Turbofan Engine System
A model of a turbofan engine with a regulator.
Description
The Turbofan Engine System simulates the operation of a turbofan engine in conjunction with a regulator, calculates the thrust developed and the specific fuel consumption of the engine.
The engine model is a first order system with dimensionless heuristic tables of values for thrust, specific fuel consumption and engine time constant. The thrust is a function of Mach number, the specific fuel consumption is a function of thrust and Mach number, and the engine time constant is a function of thrust. The values in the dimensionless tables depend on the relative values of atmospheric pressure and temperature, the maximum thrust, the smallest engine time constant, its specific fuel consumption and its loss factor.
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The block uses the 1976 COESA atmospheric model. |
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This engine model is a demonstration. It is not recommended to use it as a reference. |
Limitations
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The Mach number should not be greater than 1.
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The engine to be modelled has a high degree of double-circuit capability.
Ports
Input
Throttle position - engine control
scalar | vector
Throttle position. Variable in the range from 0 to 1. The value 0 corresponds to the engine off, the value 1 to the maximum developed thrust.
Data types: Float64.
Mach - Mach number
scalar
Mach number.
Data types: Float64.
Altitude - flight altitude
scalar | vector
Flight altitude, m.
Data types: Float64.
Initial thrust - initial thrust
scalar | vector
Initial value of engine thrust, N.
Data types: Float64.
Parameters
Maximum sea-level static thrust - maximum thrust
45000.0 (by default) | scalar
Maximum sea level engine thrust at M = 0, N.
Fastest engine time constant at sea-level static (sec) - smallest engine time constant
1.0 (by default) | scalar.
Smallest engine time constant at sea level static, sec.
Sea-level static thrust specific fuel consumption - specific fuel consumption
0.35 (By default) | scalar.
Specific fuel consumption per kg of thrust per hour at sea level at M = 0 and maximum thrust, kg/s.
Ratio of installed thrust to uninstalled thrust - loss factor
0.9 (by default) | scalar
Loss factor.