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)

70 years of experience and accomplishments in testing aircraft engines in high-altitude test cells of CIAM's experimental base

The article examines some scientific and methodological results obtained by specialists at CIAM's experimental base (located in Lytkarino) during research, engineering and certification tests of second- to fifth-generation aircraft engines and experimental engine cores in high-altitude test cells.

Keywords: gas turbine engine, thermobarochamber, high-altitude test cell, fan, turbine

Klinskiy B.M.

Proposals for conducting certification tests to verify the safety of a helicopter’s gas turbine engine operation in the event of dust and sand ingestion

This article examines the typical operating conditions of helicopter engines in civil aviation, which are exposed to sand and dust ingested into the flow path. Based on this analysis, a suitable approach to the development of engine testing specifications is considered, and a proposal for incorporating them into the Airworthiness Standards (Part 33) is presented. Proposals have been developed for the content of certification tests for helicopter engines with dust injection into the flow path, consisting of two parts: verification of the engine's resistance to abrasive erosion and verification of the engine's resistance to the formation of glassy dust deposits and the ingress of dust into engine systems.

Keywords: dust, sand, helicopter gas turbine engine, certification tests, airworthiness standards

Rysin L.S., Mokrous M.F., Serebryakova I.V.

The formation of a permanent joint between silicon carbide ceramic and a heat-resistant alloy using spark plasma sintering

A research has been carried out on a method for creating a permanent joint between silicon carbide ceramics (SiC) and a high-temperature alloy (grade ZhS6U-VI) utilizing spark plasma sintering. It has been demonstrated that the use of a Ti-Ag powder mixture in a 30 : 70 weight ratio, in combination with a dense layer of the mixture, as well as a damper layer based on molybdenum (Ti-Ag/Mo system), results in a durable and defect-free permanent joint between SiC and the alloy, when subjected to plasma sintering under spark conditions at 1000°С and a mechanical loading force of 4 kN. It has been established that the phase and elemental composition, as well as the structure of ceramics and alloy, undergoing spark plasma heating, do not undergo changes during the formation of the composite. Тhe defect-free structural integrity has been achieved by balancing the differences in the temperature expansion coefficients at the ceramic/alloy interface through the use of a Mo damping layer and a specific thickness of the Ti-Ag bond layer.

Keywords: high-temperature ceramics, metal-ceramic composite, functionally gradient material, sintering additive, damping layer, spark plasma sintering

Papynov E.K., Chuklinov S.V., Shichalin O.O., Sergienko V.I., Marchukov E.Yu., Mukhin A.N., Belov A.A.

An estimation of the efficiency of the manufacturing methods for combustor liners in small-sized gas turbine engines

Typical designs and manufacturing methods of combustor liners in small-sized gas turbine engines are examined. A comparison of the traditional manufacturing method with a novel approach developed and patented by the CIAM is performed. The manufacturing of the combustor liner using the patented process offers several benefits, including reduced labor requirements and improved mechanical properties of individual components.

Keywords: small-sized gas turbine engine, combustor liner, metal spinning, laser cutting

Besshapov P.P., Remchukov S.S., Lebedinskiy R.N., Osipov I.V.

A comparative analysis of low-emission combustion layouts for aircraft engine combustors

The paper presents the comparison and prediction of harmful substances emission resulting from using various low-emission combustion strategies for implementation in aircraft engine combustors. The analysis of existing engine designs according to their environmental characteristics presented in the International Civil Aviation Organization’s (ICAO) database was conducted, and an estimate of the emissions was made for the two main concepts applied in modern combustors. Then, CFD calculations for two currently operating low-emission combustion layouts and one perspective layout in model combustor sectors were performed. A comparison of harmful substances emissions for certified engines combustors and the values obtained in CFD calculations made it possible to estimate the perspectives of considered combustors types and conclude that the lean combustion layouts including MLDI demonstrate more efficient operation comparing with rich-lean combustion.

Keywords: combustor, combustion layout, harmful substances emission, CFD

Tarasenko A.N., Vasiliev A.Yu., Siluyanova M.V.

Aerodynamic features of the separated-flow compressor’s performance maps

The classic way of describing the compressor behavior during its simulation inside mathematical model is the compressor map, which represents a relation of its non-dimensional thermodynamic parameters. The classic map does not provide enough information for performance simulation of variable cycle engine. This project was aimed at developing more accurate approach to modeling a compressor with separate flow outlet. Such compressor is used in the advanced layout of a three-stream variable cycle engine. The main idea is to determine the dependence of the main parameters of the compressor (the total pressure ratio, efficiency and corrected mass flow, averaged over the first and second stream) on the corrected rotational speed, position of variable guide vanes and two arbitrary parameters that determine the throttling for each stream. The developed technique of constructing such multi-parameter maps is based on the use of a computational CFD-3D model of the compressor flow.

Keywords: compressor, performance map, engine mathematical model, three-stream engine, separated flow

Kuzmin M.V., Egorov I.N., Kretinin G.V., Fedechkin K.S.

Mathematical modeling of gas turbine engine operation during autorotation mode and startup from this mode

The research is devoted to the issues of mathematical modeling of the autorotation mode of a gas turbine engine. The study of this mode before the creation of the engine is currently difficult due to the lack of reliable characteristics of its components, a mathematical description of the processes occurring in the engine, and therefore, necessary mathematical models of an engineering level. The analysis of the published results of the study of the gas turbine engine autorotation mode is performed, and methods for approximate calculation of the dynamic process of reaching this mode and its steady-state parameters are proposed using data obtained during engine testing for validation. The methods for modeling a compressor in autorotation mode are compared and their influence on the calculation results is estimated.

Keywords: gas-turbine engine, mathematical modeling, engine control system, autorotation mode, compressor operating mode, compressor mode, turbine mode

Gurevich O.S., Zuev S.A.