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Home > Flammability Test Equipment > FAR 25.853 Part IV Rate Of Heat Release OSU Test Apparatus

FAR 25.853 Part IV Rate Of Heat Release OSU Test Apparatus

Product Model : SL833

The OSU heat release rate tester approved by FAA of the Federal Aviation Administration of the United States was originally designed by Smith of Ohio State University in 1972, and later became a FAA designated combustion test instrument for testing the heat release rate of Aeronautical materials. The test standards are FAR Part 25 Appendix F Part IV, Airbus AITM 2.00. 06, Boeing BSS 7322.

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Detailed description

Product information

Specification

A. Main Unit

1. OSU Main unit (1set)

1) Apparatus Dimensions : 760mm (W) x 1850mm x (H) x 850mm (D)

2) Test chamber

- The radiant heat source and ensure that the heat flux density is 35±0.5kW/m2

- This will determine if the material complies with FAR 25.853 requirements

- Four silicon carbide elements Type LL 508mm by 16mm with nominal resistance 1.4 Ohms as a heat source with corrosion resistant stainless steel housing

- A reflector made from stainless steel is situated behind the elements

- In front of the elements, a truncated diamond shaped mask, constructed of stainless steel, this provides uniform heat flux density over the area occupied by the 151 × 151mm vertical sample

- Wand Assembly for lighting the upper pilot and calibration burners

- Dual global power controllers for ease of heat flux uniformity adjustment

- Upper pilot and lower pilot (with spark ignition) and calibration methane gas burners

- Thermopile for heat release rate measurement, with five hot thermocouple junctions in the chimney and five cold thermocouple junctions in the air chamber

3) Specimen holders (1set)

- Two specimen holders

- Each specimen holder is fabricated from stainless steel

2. Air distribution system(1set)

- Air temperature to be 21-24℃

- Air at a flowrate of 0.043m3/sec or more

- square-edged circular plate orifice 0.5±0.1mm

- located in a circular pipe with a dimeter of 38±1mm

- The air supply manifold at the base of the pyramidal section shall have 48 evenly space hole

B. Accessories

1. Control unit(1set)

- Calibration flow rate control

- Lower burner ignition

- Calibration heat flux : calibration heat fluxmeter are two water cooled heat flux sensors are supplied to measure heat flux density at the center and each corner

2. Computer system(1set)

- CPU : Pentium 4 3.0Ghz or more

- RAM : 512MB or more

- HDD : 80GB or more

- Monitor : 17“ LCD or more

- Printer : Laser Jet

- Software : Windows XP or more

Performance characteristics

1. Stainless steel combustion test chamber with high temperature glass observation window;
2. The heat radiation source is 4 Glowbars heating rods, which can provide 35KW/M2 heat radiation flux.
3. Two independent PID temperature controllers are used for heating temperature control.
4. Equipped with fully automatic pneumatic sample propulsion device and shielding door device;
5. Equipped with upper burner and movable lower burner;
6. Rotor flowmeter can be used to adjust the gas flow rate of upper and lower burners.
7. Equipped with movable T-type calibration burner device and flow controller;
8. Mass flow controller is applied to thermopile temperature calibration automatically.
9. Water-cooled heat flow meter is equipped with cooling mode to measure the heat radiation flux of the fire surface.
10. The air temperature control device can provide constant temperature and flow air for the test chamber.
11. The orifice flowmeter is used to measure the flow pressure entering the test bin.
12. Equipped with data acquisition system and heat release standard test software.

Technical parameters

Size	760mm (W) x 1850mm x (H) x 850mm (D)
Weight	218KG
Electricity requirements	220 V, 35 Amps
Ambient temperature	10 ℃ to 35 ℃
Auxiliary Gas	Constant Temperature and Constant Current Gas
Combustion gas	methane
Standard	AITM 2.0006,BSS 7322,FAR PART 25 APPENDIX F Part IV
Applications	Aviation Materials