Testing of an adaptive engine parameters observer as part of the information and measurement system in the process of high-thrust aircraft engine testing


Аuthors

Inozemtsev A. A.1, 2*, Pleshivykh A. S.1**, Sazhenkov A. N.1*, Pervadchuk V. P.2***, Lamanova N. G.2****, Vasketsov . A.2*****

1. "UEC-Aviadvigatel"JSC, 93, Komsomolsky Prospect, Perm, 614990, Russia
2. Perm National Research Polytechnic University, PNRPU, 29, Komsomolsky Prospekt, Perm, 614990, Russia

*e-mail: office@avid.ru
**e-mail: arthur.p.s.1995@mail.ru
***e-mail: pervadchuk@mail.ru
****e-mail: nglaman@mail.ru
*****e-mail: ivanvask1@yandex.ru

Abstract

The article presents the results of full-scale tests of an adaptive observer based on the Yazvinsky filter in the system of a fifth-generation turbofan engine with a high thrust of 35 tf.

To conduct the research, a mathematical model of the adaptive observer was formed with subsequent integration into the information and measuring bench equipment. The adaptive algorithm for generating information redundancy includes an algorithm for identifying the mathematical model of the turbofan engine ACS and an algorithm for an optimal observer that generates optimal estimates of the parameters of the turbofan engine ACS output vector in real time. The program code of the tested adaptive observer was created in C++ and its size was 38 KB. The frequency of polling the measured input parameters of the Yazvinsky filter and the frequency of issuing calculated estimates is 10 Hz.

The work was carried out on modern, specialized and certified equipment operating in real time. To ensure the safety of engine tests, the method was tested in the observation mode, i.e. without the ability to control the adaptive observer by the bench and engine systems. The output vector of the engine automatic control system estimated using the adaptive observer includes the following engine parameters: low-pressure compressor rotor speed nВ, high-pressure compressor rotor speed nК, air pressure behind the high-pressure compressor РК, and gas temperature behind the low-pressure turbine ТТ.

Testing the algorithmic backup method based on the Yazvinsky filter confirmed its ability to operate as part of a digital turbofan engine ACS with acceptable accuracy indicators in statics. In the studied steady-state operating modes from idle to takeoff mode, the maximum offset does not exceed |0.008| %.

Experimental testing of the algorithmic backup method based on the Yazvinsky filter was performed for the first time in the Russian aircraft engine industry.

Based on the test results, directions for further research have been formed, which include the study of an adaptive observer in dynamic operating modes of a turbojet two-circuit engine (acceleration, discharges, counter-acceleration, go-around) and in case of physical failures of the engine parameter sensors: low-pressure compressor rotor speed nВ, high-pressure compressor rotor speed nК, air pressure behind the high-pressure compressor РК, gas temperature behind the low-pressure turbine ТТ at the inlet to the calculation algorithm.

Keywords:

aircraft engine, technology demonstrator engine, electronic engine controller, algorithmic redundancy, mathematical model, fault tolerance, optimal observer, Kalman filter, Yazvinsky filter

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