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)

The choice of rational parameters of distributed power-plant for long-range aircraft taking into account boundary layer influence on the fans’ inlet

The distributed power-plant concept is considered under various conditions of its integration with long-range aircrafts taking into account the influence of boundary layer on a remote fan modules inlets. The influence on thrust of the distributed power-plant is considered separately and influence of ingress boundary layer include two compo­nents: falling of a general level of an inlet total pressure and its own non uniformity. The technique of rated researches and distributed power-plant rational parameter sets are presented for various level of an inlet total pressure losses. The preliminary analysis of influence of total pressure losses and non uniformity of pressure upon profitability and weight-and-size of the formed power-plant is made.

Keywords: turbojet bypass engine, long-range airplane, distributed power-plant, fan module, designing.

Ezrokhi Yu.A., Kalenskii S.M., Morzeeva T.A., Khoreva E.A.

    

Multidisciplinary design of axial-centrifugal compressor

Aerodynamic and structural design of a family of axial-centrifugal compressors with total pressure ratio p* = 14…25 is discussed. Such compressors are actual for modern small turbo-shaft engines. Examined compressors have 3–5 axial stages and one rear centrifugal stage.

Keywords: axial-centrifugal compressor, total pressure ratio, compressor efficiency, structural analysis.

Startsev A.N., Steshakov Eu.G., Yakushev D.A.  

  

Numerical and experimental analysis of rotor and stator clocking effect by example of model high loaded two stage compressor 

In frame of this work the two stages compressor (HPC-2 with the designed pressure ratio 3,7) of unique design was developed for investigation of rotor and stator clocking effect. The results of first experimental study of high loaded two stage compressor HPC-2 at different relative circumferential positions of rotor and stator rows are represented. The results illustrate the fact that, starting from rotational speed n` = 70% strong clocking effect of rotors and stators are clearly seen.

Keywords: rotor clocking effect, stator clocking effect, high loaded two stage compressor, bladed rows unsteady interaction.

Mileshin V.I., Markov S.A., Kozhemyako P.G., Savin N.M.


Using of reactive element for aviation engine noise reduction

Developed liner combines the traditional honeycomb liner and the reactive element in the form of a lattice of plates. Experiments have shown that the combined liner reduces the fan noise by 2…3 dB more effective than the two-layer honeycomb liners of the same length. The effect of the casing treatments on the fan noise of modern aircraft engine was investigated.

Keywords: reactive element, slot casing treatment, honeycomb liner, turbofan.

Khaletskii Yu.D., Pochkin Y.S.

    

Experimental and computational study of the model of a ring flame tube with a swirling flow

The results of a combined calculation and experimental stude of the mixing characteristics in the model of a flame tube of a prospective combustion chamber are presented for various flow Mach number from 0,05 to 0,2 and a swirl angle from 0 to 60°. Numerical simulations have been carried out by using in-house vortex-resolving HIHAR code on basis of the RANS/ILES approach.

Keywords: combustion chamber, ring flame tube, mixing, swirl, RANS/ILES.

Belov N.O., Bendersky L.A., Komratov D.V., Lyubimov D.A., Stepanov V.A.

 


Mathematical model of unsteady cooling of gases in heat exchanger

Mathematical model of unsteady heat transfer for heat-exchanger walls is suggested. The heat-exchanger is used for decrease of aviation engine test facility exhaust gas temperature. The analytical solution in quadratures for partial differential system of equations for unsteady heat exchanger parts heating was found, taking into account its conjugation.

Keywords: unsteady heat transfer, heat exchanger, mathematical model.

Aleksandrov V.Yu., Koroleva A.P., Safonova D.B., Frantsuzov M.S.

    

Fatigue of single crystal NI-based superalloy VZHM-4 and VZHM-5 at elevated temperatures

Results of low-cycle and high-cyclic fatigue researches of advanced VZHM-4 and VZHM-5 NI-based superalloy single crystal specimens at 850 and 1050°C.

Keywords: single crystal specimens, low-cycle and high-cyclic fatigue tests, asymmetry coefficient, computation models, low-cycle fatigue curve, high-cyclic fatigue curve, fracture mode.

Golubovsky E.R., Volkov M.E.

  

Cermet-matrix composite material studies

The experimental results are represented for samples of cermet-matrix composite materials based on titanium carbonitride. Tensile strength, compressive strength and bending strength at temperatures up to 1000°C are presented. Deflection curves are shown.

Keywords: composite material, cermet-matrix material, strength.

Nizovtsev V.E., Klimov D.A., Bortnikov A.D., Stupen’kov M.I., Bredikhina E.N., Myktybekov B.

    

Analysis of axial turbine stage for small gas turbine engine using parametric three-dimensional model and subject to the manufacture technology

This article describes the technique of design, gas-dynamic calculation and technological preparation of the axial stage of the turbine of small gas turbine engine based on the use of parametric three-dimensional stage model with a high degree of automation.

Keywords: small gas turbine engine, uncooled turbine stage, blisks turbine, parametric model, end-to-end design.

Danilov M.A.


Influence of fuel properties on the characteristics of an aircraft with air-jet engine

The influence of the fuel energy characteristics on the flight range of rocket aircraft with a ram-jet engine is analyzed. Special attention is paid to the study of effect of density and mass heat of combustion of the fuel on specific impulse of engine and the aerodynamic quality of aircraft. Recommendations are given on the use of the Breguet formula when comparing different fuels.

Keywords: air-jet engine, fuel, flight range.

Averkov I.S., Raznoschikov B.B., Yanovskiy L.S.