| HS Code | 492947 |
| Product Name | 3D Systems VisiJet RWT-RCL-R36 Multi-Material Composites |
| Material Type | Multi-Material Composite |
| Constituent Materials | VisiJet CR-WT 200 + VisiJet CR-CL 200 |
| Color | White/Clear |
| Tensile Strength | 52 MPa |
| Tensile Modulus | 2500 MPa |
| Elongation At Break | 13% |
| Flexural Strength | 82 MPa |
| Flexural Modulus | 2340 MPa |
| Hardness | 82 Shore D |
| Heat Deflection Temperature | 52 °C |
| Density | 1.11 g/cm³ |
| Water Absorption | 0.46% |
| Impact Strength | 18 J/m |
| Layer Thickness | 16 microns |
| Support Material | VisiJet S200 |
| Printing Technology | MultiJet Printing (MJP) |
As an accredited 3D Systems VisiJet RWT-RCL-R36 Multi-Material Composites (VisiJet CR-WT 200** + VisiJet CR-CL 200 factory, we enforce strict quality protocols—every batch undergoes rigorous testing to ensure consistent efficacy and safety standards.
| Packing | |
| Shipping | |
| Storage |
In high-fidelity jewelry casting, the VisiJet RWT-RCL-R36 multi-material set—comprising VisiJet CR-WT 200** and VisiJet CR-CL 200—is used to produce soluble-supported wax patterns for hollow-link bracelets, filigree rings, stone-setting models, and watchcase components that contain internal undercuts and fine gallery holes. The clear support is removed in a temperature-controlled support-removal bath, typically held at 40–45°C for 15–30 min, after which the wax pattern is rinsed in isopropyl alcohol and dried at 22–26°C to prevent moisture entrapment before treeing. Build-to-support volume ratio is not a fixed formulation value; it derives from sliced geometry and support-density settings, and on production filigree rings it generally lies between 0.4:1 and 1.1:1 support-to-wax, rising when the pattern carries concave stone seats or hidden box clasps. The wax pattern is attached to an injection wax sprue with a heated wax pen, and the completed tree is invested in a gypsum-bonded investment slurry formulated for flask casting, vacuum-debubbled, and allowed to bench set for 2–4 h at 21–24°C before flask loading. Burnout in a digitally ramp-controlled kiln follows a stepped profile of 2°C/min to 550°C with a hold of 2–3 h, followed by a temperature plateau at 650–700°C for casting temperature stabilization. The terminal cast articles are produced in sterling silver, karat gold, platinum, or palladium alloys and may be finished by tumbling, stone setting, and polishing. Compliance for United States distribution is guided by ASTM F2999-19 for lead and cadmium limits in adult jewelry, while EU markets require REACH Annex XVII restrictions on cadmium and lead, and national assay office hallmarking applies to precious metal fineness. Foundry operators should not store printed wax patterns above 35°C because thermoplastic creep can alter dimensional accuracy; exposure to ketone-based solvents or prolonged direct sunlight is also incompatible with the wax formulation.
Dental milling centres and partial denture laboratories use the system for sacrificial patterns of cobalt-chromium and nickel-chromium frameworks, telescopic crowns, and implant-supported bars. The support removal protocol for dental patterns is adjusted to protect thin lingual and incisal edges; ultrasonic agitation at 35–40°C for 20–30 min is followed by air-drying at 25°C to minimise edge rounding. In this segment the support-to-wax volume ratio is commonly between 0.5:1 and 1.5:1 for full-arch bars with deep intaglio surfaces; the ratio is generated by the nesting software rather than blended into the material. The wax framework is sprued along the lingual arch to reduce hot-spot turbulence during induction or flame melting, then invested in a phosphate-bonded investment designed for high-expansion compensation of Co-Cr solidification shrinkage. Burnout in a dental quartz-tube furnace proceeds at 0.5–1.0°C/min to 450°C with a 1 h soak, then ramps at 3°C/min to 850–900°C and holds for 45–90 min before centrifugal or vacuum-pressure casting. Terminal frameworks are finished to fit implants, then veneered with feldspathic porcelain or composite. Compliance with ISO 22674:2016 for dental metallic materials and ISO 9693-1:2012 for metal-ceramic systems is determined on the cast alloy, not on the pattern; the pattern material is selected to decompose without silica-reactive residues. Incompatibility arises if the operator substitutes a gypsum-bonded investment formulated for gold and applies a fast ramp above 2°C/min below 650°C; the resulting internal pressure can crack the mold or distort thin marginal areas.
