Begell House Inc.
TsAGI Science Journal
TSAGI
1948-2590
45
3-4
2014
TO THE 100TH BIRTHDAY OF VLADIMIR VASILIEVICH STRUMINSKII
179-180
10.1615/TsAGISciJ.2014011674
Sergei Leonidovich
Chernyshev
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russia
STRUMINSKII
PREFACE: COMPUTATIONAL EXPERIMENTS IN AEROACOUSTICS
181
10.1615/TsAGISciJ.2014011704
Ivan Vladimirovich
Egorov
Deputy Director, Aerothermodynamics, Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russia; MIPT, 9 Institutsky pereulok, Dolgoprudny, Moscow region, Russia
Conference
EXAMPLES OF NUMERICAL SIMULATION OF COMPLEX TURBULENT FLOWS AND ACCOMPANYING PROBLEMS
183-213
10.1615/TsAGISciJ.2014011734
Sergei Yu.
Krasheninnikov
Central Institute of Aviation Motors (CIAM), 2 Aviamotornaya St., Moscow, 111116, Russia
Dmitriy Aleksandrovich
Lyubimov
Central Institute of Aviation Motors (CIAM), 2 Aviamotornaya St., Moscow, 111116, Russia
Aleksey Konstantinovich
Mironov
Central Institute of Aviation Motors (CIAM), 2 Aviamotornaya St., Moscow, 111116, Russia
Dmitriy Evguenyevich
Pudovikov
Central Institute of Aviation Motors (CIAM), 2 Aviamotornaya St., Moscow, 111116, Russia
Pavel Damirovich
Toktaliev
Central Institute of Aviation Motors (CIAM), 2 Aviamotornaya St., Moscow, 111116, Russia
numerical simulation
spatial unsteady flows
turbulence
RANS
URANS
LES
acoustic waves
Numerical solutions to the steady Reynolds-averaged Navier−Stokes (RANS) and unsteady RANS (URANS) equations with phenomenological turbulence modeling and full unsteady Navier−Stokes equations are obtained for complex flows, in which the important characteristics are turbulence, unsteady behavior, three-dimensionality, instability development, existence of acoustic effects, etc. A series of problems are solved, which are addressed to not only determine specific parameters of the considered complex flows, but also to analyze their features, which cannot be simulated by numerical methods, or new features, that were unknown before the current investigation. Numerical simulation of a vortex flow that arises during aeroengine operation near the ground was performed based on the solutions to the Reynolds equations. The numerical simulation showed that external particles are sucked into the air intake by the vortex through ejection of small particles from the vortex and their subsequent accumulation at the base of the vortex, where a high-density dust particle medium is formed. Numerical simulation of a separated flow in a curved annular diffuser was performed based on the RANS, URANS, and large eddy simulation (LES) approaches. Simultaneously, experimental research was carried out on the models. In both the simulations and experiments, zones of nonuniformity were detected and unsteady and three-dimensional types of flow were observed. However, the average flow field at the diffuser exit was found to be axisymmetrical. The flow simulation and experiments for a strongly swirling jet showed that the flow in the jet is fundamentally unsteady and three-dimensional and can be classified as steady and two-dimensional only on average. Numerical simulation of a flow in a turbulent jet behind the chevron nozzle based on the RANS technique allowed detecting vortex structures generated by chevrons and determining the intensity of the longitudinal vorticity, in which the values agreed with the acoustic measurements. A formulation of the initial conditions for the numerical solution of the unsteady Navier−Stokes equations is proposed for the simulation of flows in turbulent jets near the nozzle edge. The proposed initial conditions allow the process of mixing layer development near the nozzle edge to be simulated with appropriate accuracy.
HIGH-RESOLUTION RANS/ILES METHOD FOR COMPLEX TURBULENT JETS
215-236
10.1615/TsAGISciJ.2014011703
Leonid Aleksandrovich
Bendersky
Central Institute of Aviation Motors (CIAM), 2 Aviamotornaya Str., Moscow, 111116 Russia
Dmitriy Aleksandrovich
Lyubimov
Central Institute of Aviation Motors (CIAM), 2 Aviamotornaya St., Moscow, 111116, Russia
RANS/ILES
turbulent jet
supersonic jet
aerodynamic chevrons
single nozzle
C/D nozzle
bypass nozzle in TJE installation
The high-resolution Reynolds-averaged Navier−Stokes/implicit large eddy simulation (RANS/ILES) method has been applied to coupled flow calculations in the nozzles with different geometries and nozzle jets. Good agreement with the experiment was achieved in the turbulence and flow parameters for a subsonic jet. The sound pressure spectra satisfactorily fit the experiment data up to Sh = 4−6. The effect of the inlet temperature on the flow and turbulence parameters was investigated in a supersonic jet from a convergent/divergent (C/D) nozzle. The influence of aerodynamic chevrons on the flow and turbulence parameters in the nozzle jet of a bypass turbojet engine (TJE) was studied numerically. Installation calculations in the jet from bypass TJE nozzle were performed as well. The installation included a bypass nozzle, pylon, and wing with deflected flaps. The effect of the angle of attack on the jet flow from the TJE nozzle was investigated for the specified installation. The aforementioned calculations were performed on grids with 1-3.3 × 106 cells, providing sufficiently good agreement with the available experimental data in each case.
