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propulsion-expert

Expert-level aerospace propulsion covering gas turbine engines, rocket propulsion, thermodynamic cycles, nozzle design, and propellant chemistry.

The English summary is being prepared. Showing the original description.

luokai0/ai-agent-skills-by-luo-kai

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SKILL.md (original)

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Propulsion Expert

Before Starting

  1. Air-breathing or rocket propulsion?
  2. Which engine type? (turbojet, turbofan, turboprop, ramjet, rocket)
  3. Design point or off-design analysis?

Core Expertise Areas

Gas Turbine Engines

Turbojet: intake, compressor, combustor, turbine, nozzle. Turbofan: bypass flow around core, better fuel efficiency, lower noise. Bypass ratio: ratio of bypass to core flow, high BPR for subsonic transport. Turboprop: turbine drives propeller via gearbox, efficient at low speed. Compressor pressure ratio: determines thermal efficiency and specific thrust.

Brayton Cycle Analysis

Ideal cycle: isentropic compression, constant pressure heat addition, isentropic expansion. Thermal efficiency: eta = 1 minus 1 over r_p to power k-1 over k. Specific fuel consumption: fuel flow per unit thrust, measure of efficiency. Component efficiencies: polytropic efficiency for compressor and turbine. Turbine inlet temperature: key design parameter, limited by material capability.

Rocket Propulsion

Rocket equation: delta-V = Isp times g0 times ln m0 over mf. Specific impulse: Isp = thrust over mass flow times g0, measure of propellant efficiency. Liquid propellants: RP-1/LOX, LH2/LOX, hypergolic NTO/MMH. Solid propellants: HTPB-based, simple, reliable, not throttleable. Hybrid: solid fuel with liquid or gaseous oxidizer.

Nozzle Design

Convergent-divergent nozzle: accelerates flow from subsonic to supersonic. Area ratio: determines exit Mach number and expansion ratio. Nozzle efficiency: accounts for friction and non-uniform flow losses. Thrust coefficient: CF = thrust over P_c times At, measures nozzle performance.

Best Practices

  • Match engine design point to most critical operating condition
  • Account for altitude effects on engine performance
  • Verify combustion stability before finalizing injector design
  • Include installation effects in installed thrust calculation

Common Pitfalls

PitfallFix
Ignoring off-design performanceEngine must perform across full flight envelope
Overexpanded nozzle at sea levelCheck nozzle exit pressure vs ambient
Underestimating turbine coolingTIT limits require significant cooling air fraction
Wrong Isp unitsClarify whether Isp is in seconds or N s/kg

Related Skills

  • aerodynamics-expert
  • thermodynamics-mech-expert
  • spacecraft-design-expert

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