Aerospace foundries producing equiaxed, directionally solidified, or single-crystal turbine blades use the pattern system where ceramic core registration requires non-contact internal support during wax injection. The clear support is removed from internal passages before ceramic core insertion; post-print support dissolution is carried out in a temperature-controlled bath at 40–50°C, with narrow openings flushed to prevent residue trapping. Support-to-build volume ratio for cored blade patterns is highly asymmetric, ranging from 1.0:1 to 2.4:1 for parts with serpentine internal cooling geometry, because the printhead must support each passage temporarily before investment. The wax pattern is assembled onto a wax tree with preformed gates, and the ceramic shell is built by alternate dipping in colloidal silica slurry and fluidised-bed refractory stucco, with a prime coat applied using a zircon-based slurry. Dewaxing is performed in a steam autoclave with chamber pressure held between 0.4 MPa and 0.7 MPa and steam inlet temperature of 150–170°C; steam penetration melts the bulk wax within 10–20 min while the green shell remains mechanically stable. Firing of the de-waxed shell reaches a peak of 1000–1500°C depending on the shell formulation and casting temperature of the superalloy; residual ash from the pattern must remain below 0.02 wt% by standard ash-test methods so that surface inclusions do not initiate recrystallisation or creep defects. Compliance with SAE AMS 5390 class alloy requirements and NADCAP AC7104 investment casting audit criteria governs process control; material lot traceability and pattern storage below 35°C are mandatory. The terminal components—turbine blades, vane segments, and nozzle guide vanes—are cast in nickel-based alloys such as IN718, CMSX-4, or René alloys. The primary incompatibility is the use of excessive autoclave pressure above 0.7 MPa, which can split low-green-strength shell sections, particularly in trailing-edge areas with thin ceramic over unsupported wax.
Published data for this specific multi-material pairing is limited; the burnout windows in Table 1 are compiled from commercial foundry operating envelopes for unfilled wax pattern systems.
| Alloy class | Dewax method | Shell preheat | Burnout peak | Hold time | Reference standard |
|---|---|---|---|---|---|
| Gold/silver jewellery | Flash-fire oven 150–180°C | 650–700°C | 550–650°C | 2–3 h | ASTM F2999-19 |
| Dental cobalt-chromium | Steam autoclave 0.3–0.5 MPa | 850–900°C | 750–900°C | 45–90 min | ISO 22674:2016 |
| Nickel-based superalloy | Steam autoclave 0.4–0.7 MPa | 1000–1100°C | 1000–1500°C | 2–4 h | SAE AMS 5390 |
| Stainless steel and nickel-copper alloys | Flash-fire oven 160–180°C | 850–1050°C | 850–1050°C | 1.5–2.5 h | API 610 |
When an automotive turbocharger or coolant pump supplier replaces machined wax assemblies with multi-material printed patterns, the manufacturing value concentrates in fast pattern iteration and in the elimination of hard tooling for pre-production batches. The support removal station is integrated into the pattern-preparation line at 38–43°C, and the clean wax patterns are handed to wax welding operators for assembly onto injection-moulded sprue bases. The support-to-wax volume ratio for small impeller patterns with tightly spaced blades typically falls between 0.6:1 and 1.4:1; this ratio is output from nesting software and is not an adjustable resin blend parameter. Shell construction for turbocharger wheels uses a colloidal silica slurry with alternating zircon and fused-silica stucco layers, with each coat dried at 22–26°C and 50–55% RH for 4–6 h per coat to avoid shell cracking. After wax removal in a steam autoclave or flash-fire oven at 160–180°C, the ceramic shell is preheated to 1000–1100°C to remove residual carbon and then charged with vacuum-melted nickel-based K418 or Inconel alloy. Terminal components are turbocharger impellers, pump runners, and engine exhaust manifold segments. The pattern must be judged against ISO 9001/IATF 16949 production part approval workflows; REACH dossier compliance covers only any intentionally released substances during burnout, which for unfilled wax is limited to hydrocarbons and carbon dioxide under oxidising kiln conditions. A known limitation is that thin trailing-edge features can deform if pattern storage exceeds 35°C, and post-casting dimensional inspection to ISO 8062 general geometric tolerances is required to validate the printed pattern against the machined-wax baseline.
In bronze and brass art foundries, the system is adopted for statue sections, figurative components, and hollow-core sculptures that require internal support during casting sprue assembly. The clear support is dissolved in a heated bath at 40–45°C; the wax sections are then hand-welded with a wax stick at 70–80°C to form the complete pattern tree. The support-to-wax volume ratio for sculptures with internal cavities and drapery undercuts can exceed 1.5:1, but for low-relief panels it drops to 0.3:1–0.6:1; this ratio is not controlled by the raw material, only by orientation and support-density settings. Ceramic shell investment proceeds in a six-to-eight-coat colloidal silica and molochite stucco system, dried under controlled air movement to preserve fine surface details, then the pattern is dewaxed in a batch flash-dewaxing oven at 150–180°C for 20–30 min to prevent wax expansion damage. Kiln burnout for bronze shell molds reaches 700–800°C before pouring of silicon bronze or yellow brass at 1100–1200°C. Terminal articles include limited-edition sculpture, restoration elements, and architectural bronze castings. Compliance is governed by the purchaser specification and national foundry safety regulations; UNS alloy composition may be referenced to ASTM B584-14 for copper alloy sand and permanent mold castings. The principal incompatibility is mixing printed wax with traditional filled pattern waxes, because filler residues can increase ash content and create surface porosity; foundries that maintain separate wax reclamation loops avoid this failure mode.
High-alloy industrial pump and valve investment casting uses the printed pattern set for impeller casings, wear-ring sections, and valve body volutes where internal flow passages are too tortuous for simple tooling. After support dissolution at 40–45°C and air-drying at 22–26°C, patterns are assembled with wax-injected gates and inspected for shell-critical undercuts using digital structured light. The support-to-wax volume ratio in this segment is typically 0.3:1–0.8:1 for external supporting geometries, but internal volute windows may drive the ratio above 1.2:1 when the printing algorithm must support channel ceilings. Shell building uses a ceramic slurry system with ethyl silicate or colloidal silica binders, followed by autoclave or microwave dewaxing at 0.3–0.5 MPa steam pressure or 150–170°C dry heat. Burnout in a gas-fired kiln reaches 850–1050°C for stainless steel and nickel-copper alloys, while titanium-containing alloys require an inert or vacuum burnout environment to avoid shell oxidation. Final components are cast in 316 stainless steel, duplex stainless steel, or Monel, then hydrostatically tested to API 610 or ISO 5199 depending on service duty. The printed wax must demonstrate ash residue below 0.02 wt% under the foundry’s in-house burnout test, and pattern storage below 35°C is required to prevent creep in thin volute lips. Incompatible handling includes exposure to solvent vapours from adjacent cleaning tanks, which can soften the wax surface and alter surface roughness before shell coat application.
Competitive 3D Systems VisiJet RWT-RCL-R36 Multi-Material Composites (VisiJet CR-WT 200** + VisiJet CR-CL 200 prices that fit your budget—flexible terms and customized quotes for every order.
For samples, pricing, or more information, please contact us at +8618136850665 or mail to admin@ascent-chem.com.
We will respond to you as soon as possible.
Tel: +8618136850665
Email: admin@ascent-chem.com
Flexible payment, competitive price, premium service - Inquire now!
