Method for evaluating thermodynamic cycle parameters of turboshaft engine based on cost and task requirements

By optimizing the thermodynamic cycle parameters of the turboshaft engine and combining the costs of various components with flight mission requirements, a relationship model between thermodynamic cycle parameters and component costs was established. This solved the problem that costs and mission requirements were not comprehensively considered in existing technologies, and achieved engine cost reduction and improved flight platform economy.

CN120633268AActive Publication Date: 2025-09-12AECC HUNAN AVIATION POWERPLANT RES INST
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Patent Information

Application Number
CN202511154244.X
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-08-18
Publication Date
2025-09-12
Estimated Expiration
2045-08-18

AI Technical Summary

Technical Problem

The existing turboshaft engine thermodynamic cycle parameter design method fails to effectively and comprehensively consider the cost and mission requirements, resulting in high engine costs and affecting the economy of the flight platform.

Method used

By establishing the cost ratio of each engine component, combining the flight platform mission conditions, optimizing the combustion chamber outlet temperature and pressure ratio, and establishing a relationship model between thermodynamic cycle parameters and component costs, we analyze its impact on manufacturing and periodic overhaul costs, and fuel costs, and evaluate the applicability of different parameter combinations.

Benefits of technology

This has achieved the goal of reducing engine costs while improving the range and mission capability of the flight platform and ensuring that the minimum residual weight coefficient is within an acceptable range.

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Abstract

The invention discloses a turboshaft engine thermodynamic cycle parameter evaluation method based on cost and task requirements, and the method achieves the evaluation of the thermodynamic cycle parameters of a turboshaft engine on the premise of comprehensively considering the coupling influence of cycle parameters, all parts and air system parameters. According to the method, the relation between the thermodynamic cycle parameters and all parts and the whole machine cost is established, and the distribution condition of the engine cost and the engine and fuel oil weight coefficient about the cycle parameters is obtained by combining the balance between the aircraft task and the weight, so that a reliable and scientific basis is provided for thermodynamic cycle parameter evaluation and further optimization; the method can be used for evaluating the applicability of different thermodynamic cycle parameter combinations to the flight platform, so that the cost of an engine is more advantageous, the minimum residual weight coefficient of the flight platform is still within an acceptable range, and the voyage of the flight platform is further improved.
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