Component Aerodynamics
NASA/pyCycle generic component maps provide the aerodynamic basis for fan, compressor, and turbine performance and are scaled to the engine being modeled.
turbofanmodeling.org
TurboFanModel
Real-Time Physics-Based Turbofan Modeling Framework
TurboFanModel is a real-time system-level model of modern turbofan engine behavior. The framework combines aerodynamic component maps, Brayton-cycle thermodynamics, shaft work balance, fuel control, inlet and exhaust calculations, and numerical integration of transient spool dynamics into a self-contained engine model.
Development and test environment
TurboFanLab
TurboFanLab provides real-time access to engine controls, operating conditions, spool response, fuel flow, EGT, thrust, and shaft-work relationships during model development and validation.
Modeling method
Physics first, with traceable engine definitions
Thermodynamic Cycle
Pressure, temperature, mass flow, fuel addition, turbine work, and exhaust conditions are calculated through the coupled engine flow path.
Real-Time Dynamics
HP and LP spool response is formulated with differential equations and numerical integration techniques such as fourth-order Runge–Kutta.
Traceability
Engine-definition values are identified as published, calculated, estimated, or tuned so that assumptions and validation changes remain visible.
Closed-loop simulation
Real-Time Flight Dynamics Integration
TurboFanModel can be dynamically coupled to a flight simulation that provides data of flight performance for calculating engine performance, placing the engine model into a continuously changing flight environment and creating a genuine closed-loop simulation.
Flight dynamics
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TurboFanModel
Reference engine development
Engine Models
Engine-specific development is maintained as part of the TurboFanModel project. Each engine page records current status, model-definition values, map basis, validation work, and revision progress.
Operational baseline / re-baselining
CFM56-7B24
The current working engine used to develop the real-time model, TurboFanLab test process, and FlightGear integration. Its public-data basis and generic pyCycle component maps are now being reviewed with the same traceable methodology being applied to the GE90.
View CFM56-7B24 model status →Current reference-engine demonstration
GE90-115B
Publicly available GE, NASA, certification, and research data are being used to establish the master parameter set and convert NASA/pyCycle component-map surfaces to GE90 design targets.
View GE90-115B model status →Potential applications
One engine core, several research interfaces
Propulsion controls
Hardware-in-the-loop
Engine health / PHM
Digital-twin research
Hybrid-electric propulsion
Aircraft / propulsion studies
Flight simulation
The engine core is intended to remain independent of the host application, allowing a common engine definition to support laboratory development, aircraft simulation, controls, and research interfaces.
Current review material
Documents
Development documents remain available for download while the engine-model pages provide the current online status.
TurboFan_7 User Manual — Rev 1.13 (DOCX)
Operating guide for TurboFanLab, TurboMgr, TurboModel, networking, parameters, and test workflow
TurboFanModel Framework Overview v0.2 (DOCX)
One-page project description
GE90-115B Modeling Basis v0.1 (DOCX)
Published data, calculations, assumptions, and modeling plan
GE90-115B Master Parameters v0.1 (XLSX)
Working parameter and map-conversion workbook
Point of contact
Contact
Questions, research interest, or collaboration inquiries are welcome.
contact@turbofanmodeling.org
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