The geometric characteristics of the front and the length selection for the combustion chamber of direct flow type

A method has been developed for selecting the geometric characteristics of the front and the length of the direct-flow combustion chamber. Afterburner combustion chambers are of the ramjet type and are used for a short-term increase in the thrust of a gas turbine engine during takeoff, for overcomin...

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Autor principal:	Дмитрий Викторович Козел
Formato:	article
Lenguaje:	EN RU UK
Publicado:	National Aerospace University «Kharkiv Aviation Institute» 2021
Materias:	прямоточная камера сгорания стабилизаторы пламени фронтовое устройство полнота сгорания топлива потери полного давления Motor vehicles. Aeronautics. Astronautics TL1-4050
Acceso en línea:	https://doaj.org/article/9393cd90f53b4fe18394405d972e19f0
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spelling	oai:doaj.org-article:9393cd90f53b4fe18394405d972e19f02021-11-09T07:53:52ZThe geometric characteristics of the front and the length selection for the combustion chamber of direct flow type1727-73372663-221710.32620/aktt.2021.4sup2.03https://doaj.org/article/9393cd90f53b4fe18394405d972e19f02021-08-01T00:00:00Zhttp://nti.khai.edu/ojs/index.php/aktt/article/view/1472https://doaj.org/toc/1727-7337https://doaj.org/toc/2663-2217A method has been developed for selecting the geometric characteristics of the front and the length of the direct-flow combustion chamber. Afterburner combustion chambers are of the ramjet type and are used for a short-term increase in the thrust of a gas turbine engine during takeoff, for overcoming the sound barrier by an aircraft and for flying at supersonic speed, and for making maneuvers. As part of ramjet engines, ramjet combustion chambers are used as the main combustion chambers in which the process of fuel combustion and heat supply to the working fluid is ensured. The developed method for selecting the geometric characteristics consists in optimizing the main operating characteristics of the combustion chamber. Mathematical models are proposed for describing the dependence of the total pressure loss, the combustion efficiency and the range of stable operation of the combustion chamber against the parameters of the flow at the inlet to the combustion chamber and the geometric characteristics of the front device and the length of the combustion chamber. The analysis of the dependences of the combustion chamber working characteristics on the geometric characteristics of the front-line device and its length is carried out. As a result of the analysis of mathematical models, a list of the main geometric characteristics of the front device was determined, on which the total pressure loss, the combustion efficiency and the range of stable operation of the combustion chamber depend. Optimization parameters, optimization criterion and limits for solving the optimization problem are determined. As an implementation of the optimization method, it is proposed to use a diagram of the combustion chamber performance in the coordinates of the optimization parameters. The developed method makes it possible to ensure the optimal basic operating characteristics of the combustion chamber - total pressure loss, combustion efficiency and combustion stability limits.Дмитрий Викторович КозелNational Aerospace University «Kharkiv Aviation Institute»articleпрямоточная камера сгораниястабилизаторы пламенифронтовое устройствополнота сгорания топливапотери полного давленияMotor vehicles. Aeronautics. AstronauticsTL1-4050ENRUUKАвіаційно-космічна техніка та технологія, Vol 0, Iss 4sup2, Pp 19-28 (2021)
institution	DOAJ
collection	DOAJ
language	EN RU UK
topic	прямоточная камера сгорания стабилизаторы пламени фронтовое устройство полнота сгорания топлива потери полного давления Motor vehicles. Aeronautics. Astronautics TL1-4050
spellingShingle	прямоточная камера сгорания стабилизаторы пламени фронтовое устройство полнота сгорания топлива потери полного давления Motor vehicles. Aeronautics. Astronautics TL1-4050 Дмитрий Викторович Козел The geometric characteristics of the front and the length selection for the combustion chamber of direct flow type
description	A method has been developed for selecting the geometric characteristics of the front and the length of the direct-flow combustion chamber. Afterburner combustion chambers are of the ramjet type and are used for a short-term increase in the thrust of a gas turbine engine during takeoff, for overcoming the sound barrier by an aircraft and for flying at supersonic speed, and for making maneuvers. As part of ramjet engines, ramjet combustion chambers are used as the main combustion chambers in which the process of fuel combustion and heat supply to the working fluid is ensured. The developed method for selecting the geometric characteristics consists in optimizing the main operating characteristics of the combustion chamber. Mathematical models are proposed for describing the dependence of the total pressure loss, the combustion efficiency and the range of stable operation of the combustion chamber against the parameters of the flow at the inlet to the combustion chamber and the geometric characteristics of the front device and the length of the combustion chamber. The analysis of the dependences of the combustion chamber working characteristics on the geometric characteristics of the front-line device and its length is carried out. As a result of the analysis of mathematical models, a list of the main geometric characteristics of the front device was determined, on which the total pressure loss, the combustion efficiency and the range of stable operation of the combustion chamber depend. Optimization parameters, optimization criterion and limits for solving the optimization problem are determined. As an implementation of the optimization method, it is proposed to use a diagram of the combustion chamber performance in the coordinates of the optimization parameters. The developed method makes it possible to ensure the optimal basic operating characteristics of the combustion chamber - total pressure loss, combustion efficiency and combustion stability limits.
format	article
author	Дмитрий Викторович Козел
author_facet	Дмитрий Викторович Козел
author_sort	Дмитрий Викторович Козел
title	The geometric characteristics of the front and the length selection for the combustion chamber of direct flow type
title_short	The geometric characteristics of the front and the length selection for the combustion chamber of direct flow type
title_full	The geometric characteristics of the front and the length selection for the combustion chamber of direct flow type
title_fullStr	The geometric characteristics of the front and the length selection for the combustion chamber of direct flow type
title_full_unstemmed	The geometric characteristics of the front and the length selection for the combustion chamber of direct flow type
title_sort	geometric characteristics of the front and the length selection for the combustion chamber of direct flow type
publisher	National Aerospace University «Kharkiv Aviation Institute»
publishDate	2021
url	https://doaj.org/article/9393cd90f53b4fe18394405d972e19f0
work_keys_str_mv	AT dmitrijviktorovičkozel thegeometriccharacteristicsofthefrontandthelengthselectionforthecombustionchamberofdirectflowtype AT dmitrijviktorovičkozel geometriccharacteristicsofthefrontandthelengthselectionforthecombustionchamberofdirectflowtype
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The geometric characteristics of the front and the length selection for the combustion chamber of direct flow type

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