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The method of advanced bypass turbojet engine core research tests with simulation of target inlet thermogasdynamic parameters at the engine OEM site is considered. It is stated that research testing is traditionally associated with the use of multifunctional test facilities capable of simulat-ing operating conditions as close as possible to operational ones for a wide range of test objects of different thrust (power) and application. Such test facilities require significant investment and operating costs, which in general determines their limited number in the world. It is shown that the steady growth of the share of research tests at the initial design stages requires organization of tests with minimal financial and material costs directly at the engine OEM site, where testing the advanced bypass turbojet engine core plays a special part. Determination of the method for simulating thermogasdynamic parameters is associated with solution of rather contradictory problems, where, on the one hand, it is required to ensure reliable reproduction of the actual operating conditions of the core for all configurations of the bypass turbojet engine under development, and on the other hand, to ensure lower manpower and cost of testing. One of the effective solutions is the use of specialized test facilities, a distinctive feature of which is determination of the simplest and most economical means of obtaining the working fluid with the required thermogasdynamic parameters for a pre-determined range of test objects of different thrust (power) and application. The technical implementation of the dedicated test facility for testing the advanced bypass turbojet engine core at UEC-Aviadvigatel JSC (Perm) is considered.

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Continuous improvement in the operational characteristics of gas turbine equipment and a significant reduction in the time of its creation have led to the development and application of new technologies for conducting research tests of a gas generator—the basic section of a bypass turbojet engine. Carrying out such tests requires the reproduction of the thermo gas dynamic parameters of the working fluid at the gas generator inlet to ensure maximum similarity to the processes occurring in the engine being designed. Obtaining a working fluid with the required thermo gas dynamic parameters such as temperature, pressure, and air flow rate is carried out on the basis of a test complex. The test complex, as a control object, is a non-linear, non-stationary, multi-variable system, where each controlled variable substantially depends on other control actions. The article presents the main aspects of the behavior of the object under consideration, which are the basis for the development of an automated test system and, in particular, the principles of forming control algorithms based on the theory of fuzzy logic. The graphs of the state and control of the main elements of the test complex are presented. Special attention is given to the analysis of the proposed control algorithms.

The article describes the development of mathematical models and user environment in the APD language which are based on the finite element system solver and allow for the SLM physical process numeric modelling with the required accuracy. The main task is to evaluate the final shrinkage and residual strength of the blanks of gas turbine parts for optimizing the technological process of production. The activities on introducing pre-distortions into the part geometry were performed to compensate for thermal deformation during the growth process; the part with pre-distortion was produced and controlled.