Conjugate Analysis of Silica-Phenolic Charring Ablation Coupled with Interior Ballistics

Alanyalioglu C. O., ÖZYÖRÜK Y.

JOURNAL OF PROPULSION AND POWER, cilt.37, sa.4, ss.528-543, 2021 (SCI-Expanded) identifier identifier

  • Yayın Türü: Makale / Tam Makale
  • Cilt numarası: 37 Sayı: 4
  • Basım Tarihi: 2021
  • Doi Numarası: 10.2514/1.b37839
  • Dergi Adı: JOURNAL OF PROPULSION AND POWER
  • Derginin Tarandığı İndeksler: Science Citation Index Expanded (SCI-EXPANDED), Scopus, Aerospace Database, Aquatic Science & Fisheries Abstracts (ASFA), Communication Abstracts, Compendex, INSPEC, Metadex, Civil Engineering Abstracts
  • Sayfa Sayıları: ss.528-543
  • Anahtar Kelimeler: Ballistics, Thermochemical Ablation, Pyrolysis Gas Flow, Surface Energy, Convective Heat Transfer Coefficient, Nozzle Thrust Coefficients, Solid Rocket Motor, Surface Temperature Measurement, CFD Analysis, Aluminized Solid Propellant, HEAT-TRANSFER, TURBULENCE MODELS, EQUATION, SURFACE
  • Orta Doğu Teknik Üniversitesi Adresli: Evet

Özet

Because of its excellent insulation capability, the usage of a silica-phenolic charring ablator as a nozzle liner is a common practice in the solid rocket motor industry. During the design of a solid rocket motor employing a silica-phenolic nozzle liner, it is desired to conduct an accurate analysis yielding in-depth thermal response and recession characteristics. As the interior ballistics and nozzle recession rate mutually interact, the best practice is to perform a coupled solution to both. Commonly used one-dimensional analysis tools with empirical approaches for estimation of convective heat transfer rate and blowing effect generally lack sought accuracy and do not model the transient shape-change phenomenon, which affects the nozzle performance. This Paper considers governing equations for charring, including pyrolysis gas injection and surface energy balance for melting ablation, along with a boundary condition governed by interior ballistics, and demonstrates a framework in which these equations are solved with governing equations for the nozzle flowfield in a coupled manner. Development and validation of a one-dimensional material response solver based on the same governing equations is also demonstrated. Also, results from a static firing test conducted with a small-scale ballistic evaluation motor employing a silica-phenolic nozzle insert are provided. Results from both investigations are compared and discussed.