Laboratory Burner for Insulation Fire Performance

Whats/App: +86 156 1874 6768

Web: standard-groups.com

Standards

The system is compatible with the following international aerospace fire testing standards:

BSS 7387 – Flame spread and combustion behavior of aerospace materials

AITM 2.0056 – Heat release rate measurement of aerospace materials using cone calorimeter

FAR Part 25 Appendix F Part VII – Heat release and fire performance requirements for aircraft cabin materials

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

Incorporates the FAA-approved NexGen aviation fuel burner, developed to replace discontinued legacy burners (Park DPL 3400. Lennox OB-32. Carlin 200 CRD).

Retains the operational principles of previous burner generations while enabling more precise measurement of fuel and air test parameters.

Modular architecture facilitates future FAA upgrades without full system replacement.

The burner cone is fabricated from corrosion-resistant and high-temperature alloy to ensure durability in severe thermal conditions.

The NexGen burner includes key components such as baffle, fuel nozzle, igniter, fuel rail, mounting plates, ventilation duct, housing, muffler, and acoustic resistance unit.

Equipped with fuel pressure gauge, fuel solenoid valve, fuel temperature sensor, air pressure regulator, and air temperature sensor for stable control.

A temperature-controlled ice bath system (≥ 2 × 0.14 m³) allows regulation of fuel temperature prior to combustion.

Flame characteristics can be adjusted by modifying fuel nozzle configuration and air pressure input to meet different standard requirements.

The burner is covered with a thermal insulation blanket to protect fuel lines and the burner body.

Capable of delivering flame temperature of at least 2000 ± 50 ℉ and heat flux of at least 10.6 W/cm².

Mounted on a heavy-duty steel frame that supports both horizontal and vertical specimen installation.

Calibration utilizes a thermocouple comb composed of seven grounded K-type thermocouples (1.6 mm diameter, ceramic-insulated, metal-sheathed, 30 AWG wire), fixed on an angle bracket for standardized placement on the specimen frame.

Includes a radiant heat flux sensor with cooling system, installed on a fixed support bracket for reliable measurement.

Accessories

The system is supplied with the following components:

NexGen aviation fuel burner

Flame penetration test fixture for thermal and acoustic insulation

Dynamic loading motion system

Fuel temperature control ice bath

Thermocouple calibration comb

Radiant heat flux sensor with cooling unit

Heavy-duty specimen mounting frame

Burner thermal insulation blanket

Test Procedures

Mount the test specimen on the horizontal or vertical frame according to the selected standard.

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 per test requirements.

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 whether flame penetrates the insulation material within the specified time.

Record data and evaluate performance in accordance with the applicable standard.

Maintenance Information

To ensure long-term reliability and compliance:

Clean the fuel nozzle regularly to prevent blockage.

Inspect fuel lines and valves for leakage before each test.

Calibrate thermocouples and heat flux sensors periodically.

Replace the burner insulation blanket if damaged or degraded.

Maintain proper ventilation in the test area.

Keep the compressed air system dry and free from oil contamination.

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