1D Thermodynamical Model of Gas Turbine Engine
The result's identifiers
Result code in IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F20%3A00360292" target="_blank" >RIV/68407700:21220/20:00360292 - isvavai.cz</a>
Result on the web
<a href="https://www.fs.cvut.cz/ustavy/sekce-centrum-leteckeho-a-kosmickeho-vyzkumu/centrum-leteckeho-a-kosmickeho-vyzkumu-12203/centrum-12203/" target="_blank" >https://www.fs.cvut.cz/ustavy/sekce-centrum-leteckeho-a-kosmickeho-vyzkumu/centrum-leteckeho-a-kosmickeho-vyzkumu-12203/centrum-12203/</a>
DOI - Digital Object Identifier
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Alternative languages
Result language
angličtina
Original language name
1D Thermodynamical Model of Gas Turbine Engine
Original language description
Software for calculating the thermodynamic parameters of a turbine aircraft engine based on generally known physical relationships and supplemented with realistically measured characteristics and parameters.
Czech name
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Czech description
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Classification
Type
R - Software
CEP classification
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OECD FORD branch
20304 - Aerospace engineering
Result continuities
Project
<a href="/en/project/EF16_019%2F0000826" target="_blank" >EF16_019/0000826: Center of Advanced Aerospace Technology</a><br>
Continuities
P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)
Others
Publication year
2020
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů
Data specific for result type
Internal product ID
12203_CASR_Parez_VES1.0
Technical parameters
The calculation tool allows the calculation of thermodynamic parameters of the gas turbine engine.The calculation is divided into substructural nodes which are: inlet system, compressor, combustion chamber, turbine and outlet. The calculation works on the basis of the engine steady states. The input parameters are limited by the international standard atmosphere standards used in the calculation of aircraft engines.
Economical parameters
The software works based on scripts in Matlab. The calculation defines the important thermodynamic parameters of the gas turbine engine in steady state operation. The input is arbitrarily set engine operating parameters and specific characteristics of the design nodes. The use of these output parameters is possible when designing new structures and defining boundary conditions during its development. The economic benefit is possible when used by specific entities involved in power generation, development and research of aircraft engines and gas turbines.
Owner IČO
68407700
Owner name
České vysoké učení technické v Praze / FS / centrum leteckého a kosmického výzkumu