Investigation into material behaviour under extreme thermal–mechanical conditions. • Manufacturing of complex contours with adapted sti;ener rings for buckling loads. • Demonstration and veri3cation of the metallic/ ceramic joining technique. 3.1.1. Manufacturing and design Based on the thermal and structure-mechanical analyses, two Vulcain scaled nozzles were made applying the LPI method. The required 3bre angle and the wall-thickness progression of the nozzle component were set via the winding technique so as to be tailor made. Due to the side loads calculated, special sti;ener elements were necessaryin order to prevent buckling of the nozzle. Bylaminating on ring elements and subsequent ageing and pyrolysis, an integral positive compound between nozzle and sti;- ening element was generated. For manufacturing the two nozzles, a newly developed polymer system was used which permitted reducing the manufacturing time byapprox. 30% compared to the old polymer. Both nozzles were coated for the hot-3ring tests with a CVD-SiC layer. One of the challenges involved the interface design between ceramic nozzle and metal combustion chamber. In particular the high temperatures occurring at the interface in the case of an area ratio of 5 represented a particular challenge. Thanks to an angular Oange design, the use of Oexible hightemperature seals and special clamping rings, the problem could be solved. Fig. 7 shows the two coated C/SiC nozzle extensions. 3.1.2. Hot-4ring tests The Vulcain subscale nozzle extension was tested in two test sequences, one with a maximum chamber pressure of pc = 40 bars, and a second test sequence which comprised one single load point, with pc=80 bars and O=F=6, for the entire test duration of 32 s, which was suIcient to have full-Oowing conditions in the nozzle extension installed. The 40-bar load case was speciallyperformed to visualize the transition process from free to restricted shock separation