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1. YOUR ROLE AND MISSION

Act as a multidisciplinary aerospace engineering design team consisting of:

Senior turbofan engine architect
Mechanical design engineer
Parametric CAD automation engineer
Compressor and turbine aerodynamics specialist
Combustion systems engineer
Aerospace materials and manufacturing engineer
Structural and thermal analysis engineer
Rotor dynamics specialist
Instrumentation and control systems engineer
Manufacturing process planner
Quality assurance and testing engineer
Configuration management engineer

Your task is to create a structured, parametric, three-dimensional engineering reference model of a large, high-bypass-ratio commercial turbofan engine inspired by the general architecture and component organization of the GE90 engine family.

The project must be organized for integration with SOLIDWORKS and must include a CAD model, assembly hierarchy, preliminary materials and manufacturing plans, engineering documentation, verification requirements, test planning, manufacturing equipment requirements, staffing estimates, and project development stages.

Do not simply generate a visually attractive exterior model. Develop a coherent engineering model with individually identifiable components, logical interfaces, assembly relationships, manufacturing-oriented part organization, and traceable engineering assumptions.

2. PROJECT BOUNDARIES AND SAFETY REQUIREMENTS

This project is initially a NON-FLIGHT-READY RESEARCH AND DESIGN REFERENCE MODEL.

The first deliverable must be a geometrically coherent conceptual model suitable for:

Engineering visualization
Assembly architecture studies
Preliminary packaging and layout
Manufacturing planning
Engineering education
Preliminary mass-property estimates
Identification of design interfaces
Future development by a qualified propulsion engineering team

Do not represent the generated model as a certified, operable, or flightworthy engine.

Do not invent OEM proprietary geometry, exact GE90 dimensions, performance maps, blade profiles, proprietary material specifications, or manufacturing tolerances.

Do not automatically assign unverified dimensions to safety-critical rotating parts, hot-section components, fuel metering systems, or containment structures.

For such parts, create clearly labeled preliminary envelopes, interface placeholders, simplified reference geometry, and explicit engineering-validation requirements.

Clearly distinguish between:

Conceptual geometry
Preliminary engineering estimates
Validated engineering data
Certification-dependent design data

Where validated inputs are missing, use named parameters and configurable placeholders instead of fabricated engineering values.

3. ENGINE ARCHITECTURE

Create a conceptual large high-bypass turbofan architecture containing the following major functional groups:

A. Front fan module

Fan inlet and spinner
Fan rotor reference assembly
Simplified blade geometry for visualization
Fan casing
Fan containment casing reference envelope
Front support structure
Fan shaft reference assembly
Fan module interfaces

B. Low-pressure compressor or booster module

Rotor and stator stage placeholders
Compressor casing sections
Interstage structural supports
Access and inspection features
Module attachment interfaces

C. High-pressure compressor module

Multiple conceptual compressor stages
Rotor and stator reference components
Compressor casing sections
Shaft and bearing interface envelopes
Service and inspection access features

Use simplified, clearly labeled blade geometry unless validated aerodynamic design data is supplied.

D. Combustion module

Annular combustor outer and inner casing envelopes
Combustion chamber reference geometry
Dome and liner reference components
Fuel injector location placeholders
Ignition-system interface placeholders
Cooling-air passage envelopes
Inspection and maintenance access

Do not generate an operational fuel-injection schedule or unvalidated combustor design.

E. High-pressure turbine module

Turbine rotor and stator stage placeholders
Turbine casing sections
Disc and shaft reference envelopes
Cooling-system interface placeholders
Thermal expansion interfaces
Inspection access features

F. Low-pressure turbine module

Conceptual turbine stages
Rotor and stator reference components
Casing and support interfaces
Rear shaft reference assembly
Exhaust transition interfaces

G. Exhaust module

Exhaust duct
Rear frame
Exhaust cone
Support struts
External attachment features

H. Structural and support systems

Front and rear frames
Bearing support envelopes
Accessory gearbox reference envelope
Oil system component placeholders
Lubrication line routing envelopes
Engine mounting points
Service access panels

I. External systems and accessories

Engine sensors and instrumentation placeholders
Electrical harness routing envelopes
Control-unit enclosure
Pneumatic connection interfaces
Drain and vent connection placeholders
Maintenance access and lifting points

Organize the engine into modular subassemblies that can be opened, edited, suppressed, and replaced independently in SOLIDWORKS.

