Software Development for EECU Platform of Turbofan Engine
-
Bo Gyoung Kim
,
Dohyup Kwak
Abstract
The turbofan engine operation consists of a number of hardware and software. The engine is controlled by Electronic Engine Control Unit (EECU). In order to control the engine, EECU communicates with an aircraft system, Actuator Drive Unit (ADU), Engine Power Unit (EPU) and sensors on the engine. This paper tried to investigate the process form starting to taking-off and aims to design the EECU software mode and defined communication data format. The software is implemented according to the designed software mode.
Acknowledgements
This paper is based on the presentation which was carried out in frames of conference APCATS 2015.
Nomenclature
- ADU
Actuator Driver Unit
- DAQ
Data Acquisition
- EECU
Electronic Engine Control Unit
- EPU
Electrical Power Unit
- FMVsts
Fuel Main Valve status
- FSVsts
Fuel Start Valve status
- GUI
Graphical User Interface
- HIL
Hardware-In-the-Loop
- HUMS
Health and Usage Monitoring System
- ICD
Interface Control Document
- NH
High Pressure Shaft Speed
- NL
Low Pressure Shaft Speed
- PLA
Power Lever Angle
- T6
Exhaust Gas Temperature
- WOW
Weight On Wheels
References
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© 2017 Walter de Gruyter GmbH, Berlin/Boston
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- Numerical Studies on the Performance of Scramjet Combustor with Alternating Wedge-Shaped Strut Injector
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- Nozzle Admittance and Damping Analysis Using the LEE Method
- Software Development for EECU Platform of Turbofan Engine
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Articles in the same Issue
- Frontmatter
- Influence of Structural Parameters on the Performance of Vortex Valve Variable-Thrust Solid Rocket Motor
- Numerical Studies on the Performance of Scramjet Combustor with Alternating Wedge-Shaped Strut Injector
- Investigation of HP Turbine Blade Failure in a Military Turbofan Engine
- Nozzle Admittance and Damping Analysis Using the LEE Method
- Software Development for EECU Platform of Turbofan Engine
- Numerical Study of the Propulsive Performance of the Hollow Rotating Detonation Engine with a Laval Nozzle
- Analysis of Compressor Surge in a Military Turbojet Engine: A Case Study
- The Combined Effects of Surface Roughness with Upstream Wakes on the Boundary Layer Development of an Ultra-High-Lift LPT Blade
- Numerical Investigation of a Model Scramjet Combustor Using DDES
- Flow Field Measurement in Multi-stage Axial Compressor Stator by Using Multi-hole Pneumatic Probes
- Effect of Air Pressure and Gutter Angle on Flame Stability and DeZubay Number for Methane-Air Combustion
- Control of Subsonic and Sonic Jets with Limiting Tabs
