Rocket Engine thrust chambers

Test

Thrust chamber testing includes:

• Pressure tests with gaseous helium up to 250 bar and with de-ionised water up to 300 bar.

• Leak tightness tests with gaseous helium up to 10 -10 mbar with integral and local vacuum and excess pressure methods.

• Thermal tests from +180 C° to -196 C°.

• Follow-through tests with
  - deionised water from 0.001 lt/s to 60 lt/sec
  - gaseous nitrogen from 0.15 m3/hr to 5,000 m3/h.

The above tests are performed on specifically developed test stands together with state-of-the-art measuring equipment, data recording and test data evaluation.

Thrust chamber test area facilities include:

• Water cooling channel flowback facility up to 16 bar for all combustion chambers.

• Thermal test facility for thrust chamber components, including inlet and outlet manifolds, injector heads etc.

• GN2 Robot facility.

• Water flowcheck facility up to 40 bar for all combustion chambers.

If you require more detailed information on any of our products or services, then please contact us, indicating your particular areas of interest or intended application. Your enquiry will receive our best attention.