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Turbofan engine self-adaptive component level simulation model construction method

A turbofan engine and simulation model technology, applied in design optimization/simulation, special data processing applications, instruments, etc., can solve problems such as huge workload of model matching, achieve strong adaptability, high output tracking accuracy, and improve model accuracy Effect

Active Publication Date: 2018-10-12
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0004] The purpose of the present invention is to provide a method for constructing a turbofan engine adaptive component-level simulation model to solve the problem of using experience to manually adjust the characteristics of the engine gas path components and make the model match the huge workload.

Method used

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  • Turbofan engine self-adaptive component level simulation model construction method

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Embodiment

[0044] In this embodiment, the construction of an adaptive component-level simulation model of a turbofan engine with dual-shaft mixed exhaust is taken as an example. figure 1 is the schematic diagram of the turbofan engine adaptive component-level simulation model, and the establishment of the simulation model includes the following steps:

[0045] Step A, according to the aerodynamic thermodynamic characteristics of each component of the turbofan engine, obtain the parameters of each working section of the turbofan engine, and establish a non-linear component-level dynamic general model of the turbofan engine above the idle state; the detailed steps are as follows:

[0046] In step A1, an engine component-level model is established according to the characteristics of turbofan engine components, design point parameters and test run data. Mixing chamber and nozzle, etc., and then establish the common working equations among the components according to the principles of continu...

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Abstract

The invention discloses a turbofan engine self-adaptive component level simulation model construction method, which comprises the following steps: step A, obtaining parameters of each working sectionof a turbofan engine, establishing a nonlinear component level dynamic universal model of the turbofan engine in a state above a slow train; step B, designing a volume tracking filter and estimating an unmeasurable performance feature parameter of an air channel component of the turbofan engine in the nonlinear component level dynamic universal model obtained in the step 1, wherein the air channelcomponent comprises a fan, a gas compressor, a high pressure turbine and a low pressure turbine; step C, using the performance feature parameter estimated in the step B to automatically update the flow and efficiency characteristic diagram of the air channel component, using the adjusted air channel component characteristic parameters for calculation of component aerothermodynamic parameters, andestablishing a self-adaptive component level simulation model in a state above the slow train. The turbofan engine self-adaptive component level simulation model construction method in the inventionsignificantly improves the precision of the nonlinear component level engine individual model in the state above the slow train.

Description

technical field [0001] The invention relates to the field of aero-engine modeling and simulation, in particular to a method for constructing a turbofan engine adaptive component-level simulation model. Background technique [0002] The structure of the turbofan engine is complex and the working environment is harsh, and the requirements for its safety and reliability are very high. The research on the adaptive modeling technology of the turbofan engine has always been an important topic. The aero-engine adaptive model can reflect the differences between engines and the influence of factors such as performance degradation during service life on engine performance, which is the basis for realizing engine adaptive adjustment control and ensuring the normal operation of the engine. At the same time, the sensor fault diagnosis, isolation and fault-tolerant control of the engine control system also require an accurate engine model as a prerequisite, so establishing an accurate ada...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20
Inventor 鲁峰高天阳一黄金泉周文祥仇小杰吴斌
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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