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Abstract <p>The paper considers the method of selecting the scheme and main parameters of the engine, the number and distribution of parameters by turbocharger stages when designing a gas turbine engine. The paper proposes a sequence and a method of selecting and optimizing the main parameters of the fan, low-pressure and high-pressure compressors when designing gas turbine engines of different types, namely, a bypass turbojet engine (with separate nozzles, with flow mixing and an afterburner), a turbojet and a turboprop engine. The proposed method was tested using the example of a bypass turbojet engine of the PD-14 type as a part of the MS-21 aircraft.</p>

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Decision Support at the Initial Stage of Turbofan Engine Design

  • 期刊论文

  • 发表日期：

    2025年6月1日

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  • I. A. Krivosheev,
  • K. E. Rozhkov,
  • N. B. Simonov,
  • O. N. Ivanova

摘要

Abstract

The paper considers the method of selecting the scheme and main parameters of the engine, the number and distribution of parameters by turbocharger stages when designing a gas turbine engine. The paper proposes a sequence and a method of selecting and optimizing the main parameters of the fan, low-pressure and high-pressure compressors when designing gas turbine engines of different types, namely, a bypass turbojet engine (with separate nozzles, with flow mixing and an afterburner), a turbojet and a turboprop engine. The proposed method was tested using the example of a bypass turbojet engine of the PD-14 type as a part of the MS-21 aircraft.