Alternative Method to Simulate a Sub-idle Engine Operation in Order to Synthesize Its Control System
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Sergii I. Sukhovii
Abstract
The steady-state and transient engine performances in control systems are usually evaluated by applying thermodynamic engine models. Most models operate between the idle and maximum power points, only recently, they sometimes address a sub-idle operating range. The lack of information about the component maps at the sub-idle modes presents a challenging problem. A common method to cope with the problem is to extrapolate the component performances to the sub-idle range. Precise extrapolation is also a challenge. As a rule, many scientists concern only particular aspects of the problem such as the lighting combustion chamber or the turbine operation under the turned-off conditions of the combustion chamber. However, there are no reports about a model that considers all of these aspects and simulates the engine starting. The proposed paper addresses a new method to simulate the starting. The method substitutes the non-linear thermodynamic model with a linear dynamic model, which is supplemented with a simplified static model. The latter model is the set of direct relations between parameters that are used in the control algorithms instead of commonly used component performances. Specifically, this model consists of simplified relations between the gas path parameters and the corrected rotational speed.
Funding statement: Funding: The work has been performed with the support of the National Polytechnic Institute of Mexico (research project 20131509).
Acknowledgments
Our acknowledgments to ASME for a kind permission to publish this paper.
Nomenclature
- b
coefficient of LDM
- cp
heat capacity
- d
coefficient of LDM
mass flow through a component (engine)
- HPR
high pressure rotor
- Hu
lower caloric value
- J
moment of inertia
work of component
- LDM
linear dynamic model
- LPR
low pressure rotor
torque
power of component
rotational speed
pressure
temperature, time constant
- TC
thermocouple
- t
time
efficiency
time constant of thermocouple
- ω
angular velocity
- Subscripts
air
- br
breakaway
compressor, compressor discharge station
- calc
calculated parameter
- cons
consumer
corrected parameter
- f
fuel
- FT
free turbine
engine inlet
inertia
- HP
parameter of the high pressure rotor
- res
resistance
specific parameter
static parameter
starter
turbine, turbine discharge station
- TC
thermocouple
- torq
torque
- univ
parameter calculated from the universal performance
- wind
windmilling
- *
stagnation parameter
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©2016 by De Gruyter
Articles in the same Issue
- Frontmatter
- Experimental Investigation on the Ignition Delay Time of Plasma-Assisted Ignition
- Effect of Inlet Clearance on the Aerodynamic Performance of a Centrifugal Blower
- Alternative Method to Simulate a Sub-idle Engine Operation in Order to Synthesize Its Control System
- Aerodynamic Design and Numerical Analysis of Supersonic Turbine for Turbo Pump
- A Comparison of Hybrid Approaches for Turbofan Engine Gas Path Fault Diagnosis
- Optimization of a Turboprop UAV for Maximum Loiter and Specific Power Using Genetic Algorithm
- Taguchi Based Regression Analysis of End-Wall Film Cooling in a Gas Turbine Cascade with Single Row of Holes
- Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime
Articles in the same Issue
- Frontmatter
- Experimental Investigation on the Ignition Delay Time of Plasma-Assisted Ignition
- Effect of Inlet Clearance on the Aerodynamic Performance of a Centrifugal Blower
- Alternative Method to Simulate a Sub-idle Engine Operation in Order to Synthesize Its Control System
- Aerodynamic Design and Numerical Analysis of Supersonic Turbine for Turbo Pump
- A Comparison of Hybrid Approaches for Turbofan Engine Gas Path Fault Diagnosis
- Optimization of a Turboprop UAV for Maximum Loiter and Specific Power Using Genetic Algorithm
- Taguchi Based Regression Analysis of End-Wall Film Cooling in a Gas Turbine Cascade with Single Row of Holes
- Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime
