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Experimental Study of Acceleration Effect on Combustion Chamber Pressure Field

Goodarz, Masood | 2017

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 52094 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Farahani, Mohammad; Mohammadi, Alireza
  7. Abstract:
  8. This thesis is conducted to study acceleration effect on the burning rate augmentation of a solid propellant. A centrifugal experimental setup is designed to obtain a uniform acceleration field. An internal burning tube is used as grain, so acceleration vector is always perpendicular to burning surface of propellant. Inner radius of tube is small, so the magnitude of acceleration increases as the grain burns back. The pressure of combustion chamber was changed from 30 bar to 80 bar by changing the nozzle throat and the magnitude of acceleration changed from 2g to 60g by changing the rotational speed of SRM. Burning time of all tests was below 2 sec. due to small web of the grain. Pressure of combustion chamber was measured. An analytical 0D Code was used to compute burning rate of propellant.As investigated, at low acceleration level (below 5g), burning rate of propellant is not sensitive to acceleration while in the condition in which acceleration changed from 30g to 60g, burning rate augmentation ratio increased from 1 to 1.5. At high acceleration level, inner cylindrical surface of inhibitor was coated with aluminum oxide particles.Nozzle throat diameter is another parameter controlling pressure field of combustion chamber of SRM. Thermomechanical erosion of nozzle throat is significant in aluminized propellant. As investigated in this study, erosion rate of nozzle throat diameter at 375 RPM condition is 2.4 times higher than static condition
  9. Keywords:
  10. Burning Rate ; Combustion Chamber ; Acceleration Effect ; Solid Propellants

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