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The problem of aircraft engine emissions and their impact on atmospheric processes and climate

The influencing factors of the impact of aircraft engine exhaust gases on atmospheric processes and climate, as well as measures to reduce emissions are presented in the article. A brief analysis of the work performed as part of foreign programs aimed at creating environmentally friendly and efficient aircraft with new types and designs of propulsion systems, low fuel consumption, as well as the use of alternative fuels is included. CIAM’s studies aimed at improving the environmental characteristics of aircraft engines and investigating their impact on the climate are highlighted. Recommendations on how to organize research and development to improve the competitiveness of domestic engines are provided.

Keywords: emissions, climatic impact, atmospheric impact, ICAO standards, development programs, key technologies, fuel efficiency, hybrid propulsion system, alternative fuel

Lanshin A.I., Solonin V.I.

Preliminary studies on the creation of the engine technology demonstrator of the new generation supersonic civil aircraft propulsion system

Preliminary requirements have been formulated for the engine technology demonstrator of the new generation supersonic civil aircraft propulsion system. A preliminary list of technologies that can be demonstrated on the engine during its development and further use as a tool to bring critical technologies to high TRL is given. An approach to the formation of the design concept of the engine technology demonstrator is described. The results of computational research on the determination of rational parameters are presented. The analysis of the achievable performance and economical characteristics of the engine technology demonstrator in its key operating modes is carried out.

 Keywords: supersonic civil aircraft, propulsion system, engine technology demonstrator, turbofan, experimental engine core

Alendar’ A.D., Evstigneev A.A., Grunin A.N.

Simplified model for evaluation of the elastic properties of gas-dynamic support elements

Simplified model for evaluation of the elastic properties of gas-dynamic bearing elements is represented with their contact interaction taken into account. Suggested model methodology is based on the equations of the bar bending theory, with the assumption of the plane curved bar axis form described in the local coordinate system. Single GFB corrugated damper stress-strain condition is calculated using suggested bar model considering its concentrated force loading and verified versus finite element simulation results obtained with the plain strain finite element model. Different methodologies and accuracy of the parameters describing contact interaction are evaluated for GFB FE model. It is shown that three-foil gas bearing FE simulation results tend to approach asymptotically to the ones obtained using simplified model while increasing the accuracy of the FE model contact interaction parameters. Simplified model advantages in comparison with the previously developed FE model, including a decrease in computational time, are shown.

Keywords: gas foil bearing, radial bearing, elastic gas-dynamic contact, mechanics of bars.

Temis M.Yu., Meshcheryakov A.B.

Unification of electroplating on sealing elements of a liquid-propellant rocket engine

The replacement of copper-fluoroplastic coatings with copper-silver coatings was carried out for the unification of electroplating coatings on sealing elements of detachable connections of components and assemblies in a liquid-propellant rocket engine. Comparative analyses of coatings were carried out: according to the composition of electrolytes, environmental hazards, complexity of application, eliminability of defects, etc., which showed the need for such a replacement. A program of experimental verification of the copper-silver coating’s effectiveness has been developed.

Keywords: liquid-propellant rocket engine, sealing element, tightness, turbopump unit, electroplating, oxidizer pump, fuel pump, detachable connections

Zakharov V.V.

Comprehensive analysis of compressor blades’ dynamic behavior at the design stage

The article is devoted to the problem of ensuring the dynamic strength of compressor blades during the creation of a jet gas turbine engine. In general, the dynamic strength of the compressor blades is studied by expensive and long-term experimental methods. We state the problem of more accurate prediction of the dynamic behavior of compressor blades at the design stage using numerical simulation of dynamic processes that cause blade oscillations and lead to their fatigue failure. The goal is the reduction of time-consuming and expensive experimental optimization of compressor blades. We develop the methods for predicting forced resonant oscillations of compressor blades as well as the conditions that lead to blade flutter. The created methods and numerical algorithms for solving the above-mentioned problems are described, and the calculation results are compared with the data obtained in experiments.

Keywords: resonance, flutter, damping, blade, compressor, gas turbine engine

Makarov P.V., Kolotnikov M.E., Vedeneev V.V., Abdukhakimov F.A.

On the instability of heat-resistant alloys

The article discusses issues of stability of heat-resistant alloys and steels used in gas-turbine development in terms of predicting their mechanical properties and service life. Factors affecting the stability of material properties are examined: operating time (number of cycles), temperature, chemical and phase composition of materials, hardening, and high-temperature corrosion.

Keywords: heat-resistant alloy, instability, microstructure, strength, plasticity, prediction, service life

Getsov L.B.

The probabilistic approach to predicting the durability of turbine parts in engine cores of the NK-family ground-based GTUs for GCUs

A method is proposed that makes it possible to predict the durability of critical turbine parts by the parameter of creep rupture strength. The method is based on the analysis of the stress-strain state of the most loaded parts – disks and rotor blades of the first stage of a high-pressure turbine – of ground gas turbine units (GTUs) NK-16ST, NK-16-18ST and NK-16-18STD series 5 for gas compressor units (GCUs). It is shown that the long-term operation of engines (both aviation engines and GTUs for GCUs) and the peculiarities of their operation lead to a change in the stress-strain state of parts. The paper uses numerous statistically processed data on the mechanical characteristics (and their change) and durability of the disks’ material (EI698-VD alloy) and rotor blades’ material (ZhS6U-VI alloy) of turbines at different levels of their operational life. The prediction of the durability of parts is implemented by considering changes in the statistical margins of safety and durability during long-term operation according to I.A. Birger’s probabilistic criterion of destruction.

Keywords: turbine, disk, rotor blade, EI698-VD, ZhS6U-VI, durability, probabilistic criterion of destruction, Birger’s criterion

Velikanova N.P., Velikanov P.G., Protasova N.A., Aliyev R.N.O.

Heat exchange boundary conditions for calculating the temperature fields of parts of a piston-cylinder unit in ICEs

The article presents main points of the methodology for mathematical modeling of mutually consistent interdependent thermal boundary conditions for calculating temperature fields, deformation fields and stresses of piston-cylinder units’parts (cylinder head – valves – piston rings – cylinder liner). The problem's complexity is demonstrated by the interdependence of temperature fields and the diverse types and conditions of heat exchange on the surfaces of the parts that influence the thermal state. The temperature fields should be coordinated and modeled simultaneously as part of the overall process of simulating the thermal loading of the piston-cylinder unit. A description of the software package for calculating the thermal state of heat-stressed parts of reciprocating engines, which implements the proposed method, as well as the results of calculating 2D and 3D temperature fields are given.

Keywords: piston engine, internal combustion engine, thermal state, heat transfer, temperature field, boundary conditions, modeling, calculations

Russinkovskiy S.Yu., Chaynov N.D.