CIAM

U.S. programs for development of fundamentally new technologies for sixth generation military aircraft engines (review)

The article explores content and implementation of research and experimental work in the framework of US government programs aimed at developing fundamentally new technologies for engines of the sixth generation of military aircraft. The priority field is the development of a unified adaptive three-stream engine, creation of which in mid-2020’s will dramatically improve combat capabilities of F-35 aircraft and provide a potential for creating aircraft with fundamentally new characteristics. Much attention is also paid to the field of hypersonic aircraft with combined power plants, creation of which is expected by 2040.

Keywords: adaptive engine, three-stream engine, unification, combined power plant, hypersonic, advanced technologies, military aircraft.

Solonin V.I., Palkin V.A.

On determining shapes of fuel manifolds

This article presents a technique for determining shape of a fuel manifold, which provides required flow distribution of the operating medium. The technique is based on application of a calculation algorithm according to the “predictor” (1D model of hydrodynamics) – “corrector” (3D model of hydrodynamics and heat transfer) scheme, which significantly reduces amount of computational costs. Results of a parametric design study of a section of typical manifold are presented. Estimates of accuracy of results of 1D modeling in comparison with results of 3D modeling are given.

Keywords: fuel manifold, mathematical modeling, Navier – Stokes equations, turbulence.

Baykov A.V., Nechiporuk S.Y., Filatov D.S., Surovezhko A.S., Martynenko S.I.

Demonstration of multidisciplinary optimization technology on the example of an experimental compressor blade

Based on the previously developed technology of multicriteria multidisciplinary optimization of compressor blades, the NASA Rotor 37 stage was optimized according to the criteria of aerodynamic efficiency and blade mass minimization. As a result, a version of the stage was obtained, which provides an increase in efficiency by 2,1% and a decrease in the centrifugal load from the blade to the disk by ~ 9%, while meeting all aerodynamic and strength requirements. Influence of the number of variable parameters on optimization results is investigated.

Keywords: multidisciplinary optimization, parameterization scheme, blade, experimental compressor, aerodynamics, strength.

Buyukli T.V., Popov G.M., Goryachkin E.S.

Development of calculation and design methods for aviation heat exchangers

Results of the parametric computational study of three types of aviation heat exchangers are presented: tubular heat exchanger located in the bypass duct of the turbofan engine, plate heat exchanger with corrugated, zigzag and micro-hill exchange surfaces and advanced heat exchanger with bionic channels. Flow features in such heat exchangers are investigated and their thermohydraulic characteristics are determined. Calculations were performed mainly in a three-dimensional formulation.

Keywords: heat exchanger, tubular heat exchanger, plate heat exchanger, micro-hill surfaces, bionic structure, mathematical modeling.

Svetlakov A.L., Verbanov I.S., Maslova D.V., Gulimovskyi I.A., Shlyakotin V.E.

Computational and analytical study to confirm effectiveness of an aircraft engine’s protection from effects of rain and hail

The most critical combination of climatic conditions and engine operating modes, in which unacceptable changes in an engine’s operation, specified in regulatory documents, can occur, is revealed based on computational and analytical study of influence of rain and hail on an aviation gas turbine engine. Calculations show that when an engine is running in idle mode, maximum penetration of hail particles into main duct of the engine is possible, which can lead to the most adverse effects on compressor and combustion chamber. Recommendations have been developed for performing certification tests of an engine under conditions of rain and heavy hail. It is shown that when performing tests in rain conditions, it is possible to simulate spectral composition of droplets with a size much smaller than specified in the regulatory documents. The possibility of equivalent replacement of tests in rain conditions with tests in hail conditions is shown, which can significantly reduce number and cost of certification tests.

Keywords: аircraft engine, climatic certification tests, rain, hail, critical operation, test rig.

Goryachev A.V., Goryachev P.A., Zhulin V.G., Grebenkov S.A.

Development of various types of small-scale gas turbine engines based on a unified core engine

Feasibility of the unification concept in creation of a family of advanced small-scale gas turbine engines of various types and purposes is confirmed based on results of design studies. Following constructive and parametric designs have been developed on the basis of the selected unified core engine: a turbojet engine with a thrust of 100 kgf, a bypass turbojet engine with a thrust of 250 kgf, a turboshaft engine with a power of 300 hp (including a layout with a heat exchanger of a heat recovery system), and auxiliary power unit with electric power of 60 kVA.

Keywords: small-scale gas turbine engine, base core engine, engine family, gearbox, heat recovery system.

Osipov I.V., Lomazov V.S.