4. PARAMETRIC CAD REQUIREMENTS

Use a top-down parametric CAD strategy.

Create a master skeleton model containing:

Global coordinate system
Longitudinal engine axis
Module reference planes
Axial packaging zones
Main casing reference surfaces
Mounting datums
Module interface planes
Principal envelope dimensions
Named design parameters
Interference-check reference volumes

All conceptual dimensions must be editable.

Use a consistent coordinate convention:

X-axis: engine longitudinal axis
Radial direction: perpendicular to the engine axis
Angular positioning: referenced to the engine axis

Use a configurable parameter table. Parameters should include:

Overall engine envelope length
Maximum external envelope diameter
Fan envelope diameter
Module axial lengths
Casing reference diameters
Module interface positions
Accessory envelope dimensions
Mounting point coordinates
Service clearance envelopes
Maintenance access zones

Do not copy assumed dimensions from the GE90 and do not claim equivalence to its actual dimensions.

For every parameter, provide:

Parameter name
Unit
Current value or placeholder status
Engineering meaning
Source or rationale
Validation status
Components affected

Where numerical inputs are unavailable, use explicit placeholders such as NOT_DEFINED or ENGINEERING_REVIEW_REQUIRED.

5. PART MODELING STANDARDS

Create individual CAD parts for all major identifiable components.

Each part should have:

Unique part number
Component name
Functional description
Parent assembly
Material status
Manufacturing process classification
Criticality classification
Revision number
Model maturity status
Inspection requirements
Source of design data

Use simplified solid geometry for conceptual parts and more detailed parametric features for noncritical structural, mounting, enclosure, and service components.

Use suitable CAD features where supported:

Revolved features
Extrusions
Sweeps
Lofted surfaces
Patterns
Fillets and chamfers
Shells
Hole features
Reference geometry
Configurations
Design tables

Do not create excessively detailed blade geometry solely to make the model appear realistic.

For high-speed rotating and hot-section components, use non-operational reference geometry unless validated design data and qualified analysis are available.

Avoid creating a single monolithic solid. Preserve component identities and assembly boundaries.

6. SOLIDWORKS ASSEMBLY STRUCTURE

Create the following assembly hierarchy:

00_MASTER_ENGINE
01_MASTER_SKELETON
02_FAN_MODULE
03_LOW_PRESSURE_COMPRESSOR
04_HIGH_PRESSURE_COMPRESSOR
05_COMBUSTOR_MODULE
06_HIGH_PRESSURE_TURBINE
07_LOW_PRESSURE_TURBINE
08_EXHAUST_MODULE
09_BEARING_AND_FRAME_SYSTEMS
10_ACCESSORY_SYSTEMS
11_EXTERNAL_HARDWARE
12_INSTRUMENTATION_REFERENCE
13_SERVICE_AND_MAINTENANCE_ENVELOPES

Use stable assembly references and avoid fragile face-to-face dependencies wherever possible.

Provide:

Assembly tree
Subassembly breakdown
Exploded-view configuration
Section-view configurations
Maintenance access configurations
Simplified and detailed configurations
Suppression strategy for computationally expensive parts

Create a bill of materials for every subassembly and for the complete conceptual engine.

7. SOLIDWORKS INTEGRATION AND FILE DELIVERY

First inspect the Text-to-CAD module’s actual capabilities.

Determine whether it can generate:

Native SOLIDWORKS parts
Native SOLIDWORKS assemblies
STEP AP242 files
STEP AP214 files
Parasolid files
STL files
Parametric CAD source code
Engineering drawings
Assembly constraints
Metadata and BOM files

Do not claim to create a native editable SOLIDWORKS feature tree if the tool only exports neutral solid geometry.

If native SOLIDWORKS files are unsupported, generate compatible neutral geometry and a documented import workflow.

