Cargo Compartment Liner Burn-Through Fuel Test System Manufacturer in China
Get a quote：
Whats/App: +86 156 1874 6768
Web: standard-groups.com
E-mail：info@standard-groups。com
Parameters
| Item | Specification |
|---|---|
| Overall dimensions | 1500 mm (W) × 1800 mm (H) × 900 mm |
| System weight | 150 kg |
| Power requirement | 220 V, 10 A |
| Operating temperature | 10°C to 35°C |
| Fuel type | Aviation kerosene |
| Air supply | Minimum 120 PSI compressed air |
| Flame temperature capability | ≥ 2000 ± 50 ℉ |
| Heat flux output | ≥ 10.6 W/cm² |
| Temperature control bath | ≥ 2 × 0.14 m³ |
Features
1. The burner cone is made of a corrosion-resistant and high-temperature-resistant alloy.
2. The NexGen aviation fuel burner includes components such as a spoiler, fuel nozzle, igniter, fuel rail, mounting plate, ventilation duct and housing, muffler, and acoustic damper.
3. Equipped with a fuel pressure gauge, fuel solenoid valve, fuel temperature detection device, air pressure regulating valve, and air temperature detection device.
4. Equipped with an ice bath with a volume of at least 2 x 0.14 m³ for fuel and air temperature control, allowing for precise fuel temperature control.
5. Different testing standards can be met by changing the fuel nozzle and air pressure input.
6. The burner is covered with an insulating blanket to cover the fuel lines and fuselage.
7. The NexGen aviation fuel burner can provide a flame temperature of at least 2000±50℉.
8. The NexGen aviation fuel burner provides a flame heat flux of no less than 10.6 W/cm².
9. Modular unit using the NexGen burner support system.
10. Heavy-duty steel frame, capable of horizontal and vertical mounting of test samples.
11. Seven 1.6 mm diameter ceramic-encapsulated, metal-sheathed, grounded Type K (NiChC-NiA) thermocouples should be used for calibration. The conductors should have an outer diameter of 0.254 mm, a cross-sectional area of 0.0507 mm², and a resistance of 361 Ω/km (US wire gauge 30 AWG). The thermocouples should be fixed to an angle steel bracket to form a thermocouple comb for placement on the sample holder during calibration.
12. Thermal radiation flux sensor, equipped with a cooling device, mounted on a fixed bracket.
Accessories
The system is supplied with the following components:
NexGen aviation fuel burner
Seat cushion test frame
Dynamic loading motion system
Fuel temperature control ice bath
Thermocouple calibration comb
Radiant heat flux sensor with cooling unit
Powder-coated steel support frame with digital scale
Movable seat cushion test fixture
Movable drip collection tray
Burner thermal insulation blanket
Test Procedures
Mount the cargo liner panel or seat cushion specimen on the designated test frame.
Connect aviation kerosene supply and compressed air (≥120 PSI).
Set and stabilize fuel temperature using the ice bath system.
Adjust air pressure and fuel flow parameters according to the selected standard.
Ignite the NexGen burner and allow the flame to stabilize.
Position the flame relative to the specimen and initiate exposure.
Monitor flame temperature and heat flux using thermocouples and sensors.
Observe flame spread behavior, burn-through occurrence, and dripping characteristics.
Collect data, including temperature, heat flux, and material response.
Evaluate performance in accordance with the applicable standard.
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