GROUND TESTING OF THE LAUNCH VEHICLE ACOUSTICS
237-254
10.1615/TsAGISciJ.2014011945
Yuriy Mikhaylovich
Lipnitskiy
Central Research Institute of Machine Building (TsNIIMash), 4 Pionerskaya str., Korolev, Moscow Region, 141070, Russia
Aleksandr Victorovich
Safronov
Central Research Institute of Machine Building (TsNIIMash), 4 Pionerskaya str., Korolev, Moscow Region, 141070, Russia
llaunching complex
launch gas dynamics
experimental facilities
acoustic processes during missile takeoff
This paper presents a generalization of the results on launch vehicle acoustics obtained at the Central Research Institute of Machine Building (TsNIIMash) over the past 15–20 years. Experimental/computational techniques are developed including acoustic studies on the small-scale facilities of TsNIIMash (with gas generator thrust below 2 tf), and large-scale facilities of Rocket and Space Industry Research and Testing Center (with the thrust up to 50 tf). The present work describes engineering computational
methods based on the generalization of in situ measurements and acquisition tests that allow optimizing testing devices and reducing the number of ground tests when examining launch vehicle acoustics and recalculating the modeled data to adjust for the full-scale conditions. Optimization of the ground acoustics testing compared to earlier works is implemented by applying a large-scale liquid propellant engine model and by reducing the number of tests on the large-scale rigs due to the small-scale tests on kerosene/
air rigs. A small-scale pulsed rig that reconstructs the full-scale temperature of the propellant using the
products of combustion of the oxygen/hydrogen/methane/nitrogen mixtures is applied to recalculate the modeled data for full-scale conditions.
CALCULATION METHOD FOR UNSTEADY AERODYNAMIC BLADE ROW INTERACTION IN A MULTISTAGE TURBOMACHINE
255-271
10.1615/TsAGISciJ.2014011921
Anatoly Alekseevich
Osipov
Central Institute of Aviation Motors (CIAM), 2 Aviamotornaya St., Moscow, 111116, Russia
Anton Anatolyevich
Rossikhin
Central Institute of Aviation Motors (CIAM), 2 Aviamotornaya St., Moscow, 111116, Russia
turbomachinery blade rows
rotor/stator interaction
two-dimensional analysis
tonal noise
dual-stage turbine
coupled mode analysis
harmonic balance method
numerical DRP scheme
A mathematical model is presented for the calculation of the multistage turbomachinery tonal noise that takes into account the effects of the unsteady aerodynamic interaction in a system of several mutually rotating blade rows. The model is based on the frequency/modal spectrum analysis of turbomachinery gas flow parameter fluctuations, which allows determining the space/time structure of the perturbation field induced by the interaction of the rotor and stator blade rows. The method of tonal noise calculation is realized in the CIAM domestic three-dimensional acoustics solver (3DAS) using modern highly efficient finite-difference schemes of the numerical integration of the Euler equations for flow parameter fluctuations.
SIMULATION OF PERIODIC VORTICAL STRUCTURES IN THE AIRFOIL WAKE
273-292
10.1615/TsAGISciJ.2014011965
Pavel Andreevich
Baranov
Battery Company "RIGEL", 38, Professor Popov Str., St. Petersburg, 197376 Russia
Sergey Vladimirovich
Guvernyuk
Institute of Mechanics, Lomonosov Moscow State University
Sergey A.
Isaev
Saint Petersburg State University of Civil Aviation, 38 Pilotov Str., St. Petersburg, 196210, Russia; Tupolev Kazan National Research Technical University – Kazan Aviation
Institute, 10 K. Marx Str., Kazan, Tatarstan, 420015, Russia
Aleksandr Grigoryevich
Soudakov
Battery Company "RIGEL", 38, Professor Popov Str., St. Petersburg, 197376 Russia
Aleksandr Evguenyevich
Usachov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
numerical simulation
turbulence
airfoil
procedure of pressure correction
multi-block computing technologies
VP2/3 software package
Parametrical calculations of an unsteady flow around a NACA 0012 airfoil at a fixed Reynolds number of 40,000 are performed using several multi-block overlapping grids of different scales and densities, which cover settlement areas of various extents, including the near and far wakes. The solutions found by Menter's shear stress transport model, the Spalart−Allmaras vortex viscosity transport
model, and the method of vortical domains, are compared with available estimated and experimental data. Verification of the two-dimensional model is performed by comparison of the numerical predictions for a cross flow over a thick plate with Igarashi's experimental data.
DEVELOPMENT OF A METHODOLOGY FOR PROPELLER NOISE CALCULATION ON HIGH-PERFORMANCE COMPUTER
293-327
10.1615/TsAGISciJ.2014011857
Victor F.
