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Turbo-shaft engine self-adaptive component-level simulation model construction method

A turboshaft engine and simulation model technology, applied in design optimization/simulation, special data processing applications, instruments, etc., can solve the problems of model mismatch, individual differences of turboshaft engines, etc., to reduce model errors, high model accuracy, Output with high tracking accuracy

Active Publication Date: 2018-11-16
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0004] The purpose of the present invention is to provide a turboshaft engine adaptive component-level simulation model construction method to solve the model mismatch problem caused by individual differences and performance degradation of turboshaft engines

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  • Turbo-shaft engine self-adaptive component-level simulation model construction method

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Embodiment

[0045] In this embodiment, the construction of an adaptive component-level simulation model of a certain type of turboshaft engine is taken as an example. figure 2 is the schematic diagram of the turboshaft engine adaptive component-level simulation model, and the establishment of the simulation model includes the following steps:

[0046] Step A, according to the aerodynamic thermodynamic characteristics of each component of the turboshaft engine, obtain the parameters of each working section of the turbofan engine, and establish a nonlinear component-level dynamic general model of the state of the turboshaft engine above idle; the detailed steps are as follows:

[0047] Step A1, the components and working sections of a certain type of turboshaft engine are as follows figure 1 As shown, the engine component-level model is established according to the characteristics of the turboshaft engine components, design point parameters and test data, including the intake port, compres...

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Abstract

The invention discloses a turbo-shaft engine self-adaptive component-level simulation model construction method. The method comprises the following steps: step A, acquiring parameters of various worksections of a turbo-fan engine according to various component aerothermodynamics features of the turbo-shaft engine, and establishing a nonlinear component-level dynamic universal model about the turbo-shaft engine over-idling state; step B, designing a volume tracking filter, estimating an unmeasured performance feature parameter of a turbo-shaft engine gas circuit component in the obtained non-linear component-level dynamic general model, wherein the gas circuit component comprises a gas compressor, a gas turbine, and a power turbine; and step C, automatically correcting the flow and efficiency feature graph of each gas circuit component by using the estimated performance feature parameter, and applying the adjusted gas circuit component feature parameter to computing the component aerothermodynamics parameter to obtain modified model output data, thereby establishing the self-adaptive component-level simulation model of over-idling state. The model mismatch problem caused by turbo-shaft engine individual difference and performance degradation is solved through the method disclosed by the invention.

Description

technical field [0001] The invention relates to the field of modeling and simulation of aeroengines, in particular to a method for constructing an adaptive component-level simulation model of a turboshaft engine. Background technique [0002] The turboshaft engine works in the harsh environment of high temperature, high speed, strong vibration and high stress, and the working state of the engine changes frequently, which requires high safety and reliability. The research on engine adaptive model modeling technology has always been an important topic. The engine adaptive model can reflect the differences between engines and the influence of factors such as performance degradation during service life on engine performance. basis for proper functioning. At the same time, the implementation of engine control system sensor fault diagnosis, isolation and fault-tolerant control technology also requires an accurate engine model as a prerequisite, so establishing an accurate adaptiv...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20
Inventor 鲁峰高天阳一黄金泉周文祥吴斌仇小杰
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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