Full-Range Mathematical Modeling of Turboshaft Engine in Aerospace
-
Hanlin Sheng
,
Tianhong Zhang
Abstract
In this paper, an approximate computation method of low-speed component characteristics in aeroengine is used and full-range component characteristics is obtained by combining experimental data above idle. Moreover, based on components matching method and variable specific heat method, a full-range static and dynamic mathematical model of turboshaft engine is built, including start-up state. And the numerical simulation result of the engine whole working process is also showed in this paper. The comparison result between the simulation result and the experimental data shows that, the full-range model built by the computation method of low-speed component characteristics is of a certain accuracy, which can meet the needs of a turboshaft engine semi-physical simulation.
Funding statement: Funding: This work was supported by National Natural Science Foundation of China(No.51176075，No.61104067), Funding of Jiangsu Innovation Program for Graduate Education (No.CXZZ13_0176).
References
1. Stamatis A, Mathioudakis K, Ruiz J, et al. Real-time engine model implementation for adaptive control and performance monitoring of large civil turbofans. ASME paper, 2001 (2001-GT): 0362.10.1115/2001-GT-0362Search in Google Scholar
2. Sellers JF, Daniele CD A Program For Calculating Steady-State and Transient Performance of Turbojet and Turbofan Engines. NASA Technical Note TN D-7901, Cleveland, April 1975. 208.Search in Google Scholar
3. Daniele CJ, Krosel SM, Szuch RJ. Digital Computer Program for Generating Dynamic Turbofan Engine Model (DIGTEM). NASA Technical Memorandum 83446. Cleveland, p. 161. 1983.Search in Google Scholar
4. Agrawal RK, Yunis M. A generalized mathematical model to estimate gas turbine starting characteristics. J Eng Gas Turbines Power 1982;104:194–201.10.1115/81-GT-202Search in Google Scholar
5. De-You Y, Zhong-Fan M. A dynamic model of a turbojet in starting at high altitude. The Sixth International Symposium on Air Breathing Engines, AIAA Paper, 1983:83–7045.Search in Google Scholar
6. Morita M, Sasaki M, Torisaki T. Restart characteristics of turbofan engines. International Symposium on Air Breathing Engines, 9th, Athens, Greece. 1989: 1200–1206.Search in Google Scholar
7. Chappell MA, McLaughlin PW. Approach of modeling continuous turbine engine operation from startup to shutdown. J Propul Power 1993;9:466–71.10.2514/6.1991-2373Search in Google Scholar
8. Rowen WI. Simplified mathematical representations of heavy-duty gas turbines. J Eng Gas Turbines Power 1983;105:865–9.10.1115/1.3227494Search in Google Scholar
9. Hannett LN, Khan AH. Combustion turbine dynamic model validation from tests. Power Syst IEEE Trans 1993;8:152–8.10.1109/59.221261Search in Google Scholar
10. Ailer P, Santa I, Szederkényi G, et al. Nonlinear model-building of a low-power gas turbine. Transp Eng 2001;29:117–35.Search in Google Scholar
11. Camporeale SM, Fortunato B, Mastrovito M. A modular code for real time dynamic simulation of gas turbines in simulink. J Eng Gas Turbines Power 2006;128:506–17.10.1115/1.2132383Search in Google Scholar
12. Kyprianidis KG, Kalfas AI. Dynamic performance investigations of a turbojet engine using a cross-application visual oriented platform. Aeronautical J 2008;112:161–70.10.1017/S0001924000002098Search in Google Scholar
13. Sexton WR. A method to control turbofan engine starting by varying compressor surge valve bleed. Virginia Polytechnic Institute and State University, 2001.Search in Google Scholar
14. Zhou W, Huang J, Dou J. Development of component-level startup model for a turbofan engine. J Aerospace Power 2006;2:003.Search in Google Scholar
15. Lei J, Chen C, Li J, et al. A study of turbofan component characteristic based on back-propagation network. Gas Turbine Exp Res 2003;4:004.Search in Google Scholar
16. Huang X, Zheng X. Research on startup model of aircraft engine based on stage-stacking method. Acta Aeronautica Et Astronautica Sinica-Series A and B- 2005;26:540.Search in Google Scholar
©2016 by De Gruyter
Articles in the same Issue
- Frontmatter
- Full-Range Mathematical Modeling of Turboshaft Engine in Aerospace
- Modeling and HIL Simulation of Flight Conditions Simulating Control System for the Altitude Test Facility
- Investigation of Detailed Flow in a Variable Turbine Nozzle
- A Study on the Installed Performance Seeking Control for Aero-Propulsion under Supersonic State
- Study of the Standard k-ε Model for Tip Leakage Flow in an Axial Compressor Rotor
- Experimental Study of Propulsion Performance by Single-Pulse Rotating Detonation with Gaseous Fuels-Oxygen Mixtures
- Finite Element Analysis for Turbine Blades with Contact Problems
- CFD Modeling of Mixed-Phase Icing
- Effect of Steam Addition on the Flow Field and NOx Emissions for Jet-A in an Aircraft Combustor
- An Integrated Optimization Design Method Based on Surrogate Modeling Applied to Diverging Duct Design
- Numerical Study of Unsteady Properties of Ethylene/Air Turbulent Jet Diffusion Flame with Detached Eddy Simulation
- Influence of Rotor-Stator Interaction on Flow Stability in Centrifugal Pump Based on Energy Gradient Method
Articles in the same Issue
- Frontmatter
- Full-Range Mathematical Modeling of Turboshaft Engine in Aerospace
- Modeling and HIL Simulation of Flight Conditions Simulating Control System for the Altitude Test Facility
- Investigation of Detailed Flow in a Variable Turbine Nozzle
- A Study on the Installed Performance Seeking Control for Aero-Propulsion under Supersonic State
- Study of the Standard k-ε Model for Tip Leakage Flow in an Axial Compressor Rotor
- Experimental Study of Propulsion Performance by Single-Pulse Rotating Detonation with Gaseous Fuels-Oxygen Mixtures
- Finite Element Analysis for Turbine Blades with Contact Problems
- CFD Modeling of Mixed-Phase Icing
- Effect of Steam Addition on the Flow Field and NOx Emissions for Jet-A in an Aircraft Combustor
- An Integrated Optimization Design Method Based on Surrogate Modeling Applied to Diverging Duct Design
- Numerical Study of Unsteady Properties of Ethylene/Air Turbulent Jet Diffusion Flame with Detached Eddy Simulation
- Influence of Rotor-Stator Interaction on Flow Stability in Centrifugal Pump Based on Energy Gradient Method