The 3D Systems VisiJet RWT-RCL-R36 Multi-Material Composites set is a two-phase wax material system comprising VisiJet CR-WT 200 and VisiJet CR-CL 200, supplied in a 3.6 kg heated-delivery cartridge configuration for MultiJet Printing systems. The R36 designation identifies the paired cartridge format rather than a single blended stock; the two components remain distinct in the feeding and jetting system until deliberate co-deposition is specified by the build file. At 25 °C, CR-WT 200 is an opaque white wax with a typical density of 0.85 g/cm³, while CR-CL 200 is a clear wax with a typical density of 0.86 g/cm³. Published material data sheets list softening temperatures in the 55–60 °C range and jetting viscosities of approximately 10–14 mPa·s at the heated reservoir temperature of 75–85 °C. Ash residue from both phases is reported below <0.02 wt% after burnout, as determined by combustion loss methods comparable to ASTM D482. The product is intended for investment casting patterns in jewelry, dental, and precision industrial foundries where the pattern must be consumed without leaving ceramic-shell contamination. The paired white and clear phases permit visual inspection strategies that are unavailable with a single opaque or single clear wax; CR-WT 200 provides high-contrast surface definition for dimensional checks, while CR-CL 200 exposes internal channel geometry and material transition zones. Support removal is performed with heated equipment rather than room-temperature solvent baths; the dedicated support material VisiJet S400 is designed for melt-away removal after printing.
| Property | VisiJet CR-WT 200 | VisiJet CR-CL 200 | Test basis |
|---|---|---|---|
| Appearance at 25 °C | Opaque white solid | Clear solid | Visual |
| Density | 0.85 g/cm³ | 0.86 g/cm³ | ASTM D792 |
| Softening temperature | 55–60 °C | 55–60 °C | DSC |
| Jetting viscosity | 10–14 mPa·s at 80 °C | 10–14 mPa·s at 80 °C | ISO 3219 |
| Ash residue | <0.02 wt% | <0.02 wt% | ASTM D482 |
In heated material delivery systems, jetting stability is a function of temperature uniformity, not simply average reservoir temperature. The printhead heater and reservoir must be calibrated so that the melt reaches the nozzle plate within a ±2 °C band; a wider band produces measurable droplet-volume drift because wax viscosity changes approximately 2–3 mPa·s per 5 °C in the working interval. This sensitivity is the main processing constraint in co-deposition.
At the jetting orifice, the two waxes must behave as near-Newtonian melts with viscosity low enough for droplet formation but high enough to maintain feature edges after deposition. Melt viscosity is characterized by rotational rheometry under ISO 3219; the published working range is 10–14 mPa·s at 80 °C. Surface tension and density differences between CR-WT 200 and CR-CL 200 influence droplet ligament breakup length, and therefore the minimum purge volume required when the printhead switches between materials. In co-deposition builds, the printhead alternates between two feedstock streams; if the switching interval is shorter than the residence time of the previous melt in the printhead chamber, the clear phase will carry white pigment into subsequent layers.
The reservoir temperature setpoint is not the only variable. Printhead temperature, build-chamber air temperature, and local cooling rate after deposition determine whether adjacent droplets coalesce into a continuous skin. In production-scale units, the build chamber is held at 40–50 °C to slow solidification; below that band, layer bonding can fail, while above it, the wax pattern may slump under its own weight during long builds. Published data for this specific configuration is limited for builds exceeding 200 mm vertical height, so orientation is adjusted to minimize tall unsupported vertical walls.
The burnout performance of CR-WT 200 and CR-CL 200 is governed by the inorganic content remaining after combustion. The white phase contains a low-load refractory pigment, and the clear phase is formulated without the same pigment loading; both are reported to leave ash residue below <0.02 wt% under combustion loss methods comparable to ASTM D482. This threshold matters because residual ash in a ceramic shell can react with silica-based slurry to form low-viscosity phases that reduce shell integrity at the metal-pouring temperature.
Dewaxing and burn-out are separate thermal events. The wax pattern is removed from the shell at 90–150 °C; rapid vaporization above 100 °C before the shell has developed full green strength can generate internal pressure sufficient to crack thin sections. The subsequent burnout ramp is typically staged: 2 °C/min to 150 °C, hold 30 min; 3 °C/min to 550 °C, hold 60 min; then 5 °C/min to 700–750 °C, hold 120 min. The final hold is the critical residue-limiting step; furnaces with poor atmosphere circulation can leave carbon micro-particulates even when the average chamber temperature meets the setpoint.
For reactive alloys such as titanium aluminide or aluminum-lithium grades, the residual carbon limit may be tighter than the ash value alone suggests. Foundries processing these alloys supplement the standard burnout with an oxidizing hold and verify shell cleanliness by energy-dispersive X-ray spectroscopy on fired shells. Published data for the R36 material pair under reactive-alloy casting is limited; process qualification is required before production use.
