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ZP/LTR Control for Turbofan Engines
Volume 4: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education, 2000Among the control methods which have loop transfer recovery ability, such as the LQG/LTR approach, the design of target feedback loop (TFL) is one important step of the procedure for control system design because the performance of the control system designed is limited by its TFL.
Zhengping Feng, Jianguo Sun, Qiuhong Li
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LPV MODELING OF A TURBOFAN ENGINE
IFAC Proceedings Volumes, 2005Abstract This article describes the application of quasi-LPV modeling techniques to an industrial military turbofan engine simulator developed by Snecma Moteurs, the French aerospace propulsion company. Two approaches are used, classical Jacobian linearization and velocity based linearization. First, we present briefly the theoretical aspects of both
Luc Reberga +3 more
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The Emergence of the Turbofan Engine
2000If you have looked out the window of an airplane lately, you may have noticed that jet engines are gradually getting shorter and fatter. You will see 737s, the most common airliner in service, with two types of engines of distinctly different shapes. The older models have long, stovepipe-shaped engines under the wings, where the newer ones (or older ...
George E. Smith, David A. Mindell
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Performance Design of a Turbofan Engine Using Multi-objective Particle Swarm Optimization (MOPSO)
International Journal of Aeronautical and Space Sciences, 2022Dong-Sun Lee, H. Sung
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Research Related to Turbofan Engines
Theoretical and Natural ScienceThe development of aerospace technology has become a topic of daily concern and discussion for the benefit of all mankind. As the global temperature rises, the living environment of human beings is threatened, and scientists have decided to work on the development of aerospace technology in order to solve this problem and meet people's needs.
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Optimum Cycle Parameters for Turbofan Engines
Volume 1A: General, 1970This paper presents closed-form solutions for optimum compressor pressure ratio, bypass ratio and fan pressure ratio, given the turbine inlet temperature, component efficiencies and flight Mach number for a turbofan engine. In addition a simple procedure is outlined for obtaining the optimum combination of these quantities and a sample calculation is ...
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