Roshan Aerospace IndustriesContact ↗

RAI-PROP-001 / CAD & report completed

Turbofan Engine Concept V1

RAI / Evidence-led development

A conceptual two-spool turbofan assembly developed to study propulsion architecture, modular CAD, flow-path packaging, and engineering documentation.

GalleryTechnical recordMathematics3D modelDocuments

02 / Engineering record

What was actually done

This project combines a fan, multi-stage compressor, annular combustor, high- and low-pressure turbines, concentric shafts, nacelle, bypass duct, and separate-flow exhaust in one conceptual assembly. The geometry demonstrates system architecture; it does not reproduce a certified engine or claim validated performance.

Evidence available

  • Complete modular CAD assembly
  • Fan, compressor, combustor, HPT, LPT, shaft, casing, nacelle and exhaust studies
  • 116-page working engineering report in the archive
  • Cross-sections, exploded views and technical renders
  • Explicit limitations and future-analysis plan documented

Recorded dimensions & specifications

ArchitectureTwo-spool turbofan
Fan hub height35 mm
Fan inner diameter30 mm
Fan outer diameter90 mm
Hub thickness7 mm
Blade angles7° inner / 30° outer

03 / Mathematics

Calculations, not decoration

Ideal compressorT₀₂/T₀₁ = (P₀₂/P₀₁)^((γ−1)/γ)

Ideal isentropic temperature-pressure relation used as the baseline for later cycle analysis.

Compressor workẆc = ṁcp(T₀₂ − T₀₁)

Relates compressor shaft power to mass flow and stagnation-temperature rise.

Net thrustF ≈ ṁeVe − ṁ0V0 + (pe−p0)Ae

General control-volume relation; the present CAD has not been experimentally validated.

04 / Interactive engineering model

3D release pending

No verified STL or browser-ready glTF file is currently available in the project archive. A fake model would damage credibility. This viewer area is intentionally locked until the real export is checked, versioned, and approved for public release.

RAI / MODEL GATESTL / GLB
NOT RELEASEDModel ownership and public-release review required

05 / Documentation

Reports & release record

Technical reportDownload project documentDOCX ↓

Declared limitations

  • Conceptual geometry—not production hardware
  • No validated mass-flow target or cycle deck
  • No CFD, FEA, rotor-dynamics, thermal, acoustic, or experimental validation
  • No certified materials, tolerances, or manufacturing plan
  • No thrust or efficiency claim
  • Public STL/GLB release remains pending