Aerospace Instrument-Making Annotation << Back Evaluation of the Influence of blades after Repair on the Gas Temperature Behind the Combustion Chamber using a Neural Network Pushkarev D.O., Kiselev D.Yu., Kiselev Yu.V. One of the main problems associated with the operation of gas turbine engines is the damage of compressor blades, which occurs due to the ingress of foreign objects. Due to the fact that blades are a very expensive element in production, there is a need for their repair. One of the disadvantages of using repair compressor blades is the increased gas temperature behind the combustion chamber, this is due to the impossibility of ideal restoration of the blade geometry. A model was created based on machine learning methods, which allows assessing the effect of repaired blades on the gas temperature behind the combustion chamber. Based on this model, it is possible to assemble a compressor using repair blades. The results obtained using the developed model were verifi ed by data collected during acceptance tests of the engine after repair. Keywords: machine learning; neural networks; blades; gas turbine engine; blade repair; thermogasdynamic parameters. DOI: 10.25791/aviakosmos.6.2026.1564 Pp. 30-41.