Société de langues et littératures médiévales d'oc et d'oïl (SLLMOO)

The work contains the results of a study of the basic design concepts of advanced engines for supersonic civil aircraft, carried out in order to make a forecast for the development of aviation technology, taking into account the experience of foreign designers. Engine designs are presented that are considered to be the most rational ones from the point of view of achieving high technical and economic parameters in the range of cruise Mach numbers from 1.2 to 5. Advantages and disadvantages of various engine designs, as well as issues of engine regulation at different flight modes, are discussed. The parameters of some engines being developed and studied at present for supersonic civil aircraft are presented. The analysis of the designs shows that an increase in the cruise Mach number leads to a complication of engine designs in the direction of an increase in the number of controlled elements, the number of working fluid flow paths, a complication of the architecture of turbomachines, as well as in the direction of using combined schemes and alternative fuels. The aspiration to meet new reinforced ecological requirements through the use of new, complex engine designs that differ significantly from traditional gas turbine engines will inevitably entail additional technical risks due to the insufficient level of technological readiness of most of the new controlled units.

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The article presents the results of weight and size optimization of a high-pressure turbine working disk for an augmented turbofan. The issues of modeling the operation of the engines first stage with a cover plate providing the delivery of cooling air to the blades are considered. Strength calculation of the stresses arising from the action of centrifugal forces under high-temperature conditions was carried out. A three-dimensional model of the disc was obtained. The finite element method was used. The pattern of temperature distribution in the disk body was obtained on the basis of heat calculation. Based on the strength calculation, the stresses and strains of the turbine disk were determined. Maximum stresses in the disc are located at the junction of the disc frontal area and the cooling air feed holes. Plastic deformation is observed in the area of the cavities for cooling air feed. It is shown that the stepped part of the disc should be made of a material with lower heat resistance and a higher value of permissible limit stress. Based on the study, a bimetallic disk design made by powder metallurgy was proposed.