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Distributed hybrid electric propulsion system optimization method and device

A system optimization and propulsion system technology, applied to ground installations, power plant types, transportation and packaging, etc., can solve problems affecting work safety, engine surge, and optimization methods that are not considered

Pending Publication Date: 2022-02-15
AECC SHENYANG ENGINE RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] 1. The impact on the aircraft was not considered in the design of the propulsion system, and the working status of the design was inaccurate;
[0006] 2. If the thrust compensation of the propulsion system occurs during use, it will affect the operating point of the engine, prone to engine surge, and affect work safety;
[0007] 3. The optimization method is not considered in the design, and the efficiency is low

Method used

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  • Distributed hybrid electric propulsion system optimization method and device
  • Distributed hybrid electric propulsion system optimization method and device
  • Distributed hybrid electric propulsion system optimization method and device

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Embodiment Construction

[0044] In order to make the objectives, technical solutions and advantages of the implementation of the application clearer, the technical solutions in the implementation modes of the application will be described in more detail below with reference to the drawings in the implementation modes of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the present application. The embodiments described below by referring to the figures are exemplary and are intended to explain the present application, and should not be construed as limiting the present application. Based on the implementation manners in this application, all other implementation manners obtained by persons of ordinary skill in the art without creative efforts fall within the scope of protection of this application. Embodiments of the pr...

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Abstract

The invention belongs to the technical field of engine design, and particularly relates to a distributed hybrid electric propulsion system optimization method and device. The method comprises the following steps: giving an initial aircraft layout; determining a thrust demand of the propulsion system; giving an initial ratio of the main thrust to the auxiliary thrust; determining the main thrust of a turbofan engine and the auxiliary thrust of each electric drive fan; determining the power of the electrically driven fan; according to the power of the electric drive fan, determining the extraction power obtained from the turbofan engine; determining the oil consumption rate of the turbofan engine; determining the oil consumption rate of the propulsion system; and judging the reduction degree of the oil consumption rate of the propulsion system compared with the oil consumption rate of the original turbofan engine, and if the reduction degree of the oil consumption rate of the propulsion system compared with the oil consumption rate of the original turbofan engine does not meet a design value, carrying out aircraft layout and thrust distribution again. When the propulsion system is designed, the influence of the propelling system on the aircraft is considered, the overall performance design is more accurate, thrust compensation is not needed, and the working risk of the engine is reduced.

Description

technical field [0001] The application belongs to the technical field of engine design, and in particular relates to a distributed hybrid electric propulsion system optimization method and device. Background technique [0002] The distributed hybrid electric propulsion system consists of an engine and an electric propulsion system, and the electric propulsion system consists of a generator, an electrically driven fan, and an air intake. Due to the small size of a single electric drive fan, the entire propulsion system requires a large number of electric propulsion fans, and the latest loaded aircraft is gradually inclined to the wing-body fusion design, which makes the fan buried in the fuselage or wing, and the fan The absorption of the boundary layer affects the performance of the electric propulsion fan system and the lift-drag characteristics of the aircraft, causing the aircraft to require more thrust, which in turn affects the working state of the turbofan engine. [...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/02B64F5/00
CPCB64D27/02B64F5/00B64D27/026
Inventor 何佳倩苏桂英芮长胜
Owner AECC SHENYANG ENGINE RES INST
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