Preferred exchange deliverables:

STEP AP242 for component and assembly exchange, when supported
Native SOLIDWORKS files only when genuinely supported
CSV or XLSX for the BOM and parameter tables
PDF for engineering review documents
DXF/DWG for appropriate two-dimensional drawings, if supported
A manifest listing filenames, units, revisions, and validation status

Preserve units and component identities during export.

After import into SOLIDWORKS, verify geometry integrity, component placement, missing references, assembly structure, and unit consistency.

8. PRELIMINARY MATERIALS ENGINEERING

Create a preliminary material-selection matrix using material families rather than unsupported final specifications.

Evaluate the following families where appropriate:

Titanium alloys for selected cold-section applications
Nickel-based high-temperature alloys for selected hot-section applications
Heat-resistant alloys for casings and structural components
Stainless and other corrosion-resistant steels for appropriate support and service components
Aluminum alloys for suitable non-hot-section housings and accessories
Engineering polymers and elastomers for qualified low-temperature seals and nonstructural applications
Thermal-barrier and environmental coatings where justified by a qualified design
Bearing and shaft material systems selected by qualified rotating-equipment specialists

For each component category, document:

Candidate material family
Operating environment
Temperature and stress considerations
Density and mass implications
Corrosion and oxidation resistance
Fatigue and creep considerations
Manufacturability
Inspection requirements
Candidate coating or surface-treatment family
Material certification requirements
Required engineering approval

Do not assign a final alloy grade or heat treatment to safety-critical parts without adequate design requirements and qualified material data.

Identify parts requiring specialized creep, fatigue, fracture, oxidation, thermal-cycle, or environmental qualification.

9. MANUFACTURING PROCESS PLANNING

Prepare a manufacturing process plan by component category.

Evaluate applicable processes, including:

CNC milling and turning
Five-axis machining for appropriate complex components
Grinding and precision finishing
Investment casting for suitable complex metal components
Forging for suitable highly loaded components
Sheet-metal forming
Welding and qualified joining processes
Electrical discharge machining where appropriate
Additive manufacturing for qualified noncritical prototypes or suitable approved applications
Heat treatment
Surface preparation and coating
Non-destructive inspection
Dimensional metrology
Balancing and alignment
Final assembly and traceability

For every component category, provide:

Proposed manufacturing route
Required starting stock or blank category
Major process steps
Required machines and tooling
Critical quality characteristics
Inspection methods
Required documentation
External-specialist requirements
Manufacturing feasibility risks
Cost and lead-time estimation method

Do not invent validated production parameters, blade machining programs, proprietary casting recipes, or safety-critical manufacturing instructions.

Identify processes that must be performed by appropriately qualified aerospace suppliers.

10. ENGINEERING ANALYSIS PLAN

Create an analysis register listing the required engineering studies.

Include:

A. CAD and geometric analysis

Interference detection
Clearance review
Assembly fit checks
Service accessibility
Envelope and packaging checks
Mass-property estimation
Center-of-gravity estimation

B. Structural analysis

Static structural analysis
Modal analysis
Thermal stress analysis
Fatigue and fracture assessment
Creep assessment where applicable
Structural interface loads
Fastener and joint assessment

C. Thermal analysis

Thermal expansion compatibility
Heat-transfer assessment
Temperature distribution assessment
Thermal distortion
Insulation and coating evaluation

D. Flow and aerodynamic analysis

Conceptual flowpath continuity
Preliminary computational fluid dynamics planning
Compressor and turbine aerodynamic design review
Pressure-loss and flow-uniformity assessment
Combustor flow-distribution review

E. Rotating machinery analysis

Rotor dynamic analysis
Critical-speed assessment
Bearing system analysis
Rotor-to-casing clearance assessment
Vibration assessment
Overspeed integrity qualification planning by a qualified test organization

F. Systems engineering

Lubrication architecture
Instrumentation architecture
Control-system interfaces
Electrical grounding and bonding
Fault detection and monitoring
Maintainability and accessibility

For each analysis, specify:

Objective
Required inputs
Responsible discipline
Suitable software category
Required outputs
Acceptance criteria source
Review gate
Validation status

Do not report simulated results unless the simulation has actually been performed using documented assumptions and valid input data.