Kopiev
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russia
Vladimir Aleksandrovich
Titarev
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, Moscow Region, 140180 Russia; Dorodnicyn Computing Centre of the Russian Academy of Sciences, 40, Vavilova Str., Moscow, 119333 Russia
Ivan Valentinovich
Belyaev
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, Moscow Region, 140180 Russia
propeller
unstructured mesh
TVD scheme
high-performance
computer calculation
airframe noise
An approach to numerical calculation of the aerodynamic and acoustic characteristics of a realistic rotor is presented. The numerical calculation of the aerodynamic parameters is based on a high-order implicit scheme applicable to arbitrary unstructured meshes. The sound field is calculated using the Ffowcs Williams−Hawkings approach. To decrease the calculation time, a parallel version of the aerodynamic solver is used, which is based on the message passing interface technology. The applicability of the approach and the corresponding software are illustrated through the problem of flow around a six-blade aviation propeller and include validation of the solver by comparing the numerical results with the experimental data for drag and thrust, scalability tests for up to 1024 processor cores, and study of the influence of the time step size on the convergence rate to the stationary solution. The calculation of the acoustic field is verified on the basis of an exact solution of the linear approximation.
EFFECT OF VORTEX GENERATORS ON THE DIRECTION DIAGRAM OF ACOUSTIC EMISSION OF SUPERSONIC JETS
329-343
10.1615/TsAGISciJ.2014011693
Valeriy Ivanovich
Zapryagaev
Khristianovich Institute of Theoretical and Applied Mechanics (ITAM), Siberian Branch of the Russian Academy of Sciences, 4/1 Institutskaya str, Novosibirsk, 630090, Russia
Nikolay Petrovich
Kiselev
Khristianovich Institute of Theoretical and Applied Mechanics (ITAM), Siberian Branch of the Russian Academy of Sciences, 4/1 Institutskaya str, Novosibirsk, 630090, Russia
Dmitriy Andreevich
Gubanov
Khristianovich Institute of Theoretical and Applied Mechanics (ITAM), Siberian Branch of the Russian Academy of Sciences, 4/1 Institutskaya str., Novosibirsk, 630090, Russia
supersonic jet
acoustic emission
direction diagram
injection of microjets
chevrons
The results of an experimental study on the influence of two types of vortex generators mounted at the exit of a convergent nozzle on the direction diagram of the acoustic emission of a supersonic under-expanded jet are reported. The vortex generators are chevrons or microjet injectors (six chevrons or six microjets). Both vortex generators are found to suppress the screech tone in jet noise. The effect of jet noise reduction using vortex generators is detected for Strouhal numbers lower than the critical value. For high Strouhal numbers, the noise intensity is found to increase. The value of the critical Strouhal number depends on the observation angle and vortex generator type. The use of a microjet generator leads to uniform reduction of jet noise in the entire range of observation angles. The presence
of a chevron vortex generator leads to effective reduction of jet noise only for observation angles close to the jet exhaustion direction.
STUDY OF THE DURABILITY OF ISOTROPIC PLATES UNDER WIDEBAND ACOUSTIC LOADING WITH DIFFERENT TYPES OF SPATIAL CORRELATION FUNCTIONS
345-365
10.1615/TsAGISciJ.2014011769
Stanislav Leonidovich
Denisov
Moscow Aviation Institute, Volokolamskoe Shosse 4, Moscow, 125993 Russia
Aleksandr Leonidovich
Medvedskii
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky St., 1, Zhukovsky,
Moscow Region, 140180, Russian Federation
Gennadii Vasil'evich
Paranin
Irkut Corporation, Leningradskii Prospekt 68, Moscow, 125315 Russia
spatial correlation function
cross-correlation function
isotropic plates
acoustic fatigue
durability
The effect of the cross-correlation function of the external wideband acoustic field on the durability of a simply supported metallic isotropic plate of finite dimensions was considered in this study. The computations performed show that the plate durability depends not only on the acoustic field spectral content but also on the form of the cross-correlation function.
COMPLEX OF ALGORITHMS AND PROGRAMS FOR CALCULATION OF AIRCRAFT NOISE
367-388
10.1615/TsAGISciJ.2014011838
Vladimir Grigor'evich
Dmitriev
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russia
Valerii Fedorovich
Samokhin
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, Moscow Region, 140180 Russia
calculation of aircraft noise
methods of calculating aircraft noise
software package AERONOISE
The AERONOISE complex of algorithms and programs developed at TsAGI is considered. The noise levels on jet and screw airplanes and helicopters can be computed with the AERONOISE complex. Also, acoustic problems arising during optimization of the parameters of an air vehicle under the criterion
of the minimum environmental aircraft noise level and at the acoustic zoning areas of airports and their vicinities can be solved with AERONOISE. In the current study, the part of the complex concerning the noise computation for jet airplanes at reference points is discussed. In the complex,
acoustic computation of an aircraft for three levels corresponding to the different stages of design and
operation of aircraft is implemented. The algorithms of the first and second levels are based on the computational gas-dynamic characteristics of the power plant and on the aircraft performance characteristics. The algorithm of the third level uses the results of the measurements of matrices of the noise levels of an engine on the open stand.