Simulation of a High Fidelity Turboshaft Engine-Alternator Model for Turboelectric Propulsion System Design and Applications
-
I. Yazar
Abstract
The term sustainability became a popular subject both in the automotive industries and in the aerospace industries. Increasing and threatening environmental pollution problems and reduction in limited fuel sources are motivating either industries and academicians to develop alternative power systems to sustain more healthier and economical life in the long term. One innovation that has been researched in the automotive industry is all electric and hybrid electric propulsion concepts. These concepts have also been proposed as alternative solutions for aviation. These novel propulsion technologies are composed of a gas turbine/internal combustion engine structure (necessary for hybrid electric and turboelectric propulsion systems) and/or energy storage components (battery, fuel cell and so on.) with multiple electric motors respectively. In this paper, simulation of a high fidelity turboshaft engine-alternator model for turboelectric propulsion system is derived. To develop an aero-thermal engine model, GE T700 turboshaft engine data is used and constructed model is connected to an alternator model on MATLAB/Simulink environment. Open-loop simulations are carried out and satisfactory results are obtained.Simulation results are compared to the real engine design point data. Results show that there are acceptable differences between the simulation results and the real engine data. The power balances between compressor - high pressure turbine and power turbine – alternator are proven in the mathematical model. It is expected that the proposed model can be easily extended to power system design and power management studies in turboelectric propulsion systems and also in other suitable novel propulsion systems.
Nomenclature
- ANFIS
Adaptive Neuro-Fuzzy Inference System
Bleed flow fractions
Specific heat value of gas, J/kgK
Generic function
Entalpy value at the compressor inlet, J/kg
Enthalpy value at the compressor outlet, J/kg
Enthalpy value at the combustion chamber, J/kg
Enthalpy value at the HPT outlet, J/kg
- HPT
High-power turbine (gas generator turbine)
HPT moment of inertia
PT moment of inertia
- LHV
Lower heating value
Mass flow rate at the compressor outlet, kg/s
Corrected mass flow rate inside the compressor, kg/s
Mass flow rate at the first volume, kg/s
Mass flow rate at combustion chamber, kg/s
Mass flow rate at HPT, kg/s
Bleed air mass flow rate, kg/s
Fuel flow rate, kg/s
Mass flow rate difference between the input and output of the component, J/kg
Compressor-HPT shaft rotational speed, rpm
Corrected compressor-HPT shaft rotational speed
PT shaft rotational speed, rpm
- PT
Power turbine
Ambient pressure, Pa
Compressor power, Watts
Generator power, Watts
HPT power, Watts
HPT power loss, Watts
Load applied on the power turbine, Watts
PT power, Watts
PT power loss, Watts
Component output pressure, Pa
Compressor input pressure, Pa
Combustion chamber input pressure, Pa
Combustion chamber output pressure, Pa
Ambient temperature, K
Component output temperature, K
Compressor input temperature, K
Compressor output temperature, K
Combustion chamber temperature, K
Gas constant
Volume
Combustion chamber pressure loss coefficient
Specific heat ratio
Non-dimensional pressure,
Non-dimensional temperature,
Combustion chamber time constant
Compressor pressure ratio
Combustor efficiency
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© 2019 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Numerical Study of Combinations of Strut and Cavity in a Round Supersonic Combustor
- Design and Numerical Analysis of a Forepart Rotation Vane for a Variable Nozzle Turbine
- Aerodynamic Efficiency Optimization of the 1st Stage of Transonic High Pressure Turbine through Lean and Sweep Angles
- The Effect of Dilution Air Jets on Aero-Engine Combustor Performance
- Simulation of a High Fidelity Turboshaft Engine-Alternator Model for Turboelectric Propulsion System Design and Applications
- Effects of Non-axisymmetric Casing Grooves Combined with Airflow Injection on Stability Enhancement of an Axial Compressor
- Exhaust System for Radial and Axial-Centrifugal Compressor with Pipe Diffuser
- Advanced Exergy Analysis of a Turbofan Engine (TFE): Splitting Exergy Destruction into Unavoidable/Avoidable and Endogenous/Exogenous
- A Preliminary Design System for Turbine Discs
- Tensile Behavior and Microstructural Evolution of the Polycrystalline Nickel-Based Superalloy Applied in Turbine Disk
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Numerical Study of Combinations of Strut and Cavity in a Round Supersonic Combustor
- Design and Numerical Analysis of a Forepart Rotation Vane for a Variable Nozzle Turbine
- Aerodynamic Efficiency Optimization of the 1st Stage of Transonic High Pressure Turbine through Lean and Sweep Angles
- The Effect of Dilution Air Jets on Aero-Engine Combustor Performance
- Simulation of a High Fidelity Turboshaft Engine-Alternator Model for Turboelectric Propulsion System Design and Applications
- Effects of Non-axisymmetric Casing Grooves Combined with Airflow Injection on Stability Enhancement of an Axial Compressor
- Exhaust System for Radial and Axial-Centrifugal Compressor with Pipe Diffuser
- Advanced Exergy Analysis of a Turbofan Engine (TFE): Splitting Exergy Destruction into Unavoidable/Avoidable and Endogenous/Exogenous
- A Preliminary Design System for Turbine Discs
- Tensile Behavior and Microstructural Evolution of the Polycrystalline Nickel-Based Superalloy Applied in Turbine Disk