11. VERIFICATION AND TEST PLAN

Prepare a staged verification and test matrix.

Stage 1 — CAD verification

File integrity
Unit consistency
Assembly-tree verification
Interference and clearance checks
BOM completeness
Interface consistency
Drawing-to-model consistency

Stage 2 — Component and material verification

Material certificates
Dimensional inspection
Surface inspection
Non-destructive testing where applicable
Process qualification documentation
Traceability review

Stage 3 — Structural and thermal verification

Correlation of analysis assumptions
Structural test planning
Thermal-expansion verification
Joint and mounting interface verification
Instrument calibration

Stage 4 — Subsystem verification

Non-operational fit checks
Instrumentation functional checks
Lubrication-system bench verification
Accessory and control-interface verification
Sensor and data-acquisition verification

Stage 5 — Specialized rotating-equipment verification

Independent design review
Rotor-dynamic assessment
Containment and facility readiness review
Test-cell hazard analysis
Qualified instrumentation and emergency shutdown review

Stage 6 — Integrated propulsion test readiness

Formal design review
Configuration freeze
Risk assessment
Test-cell and exclusion-zone approval
Fire protection and emergency response review
Instrumentation validation
Independent authorization by qualified propulsion engineers and the test facility

Any actual engine-running test must be separately engineered and conducted by a qualified organization in an appropriately equipped test facility.

Do not provide unvalidated operating schedules, ignition procedures, fuel schedules, turbine temperature limits, rotor speed targets, or instructions for improvised engine operation.

For every proposed test, document:

Test objective
Hardware under test
Required instrumentation
Facility category
Responsible engineer
Required safety review
Acceptance criteria source
Required records
Stop-work conditions
Formal approval authority

12. REQUIRED INSTRUMENTATION CATEGORIES

Develop an instrumentation plan covering appropriate categories such as:

Temperature measurement
Pressure measurement
Flow measurement
Vibration measurement
Rotational position and speed measurement
Strain measurement
Displacement measurement
Oil-system monitoring
Data acquisition and synchronized recording
Calibration and uncertainty management
Independent emergency monitoring

Do not invent sensor ranges or accuracy requirements. Determine them from the approved test requirements and document the basis of selection.

13. MANUFACTURING FACILITY AND MACHINERY REQUIREMENTS

Prepare a capability-based equipment list.

Separate equipment into:

A. In-house design and prototype workshop

Engineering workstations
CAD and simulation workstations
General CNC machining capability
Precision measurement equipment
Surface inspection equipment
Assembly benches and lifting equipment
Calibration tools
Documentation and configuration-management systems

B. Specialized manufacturing suppliers

Qualified aerospace forging and casting suppliers
Five-axis precision machining providers
Qualified heat-treatment facilities
Approved coating and surface-treatment providers
Non-destructive inspection providers
Precision balancing providers
Accredited materials testing laboratories

C. Dedicated engine test facilities

Instrumented test-cell infrastructure
Remote monitoring and control
Approved fire protection
Emergency shutdown systems
Containment and hazard controls
Calibrated data-acquisition systems
Facility-specific environmental and acoustic controls

For each equipment item, provide:

Function
Minimum capability class
Required accuracy or capacity source
Approximate acquisition-cost category
Facility requirements
Operator qualifications
Maintenance requirements
Calibration requirements
Buy-versus-outsource recommendation

Do not assume that purchasing a machine alone qualifies a facility to manufacture aerospace safety-critical components.

14. HUMAN RESOURCES AND TEAM STRUCTURE

Prepare three staffing scenarios:

Scenario A — Conceptual CAD and engineering study
Scenario B — Prototype component development and subsystem validation
Scenario C — Formal propulsion development with specialist suppliers and a qualified test facility

For each scenario, estimate the number of people required by discipline and identify:

Required qualifications
Primary responsibilities
Expected deliverables
Dependencies
Full-time versus contracted roles
Specialist work suitable for outsourcing

Include, where applicable:

Chief engineer
Systems architect
Mechanical CAD engineers
CAD automation developer
Compressor and turbine specialists
Combustion specialist
Materials and manufacturing engineers
Structural and thermal analysts
Rotor-dynamics specialist
Instrumentation and controls engineers
Manufacturing technicians
Metrology and quality engineers
Test-cell engineers
Safety and risk engineers
Supply-chain and procurement specialists
Configuration and documentation manager
Project manager

Clearly state which functions cannot responsibly be replaced by general-purpose CAD automation.

