Conceptual Design of a Small-Sized Heat Recovery Turboshaft Engine

Abstract

The growing requirements for efficiency and ecological friendliness are forcing the aircraft engine developers to pay increasing attention to power plants with non-traditional design and layout schemes. One of the promising solutions is the heat recovery engine, where the lightweight compact heat exchangers are playing a key role. The paper provides results of optimizing the heat recovery aviation engine parameters for a search-and-rescue UAV based on the criteria of specific fuel consumption in the patrol mode and the mass of a power plant and fuel. Heat recovery in the computed engine, taking into account power limitations in the patrol mode, ensures a decrease in specific fuel consumption by 26 % compared to the original engine. The paper presents a method in selecting the thermogasdynamic parameters, which ensures selection of an engine design meeting the specified requirements. In order to check adequacy of the heat exchanger specified parameters, relative analyses were performed. Those included selecting optimal parameters of the engine equipped with a recuperator with the power plant smallest mass, minimum specific fuel consumption and minimum dimensions of the heat exchanger heat-transfer matrix for a designed engine satisfying the overall mass and hydraulic losses limitations

The work performed with the support of the Ministry of Science and Higher Education of Russian Federation within the framework of the State Assignment "Development of critical technologies for creation of power plants for small and regional aviation, as well as unmanned aviation systems" (no. FEUE-2023-0007)

Please cite this article in English as:

Mikhailov A.E., Mikhailova A.B., Eremenko V.V., et al. Conceptual design of a small-sized heat recovery turboshaft engine. Herald of the Bauman Moscow State Technical University, Series Mechanical Engineering, 2024, no. 4 (151), pp. 47--67 (in Russ.). EDN: ZCPYGU

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