터빈익렬 유로에서 2상유동에 따른 삭마량 예측

다국어 초록 (Multilingual Abstract)

The present study investigates numerically particle laden flow through compressor cascades and a rocket nozzle. Engines are affected by various particles which are suspending in the atmosphere. Especially in the case of aircraft aviating in volcanic, industrial and desert region including many particles, each components of engine system are damaged severely. That damage modes are erosion of compressor blading and rotor path components, partial or total blockage of cooling passage and engine control system degradation. Numerical prediction and experimental data, erosion rates are predicted for two materials - ceramic, soft metal - on compressor blade surface. Aluminum oxide (Al₂O₃) particles included in solid rocket propelant make ablative the rocket motor nozzle and imped the expansion processes of propulsion. By the definition of particle deposition efficiency, characteristics of particles impaction are considered quantitatively. Stoke number is defined over the various particle sizes and particle trajectories are treated by Lagrangian approach. Particle stability is considered by definition of Weber number in rocket nozzle and particle breakup and evaporation is simulated in a rocket nozzle.

목차 (Table of Contents)

• ABSTRACT
  
• 1. 서론
  
• 2. 수치해석 기법
  
• 3. 압축기 수치해석 결과
  
• 4. 로켓노즐부 수치해석 결과
  
• 5. 결론
  
• 참고 문헌