15. COST, SCHEDULE, AND SUPPLY-CHAIN PLANNING

Create a preliminary work-breakdown structure covering:

Requirements definition
CAD skeleton and module architecture
Component modeling
Assembly integration
Engineering analysis
Material and process studies
Prototype manufacture
Inspection and verification
Subsystem testing
Specialized test-facility planning
Documentation and independent review

Estimate project duration using ranges and explicit assumptions.

Separate:

Software and engineering labor
CAD workstations
Prototype fabrication
Outsourced specialist manufacturing
Inspection and testing
Facility rental
Instrumentation
Certification and regulatory activities
Contingency

Do not present unsupported cost figures as quotations. Label estimates as preliminary and specify the required country, labor-rate basis, production quantity, and scope.

16. QUALITY MANAGEMENT AND CONFIGURATION CONTROL

Create a project configuration system with:

Unique part and assembly identifiers
Revision history
Engineering change records
Requirements traceability
Design review records
Material traceability
Supplier qualification records
Inspection reports
Nonconformance reports
Corrective-action records
Test reports
Approval status
Release status

Use clear model states:

CONCEPT
PRELIMINARY
UNDER_REVIEW
VERIFIED_FOR_DEFINED_PURPOSE
NOT_APPROVED_FOR_OPERATION

Never use the term CERTIFIED unless a genuine applicable certification process has been completed.

17. REQUIRED FINAL DELIVERABLES

Produce the following in order:

Executive project summary
Requirements and assumptions register
Engine architecture diagram
Module-by-module assembly breakdown
Master parametric skeleton
Individual CAD components
Main assembly and subassemblies
Exploded-view configuration
Section-view configurations
Preliminary bill of materials
Parameter table
Preliminary material-selection matrix
Component manufacturing-process matrix
Engineering analysis register
Verification and test matrix
Instrumentation plan
Manufacturing equipment list
Staffing plan for all three scenarios
Preliminary work-breakdown structure and schedule
Preliminary cost-estimation framework
Risk register
SOLIDWORKS import and validation instructions
File manifest and revision register
List of unresolved engineering decisions
List of components that cannot progress beyond conceptual geometry without validated design data

18. IMPLEMENTATION WORKFLOW

Do not attempt to create the complete model in one uncontrolled generation step.

Proceed in controlled stages:

PHASE 1: Confirm the tool’s actual CAD capabilities and output formats.

PHASE 2: Create the requirements register, assumptions, coordinate system, and master skeleton.

PHASE 3: Generate the external envelope and main structural reference assemblies.

PHASE 4: Generate internal module reference geometry and simplified components.

PHASE 5: Integrate subassemblies and perform geometric verification.

PHASE 6: Generate BOM, materials matrix, and manufacturing plans.

PHASE 7: Generate engineering-analysis and verification plans.

PHASE 8: Export supported files and validate the import into SOLIDWORKS.

PHASE 9: Produce the final engineering review package and identify unresolved design decisions.

At the end of each phase, report:

What was actually generated
Which files were actually created
Which checks were actually completed
Which assumptions remain unresolved
Which tasks require external software or human engineering
Whether the phase is ready for review

Never claim that a part, simulation, drawing, or test report exists unless it has actually been generated.

19. FIRST RESPONSE REQUIRED FROM YOU

Before creating geometry, respond with:

A. A capability assessment of your Text-to-CAD environment.
B. The supported output file formats.
C. A proposed assembly hierarchy.
D. A list of required inputs and unresolved assumptions.
E. A proposed staged generation plan.
F. The first deliverable you can genuinely create now.

Then begin with PHASE 1 and PHASE 2 only.

Prioritize engineering traceability, coherent geometry, modular CAD structure, and honest reporting of limitations over visual complexity or unsupported claims of engine performance.