The effect of heat recovery on the optimal values of helicopter turboshaft engine parameters

Abstract


Recent studies related to fuel economy in air transport conducted in our country and abroad show that the use of recuperative heat exchangers in aviation gas turbine engines can significantly, by up to 20...30%, reduce fuel consumption. Until recently, the use of cycles with heat recovery in aircraft gas turbine engines was restrained by a significant increase in the mass of the power plant due to the installation of a heat exchanger. Currently, there is a technological opportunity to create compact, light, high-efficiency heat exchangers for use on aircraft without compromising their performance. An important target in the design of engines with heat recovery is to select the parameters of the working process that provide maximum efficiency of the aircraft system. The article focused on setting of the optimization problem and the choice of rational parameters of the thermodynamic cycle parameters of a gas turbine engine with a recuperative heat exchanger. On the basis of the developed method of multi-criteria optimization the optimization of thermodynamic cycle parameters of a helicopter gas turbine engine with a ANSAT recuperative heat exchanger was carried out by means of numerical simulations according to such criteria as the total weight of the engine and fuel required for the flight, the specific fuel consumption of the aircraft for a ton- kilometer of the payload. The results of the optimization are presented in the article. The calculation of engine efficiency indicators was carried out on the basis of modeling the flight cycle of the helicopter, taking into account its aerodynamic characteristics. The developed mathematical model for calculating the mass of a compact heat exchanger, designed to solve optimization problems at the stage of conceptual design of the engine and simulation of the transport helicopter flight cycle is presented. The developed methods and models are implemented in the ASTRA program. It is shown that optimal parameters of the working process of a gas turbine engine with a free turbine and a recuperative heat exchanger depend significantly on the heat exchanger effectiveness. The possibility of increasing the efficiency of the engine due to heat regeneration is also shown.


About the authors

H. H. Omar

Samara National Research University

Author for correspondence.
Email: dr.hewa.omar@gmail.com
ORCID iD: 0000-0003-4574-0339

Russian Federation

Postgraduate Student of the Department of  Aircraft Engine Theory

V. S. Kuz'michev

Samara National Research University

Email: kuzm@ssau.ru
ORCID iD: 0000-0003-1696-2899

Russian Federation

Doctor of Science (Engineering), Professor, Professor of the Department of Aircraft Engine Theory

A. O. Zagrebelnyi

Samara National Research University

Email: zao_sam156@mail.ru

Russian Federation

Postgraduate Student of the Department of  Aircraft Engine Theory

V. A. Grigoriev

Samara National Research University

Email: grigva47@gmail.com

Russian Federation

Doctor of Science (Engineering), Professor, Professor of the Department of Aircraft Engine Theory

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