Technical notes on next generation aero combustor design-development and related combustion research /

"The aim of this book is to identify that extra high-pressure ratio (such as about 70) civil aero engine low emissions combustors and extra high fuel air ratio (FAR) (such as FAR greater than 0.051) military aero engine combustors make up the next generation of aero combustors. The aero thermal...

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Detalles Bibliográficos
Clasificación:Libro Electrónico
Autores principales: Chin, Jushan (Autor), Dang, Jin (Mechanical engineer) (Autor)
Formato: Electrónico eBook
Idioma:Inglés
Publicado: New York : Nova Science Publishers, Inc., [2021]
Colección:Mechanical Engineering Theory and Applications Ser.
Temas:
Aircraft gas-turbines > Combustion.
Avions > Turbines à gaz > Combustion.
Aircraft gas-turbines > Combustion
Acceso en línea:Texto completo
Tabla de Contenidos:
  • Intro
  • TECHNICAL NOTES ON NEXTGENERATION AERO COMBUSTORDESIGN-DEVELOPMENT ANDRELATED COMBUSTIONRESEARCH
  • TECHNICAL NOTES ON NEXTGENERATION AERO COMBUSTORDESIGN-DEVELOPMENT ANDRELATED COMBUSTIONRESEARCH
  • Contents
  • Preface
  • Chapter 1Introduction to Aero CombustorDesign
  • 1.1. Starting Points of Aero Combustor Design
  • 1.1.1. Fuel Type
  • 1.1.2. Engine Application
  • 1.1.3. Requirements of Aero Combustor
  • 1.1.4. Engine Cycle Parameters
  • 1.1.5. Geometrical Dimension Limitations
  • 1.2. Combustor Operational and Practical Requirements
  • 1.3. Performance Requirements
  • 1.3.1. Combustion Efficiency
  • 1.3.2. Total Pressure Loss Coefficient
  • 1.3.3. Liner Exit Distribution
  • 1.3.4. Ground Idle Condition Lean Blow Out (LBO)
  • 1.3.5. High Altitude Ignition
  • 1.3.6. Smoke Level
  • 1.3.7. Gaseous Exhaust Emissions
  • 1.4. Combustor Working Parameters
  • 1.4.1. Pressure
  • 1.4.2. Temperature
  • 1.4.3. Air Flow Rate
  • 1.4.4. Fuel Flow Rate
  • 1.4.5. Fuel Injector Pressure Drop
  • 1.4.6. Combustor Fuel-Air Ratio (FAR)
  • 1.4.7. Liner Fuel-Air Ratio
  • 1.4.8. Liner Effective Flow Area ACd
  • 1.4.9. Combustion Instability Pressure Fluctuation
  • 1.5. Technology Development Program Aero Combustorand Type Engine Aero Combustor Design
  • 1.6. Combustor Aero Thermal Design and MechanicalDesign
  • 1.7. Preliminary Design and Detail Design
  • Chapter 2Briefing on Next GenerationAero Combustor Design
  • 2.1. What Are the Next Generation Aero Combustors?
  • 2.2. High Pressure Civil Aero Combustor Can Not UseLPP Combustion
  • 2.3. LDM Combustion Not LDI Combustion
  • 2.4. High FAR Combustor Needs Direct Mixing Combustionbut Not Lean
  • 2.5. Next Generation Aero Combustors Need Very HighCombustion Air Fractions
  • 2.6. Next Generation Aero Combustor Layout
  • Chapter 3Type One High Pressure LowEmissions Civil AeroCombustor (without FuelStaging) Preliminary Design
  • 3.1. Determination of Single Module Combustor LinerDiameter
  • 3.2. Fuel Air Module Configuration
  • 3.3. Idle Condition Design
  • 3.4. Design Air Flow Pattern
  • 3.5. Main Fuel Air Combustion Design
  • 3.6. Main Fuel Injection Design
  • 3.7. Main Air Module Design
  • 3.8. Single Module Tubular Combustor Cooling Design
  • Chapter 4Type One High Pressure LowEmissions Combustor (withoutFuel Staging) Detail Design
  • 4.1. Full Annular Liner Design
  • 4.2. Transient Operation Design
  • 4.3. Full Annular Combustor Cooling Design
  • 4.3.1. Outer Liner Cooling Design
  • 4.3.2. Non-Uniform Cooling Hole Axial Spacing
  • 4.3.3. Inner Liner Cooling Design
  • 4.4. Cooling Calculation
  • 4.5. Combustor Inlet Diffuser Design
  • Chapter 5Type Two High Pressure LowEmissions Combustor (with FuelStaging) Design
  • 5.1. Fuel Air Module
  • 5.2. Fuel Staging
  • 5.3. Comparison of Two Types Low Emissions CombustorDesign
  • Chapter 6Design of High FAR Combustor
  • 6.1. Combustion Air Fraction
  • 6.2. Combustion Organization Design

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