When a build file assigns discrete volumes to CR-WT 200 and CR-CL 200, the printhead performs a material switch at each layer boundary. The transition is not instantaneous; a finite volume of mixed melt exists between the two streams. In the clear phase, pigment carryover is visible as a clouded zone with reduced optical transparency. The width of this mixed zone is controlled by purge volume and printhead chamber volume. Published purge volumes for the RWT-RCL-R36 configuration are machine-specific; insufficient purge produces pigment carryover and shifts the local ash residue upward in the mixed region.
The co-deposited part is therefore not a homogeneous composite in the polymer-composite sense. It is a spatially graded wax body with an interface between an opaque white region and a clear region. Differential thermal expansion between the two phases is small because both are hydrocarbon waxes with similar solid-state expansion behavior, but the white pigment alters nucleation and solidification rate. Shrinkage in the opaque phase may begin earlier during cooling because the pigment provides nucleating sites. Published differential shrinkage data for this specific material pair is limited, so dimensional stability at the interface should be verified by coordinate measuring machine on each new build orientation.
This multi-material capability provides a non-destructive inspection route for internal channels. A clear window in an otherwise white pattern permits visual or optical confirmation of channel continuity before investing. The limitation is that the clear phase is not an optically polished window; it is a translucent wax with surface scattering from layer striations, so inspection is limited to gross voids and channel misalignment rather than sub-millimetre defect detection.
Compared with castable photopolymer resins, the R36 wax pair does not rely on free-radical or cationic polymerization and therefore does not liberate residual monomer during burnout. The burnout ash values are lower than many filled photopolymer patterns, which may leave 0.1–0.5 wt% ash unless specially formulated. Compared with milled wax blanks, the material-jetting route supports internal channels and variable cross-sections that cannot be produced by subtractive contouring. The R36 pair differs from single-phase VisiJet M2 CAST in that it provides two co-printable wax phases with visual contrast; the chemical relationship between CR-WT 200 and CR-CL 200 is a matched-viscosity formulation rather than a simple pigmentation variant.
Storage conditions for the R36 cartridge are defined by wax thermomechanical stability. The cartridge should be stored at 15–30 °C and RH 60 % or lower. Hydrocarbon waxes do not absorb water as a bulk phase, but condensation on cold cartridge surfaces can introduce water into the feed path. A cartridge moved from cold storage should be equilibrated to room temperature before loading; failure to do so can create droplet voids when water flashes at jetting temperature. The material is incompatible with strong oxidizing agents, chlorinated solvents, and high-shear milling operations that could generate excessive frictional heat.
On the ProJet MJP 2500W Plus and related platforms, the R36 materials are co-printed with VisiJet S400 support wax. The support wax is not dissolved at room temperature; it is removed in a convection oven at 65–70 °C or in a proprietary melt-away station. The temperature margin between support removal and pattern softening is narrow, because the pattern materials begin to soften near 55–60 °C. A support-removal bath that overshoots to 75 °C can permanently distort free-standing walls, especially those thinner than 0.5 mm.
Production-scale builds with densely packed patterns require forced convection rather than static heating to remove support from internal channels. The removal time is set by the smallest channel cross-section and the total mass of support in the build volume. For parts with long internal galleries, the oven is often held at the lower end of the removal range and the time extended rather than using a higher temperature. Published removal times are geometry-dependent and must be established by destructive sectioning on first articles.
Build orientation should orient internal channels downward or vertical to allow melt drainage, and thin white walls should be supported by the clear phase or by S400 to maintain edge definition. The build layer thickness can be set to 16 μm for high-resolution features or 32 μm for faster throughput; thinner layers reduce surface stair-step but increase support contact and removal time. The native addressability of 375 × 375 dpi in the XY plane and 750 dpi in the Z axis defines the droplet placement grid, but the final edge definition is also a function of wax wetting and temperature control.
In foundry validation, the printed pattern is subjected to a first-article casting cycle with the same shell system and alloy chemistry intended for production. The white and clear regions are sectioned after burnout to confirm the absence of carbon deposits at the mixed interface. If the clear phase is used as an inspection window, it must be modeled as a remaining wax volume, not as a void; that wax volume contributes to the total pattern mass and must be fully removed before metal pouring.
