Name: GR1 Titanium Capillary Tube For Engine Fuel Line
Brand: TOPTITECH
SKU: 263814718

Engineered for extreme reliability in aerospace propulsion systems, TOPTITECH's GR1 Titanium Capillary Tube For Engine Fuel Line delivers unmatched performance under cryogenic and high-pressure conditions. Precision-crafted to a 2mm outer diameter and 500mm length, this aerospace-grade titanium capillary tube leverages Grade 1 titanium's ultra-low oxygen content (<0.18% per ASTM B338) to ensure optimal ductility and corrosion resistance. The α-phase microstructure, stabilized through vacuum arc remelting (VAR) and inert-gas shielded annealing, minimizes interstitial impurities while achieving a tensile strength of 240 MPa and yield strength of 170 MPa. Its seamless design, refined via cold pilgering and electrochemical polishing, eliminates microcracks and ensures uniform wall thickness-critical for preventing fuel leakage in liquid oxygen/hydrogen environments.

Ideal for rocket engine regenerative cooling channels and aircraft hydraulic systems, the GR1 capillary tube's thermal contraction coefficient (8.6×10⁻⁶/°C) and oxidation resistance (stable TiO₂ layer up to 600°C) mitigate thermal stress-induced deformation. Advanced hot isostatic pressing (HIP) post-treatment eradicates residual porosity, achieving 99.98% densification for leak-proof fluid transfer. Compliant with AMS 4941 and ISO 5832-2 standards, this tube integrates flawlessly with Swagelok®-style fittings, offering a 20% weight reduction versus stainless steel alternatives. Rigorous oxygen analysis via inert gas fusion-infrared spectroscopy guarantees compliance with NASA-STD-6012B, solidifying its role in next-generation propulsion systems where precision, durability, and weight savings are non-negotiable.

Products Specifications

Material	GR1 titanium
Diameter	2mm
Length	500mm

Products Features

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1. Exceptional Oxygen Control for Enhanced Ductility

Utilizing advanced vacuum arc remelting and inert-gas shielding techniques, the GR1 capillary tube achieves ultra-low interstitial oxygen levels, aligning with aerospace-grade purity standards. This precision metallurgical control prevents α-phase embrittlement, ensuring consistent fracture toughness even in cryogenic fuel transfer applications.

2. Seamless Cold-Worked Microstructural Integrity

A multi-stage cold pilgering process with integrated stress-relief annealing produces a homogenous grain structure, eliminating microcracks and porosity. The refined surface finish and tight dimensional tolerances resist fatigue failure in high-pressure cyclic loading environments.

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3. Optimized Strength-to-Weight Performance

The combination of titanium's inherent lightweight properties and enhanced mechanical characteristics delivers superior weight efficiency compared to traditional stainless steel alternatives, maintaining robust burst pressure resistance for compact fuel line architectures.

4. Thermal and Oxidation Resilience

Engineered with a self-stabilizing oxide layer, the tube demonstrates exceptional resistance to thermal degradation across extreme temperature fluctuations. Its low thermal expansion behavior minimizes stress accumulation during rapid thermal transitions in propulsion systems.

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5. Full-Density Material Consolidation

Proprietary hot isostatic pressing post-treatment ensures near-theoretical density, effectively eliminating residual voids that could compromise fluid containment integrity in corrosive fuel mixtures.

6. Broad Chemical Compatibility

Passivated surface chemistry provides resistance to aggressive media including hydrocarbon-based fuels, oxidizers, and hydraulic fluids, enabling reliable performance in multi-phase aerospace and biomedical environments.

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7. Leak-Proof Fluid Containment

Validated through aerospace-standard leak testing protocols, the capillary tube achieves hermetic sealing performance essential for vacuum-rated propulsion components and precision fuel metering systems.

8. Laser-Weld Ready Surface Engineering

Electrochemically polished surfaces enable high-quality weld joints with minimal heat-affected zones, critical for maintaining parent material properties in complex fuel manifold assemblies.

applications

Rocket Propulsion | Definition, Types & Principles - Lesson | Study.com

1. Cryogenic Fuel Transfer in Rocket Propulsion‌

Deployed in liquid hydrogen (LH2) and liquid oxygen (LOX) feed lines, GR1 titanium capillary tubes interface with turbo-pump assemblies to enable phase-stable fuel delivery. The tubes connect cryogenic storage tanks to combustion chambers, maintaining flow continuity during rapid pressure fluctuations in staged combustion cycles. Their seamless construction prevents vapor lock formation during subcooled fuel transfer, critical for maintaining thrust vector stability in ascent phases.

2. Aircraft APU Fuel Atomization‌

Integrated into auxiliary power unit (APU) fuel injectors, GR1 tubes regulate kerosene flow to swirl cup assemblies. The capillary network distributes fuel through micron-scale orifices positioned upstream of ignition electrodes, ensuring precise spray patterns for lean-burn combustion. This configuration supports auto-ignition sequences during high-altitude engine restarts, where air density drops below 0.3 kg/m³.

3. Regenerative Cooling Channels‌

In reusable rocket engine designs, GR1 tubes form embedded cooling channels within nozzle throat sections. Fuel flows through these capillaries prior to combustion, absorbing thermal loads exceeding 3,000°C from plasma exhaust. The capillary network's geometric arrangement (spiral/zigzag patterns) maximizes heat exchange efficiency while preventing coking deposits in methane-fueled systems.

4. UAV Fuel Quantity Probes‌

Mounted in unmanned aerial vehicle (UAV) wing tanks, GR1 capillary arrays function as capacitive sensing elements. The tubes' conductive walls interact with dielectric fuel layers to generate capacitance gradients, enabling real-time mass calculation during aggressive maneuvering at ±9G loads. This configuration replaces traditional float-based systems vulnerable to slosh-induced measurement errors.

5. Afterburner Fuel Modulation‌

GR1 capillary bundles in military jet afterburners distribute JP-8 fuel through staged injection rings. The tubes' thermal inertia delays fuel vaporization until reaching designated combustion zones, synchronizing with variable-geometry nozzle actuation. This phased injection prevents combustion instability during transonic-to-supersonic transitions, particularly in high-off-boresight maneuvering scenarios.

6. Hybrid Rocket Oxidizer Control‌

In paraffin-based hybrid propulsion systems, GR1 capillaries meter nitrous oxide (N2O) flow rates to regulate regression rates of solid fuel grains. The tubes' corrosion-resistant properties prevent decomposition reactions at phase boundaries, enabling precise oxidizer-to-fuel ratio maintenance during throttleable burn profiles.

7. Fuel Cell Hydrogen Distribution‌

For aviation PEM fuel cells, GR1 capillary matrices distribute humidified hydrogen to membrane electrode assemblies (MEAs). The tubes' low hydrogen embrittlement susceptibility ensures leak-free operation at proton exchange membrane operating temperatures, while their non-magnetic properties prevent interference with current collector plates.

8. Emergency Fuel Shutoff Systems‌

GR1 capillary-based pyrovalves serve as fail-safe actuators in crash scenarios. The tubes rupture at predefined stress thresholds, triggering frangible disk separation to isolate fuel reservoirs. This passive safety mechanism activates within milliseconds of impact detection, exceeding FAA fire containment requirements for post-crash survivability.