Aero-engine compressor disc temperature prediction method based on multi-layer perceptron

The invention discloses an aero-engine compressor disc temperature prediction method based on a multilayer perceptron. The aero-engine compressor disc temperature prediction method comprises the steps that engine compressor disc performance design data is obtained, multi-working-condition calculation is conducted on a finite element model, sample space data is formed, and invalid value elimination or normalization processing is conducted on the sample space data; dividing the sample space data into a training set and a test set, taking data of a first proportion in the sample space data as the training set, and taking data of a second proportion as the test set; the value of the first proportion is greater than that of the second proportion; a model is established according to data of the training set, and parameters of the established model are optimized through grid search; and inputting data of a test set into the model to obtain a gas compressor disc temperature prediction result corresponding to the test