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ISBN-10: 1634833368

ISBN-13: 9781634833363

In early levels of an plane layout method, it is important to figure out the minimal thrust or energy requirement and swiftly choose definitely the right propulsion, which comprises a good coupling among flight functionality and missions’ analyses, engine functionality prediction and layout optimization. the 1st bankruptcy of this e-book presents an outline of ways to figure out the minimal thrust or strength specifications for jet and propeller driving force delivery plane. the second one bankruptcy examines the great modeling and layout of creation strategies of airplane meeting. the ultimate bankruptcy makes a speciality of the computational modeling of the Be-200 and Be-103 amphibious plane types. (Imprint: Nova)

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The off-design performance of any gas turbine engine can be expressed as functional relationships between non-dimensional quantities. According to Cohen et al. [35], for a given engine of fixed geometry, burning a given fuel, the thrust F   f1  N  , M 0  and SFC SFC    f2 N  , M0  are given as function of engine rotational speed N and andwhichare ratios of ambient pressure and temperature to that at sea level. One can find thrust and specific fuel consumption for any specified combination of engine speed and flight conditions, but the major difficulties are the exact forms of relations f1, f2 are not known and vary depending on engines.

Kurzke [47], with the help of a gradient based optimization algorithm coupled to a component-level code GasTurb, conducted an optimization task to adapt an existing engine to a new application. Sane et al. [48] utilized the response surface surrogate optimizer for the optimum design of a high-bypass turbofan. Farhat et al. [49] conducted an optimization of a turbo-shaft engine, where the conflicting objective are the specific thrust, specific fuel consumption, output shaft power and overall efficiency were optimized, simultaneously, and showed that the results of 4-objective optimization provide more choices for the optimal design than the 2-objective optimization.

The throttle ratio r  Tt 4 max Tt 4 sls relates TIT values at different flight conditions to its maximum. Here a throttle ratio equal to 1 is considered. From the power balance of HP spool, total temperature ratio and pressure ratio of HP compressor are updated as follows.  CH  1 k1  b and   1     1 CH sCH CH  r CL a  a 1 (53) The relations between the core and bypass streams, considering a choked NGV of HP turbine yields new bypass ratio as follows:   k2 F  CL CH b MFP19  r F (54) From the power balance of LP spool, the fan total temperature ratio and pressure ratio are updated as follows:  F 1  k3 b 1   TL  F  1  sF  F  1 a 1   k4  r  a 1 (55) Similar relations are derived for the LP spool.

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Aircraft Design, Technology and Safety


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