Numerical Investigation of the Low Pressure Compressor Tone Noise of a High Bypass Ratio Turbofan

2020 ◽  
Author(s):  
Anton Rossikhin ◽  
Sergey Pankov ◽  
Victor Mileshin
Keyword(s):  
Frequency Domain ◽  
Computational Method ◽  
Test Facility ◽  
Frequency Domain Method ◽  
Noise Generation ◽  
Operational Conditions ◽  
3 Dimensional ◽  
Noise Simulation ◽  
Bypass Ratio ◽  
Pressure Compressor

Abstract The presented work investigates the tone noise of three booster stages designed for a high bypass ratio turbofan. Calculations were performed at the approach operational conditions. The frequency domain numerical method of multistage turbomachines tone noise simulation, developed in CIAM (Central Institute of Aviation Motors) and implemented in 3DAS (3 Dimensional Acoustics Solver) in-house solver was used. The aim was to perform once again the validation of the computational method and to obtain better understanding of the mechanisms of tone noise generation in multistage turbomachines. The results of the investigation were compared with the experimental data obtained in the CIAM C-3A acoustic test facility. In general satisfactory correspondence between the numerical calculations and the experiment was observed. This can be treated as a significant argument for the validity of the frequency domain method of the multistage turbomachinery tone noise calculations.

Numerical and Experimental Investigation of Acoustic Characteristics of a Fan Model With Struts Integrated in a Stator

2017 ◽  
Author(s):  
Anton Rossikhin ◽  
Iaroslav Druzhinin ◽  
Iurii Khaletskii ◽  
Victor Mileshin
Keyword(s):  
Horizontal Plane ◽  
Sound Pressure ◽  
Near Field ◽  
Test Facility ◽  
Acoustic Characteristics ◽  
Operational Conditions ◽  
3 Dimensional ◽  
Noise Simulation ◽  
It Support ◽  
Bypass Ratio

The results of the high bypass ratio turbofan fan tone noise simulation performed in CIAM (Central Institute of Aviation Motors) are presented. The feature of a design of the fan is that in it support struts are integrated to the stator. This investigation is a continuation of a series of papers devoted to numerical calculation of fan tone noise done in CIAM using the 3DAS (3 Dimensional Acoustics Solver) CIAM in-house solver. The calculation was performed at the approach operational conditions of the fan. As a result of the calculation the fields of the flow pulsations in the near field and the distribution of sound pressure levels in the far field on the surface surrounding the fan was obtained. It was shown that the distribution is strongly nonuniform both in the polar and in the azimuth directions. The results of the computation are compared with the experimental data from the CIAM C-3A acoustic test facility. In general, satisfactory correspondence between the calculation and the experiment for the directivity of sound in the horizontal plane is obtained.

Numerical Investigation of the First Booster Stage Tone Noise of a High Bypass Ratio Turbofan

2016 ◽  
Author(s):  
Anton Rossikhin ◽  
Sergey Pankov ◽  
Victor Mileshin
Keyword(s):  
Numerical Investigation ◽  
Operating Conditions ◽  
Test Facility ◽  
Far Field ◽  
3 Dimensional ◽  
Blade Passing Frequency ◽  
Noise Simulation ◽  
Bypass Ratio ◽  
Pressure Compressor ◽  
Forward Hemisphere

The results of the first booster stage tone noise numerical investigation for a model of low pressure compressor are presented. The investigation was performed using the frequency domain numerical method of multistage turbomachines tone noise simulation, developed in CIAM (Central Institute of Aviation Motors) and implemented in the 3DAS (3 Dimensional Acoustics Solver) in-house solver. The model under consideration included high bypass ratio fan, stator, booster and bypass duct. Calculation was performed at the approach operating conditions. Far field directivities for two tones in the forward hemisphere were obtained. One tone corresponded to the blade passing frequency of the first stage rotor, the other - to the sum of this frequency with the blade passing frequency of the fan. The results of the computation were compared with the experimental data obtained in the CIAM C-3A acoustic test facility. In general satisfactory correspondence between calculation and experiment was obtained.

Frequency-domain method for multistage turbomachine tone noise calculation

2017 ◽  
Vol 16 (6) ◽  
pp. 491-506
Author(s):  
Anton A Rossikhin
Keyword(s):  
Frequency Domain ◽  
Nonlinear Equations ◽  
Nonlinear Interaction ◽  
Cylindrical Channel ◽  
Three Dimensional ◽  
The Other ◽  
Frequency Domain Method ◽  
Noise Generation ◽  
Two Stage ◽  
Central Institute

A method of frequency-domain calculation of the multistage turbomachinery tone noise is presented. The method is based on the kinematic relations featuring dependence of flow fields in a turbomachine on time and circumferential angle. It solves the flow in several blade passages inside each row and can be used in conjunction with nonlinear equations. The method is developed at Central Institute of Aviation Motor and implemented in the Three Dimensional Acoustics Solver in-house solver. The multi-passage method is verified on two numerical problems. One is the tone noise generation by a 2D two stage turbine. The other is the problem of nonlinear interaction of circumferential modes in a 2D cylindrical channel.

Numerical Method for Turbomachinery Tonal Noise Generation and Radiation Simulation Using CAA Approach

2008 ◽  
Author(s):  
Mikhail A. Nyukhtikov ◽  
Anton A. Rossikhin ◽  
Vasily V. Sgadlev ◽  
Igor A. Brailko
Keyword(s):  
Numerical Method ◽  
Three Dimensional ◽  
Noise Generation ◽  
Tonal Noise ◽  
3 Dimensional ◽  
Ducted Fan ◽  
Noise Simulation ◽  
Direct Numerical Solution ◽  
Rotor Stator Interaction ◽  
Field Radiation

The numerical method for 3D calculation of the turbomachinery tonal noise generation, propagation and radiation in the near and far fields taking account of the rotor-stator interaction is developed in CIAM. The method is based on the direct numerical solution of three-dimensional Euler equations for disturbances in time or in frequency domain using numerical methods of computational acoustics (CAA). For far-field radiation calculation the Ffowcs Williams method is used. The method is build into CIAM domestic aeroacoustic solver 3DAS (3 Dimensional Acoustics Solver). In this paper we present some examples of our method applications for calculation of rotor-stator interaction and propagation: • Ducted fan tonal noise simulation; • Ducted counter-rotated fan noise simulation; • Low pressure turbine tonal noise simulation.

Numerical Investigation of High Bypass Ratio Fan Tone Noise

2014 ◽  
Author(s):  
Anton Rossikhin ◽  
Sergey Pankov ◽  
Igor Brailko ◽  
Victor Mileshin
Keyword(s):  
Experimental Data ◽  
Numerical Calculation ◽  
Numerical Investigation ◽  
Quantitative Agreement ◽  
Operating Conditions ◽  
Anechoic Chamber ◽  
Test Facility ◽  
3 Dimensional ◽  
Qualitative And Quantitative ◽  
Bypass Ratio

Results of the high bypass ratio (>8) turbojet fan tone noise simulations in the cutback and sideline operating conditions are presented. Calculations are performed using the method of 3D unsteady numerical calculation of interaction between fan rows implemented in the 3DAS (3 Dimensional Acoustics Solver) CIAM in-house solver. The results of computations are compared with the experimental data for the fan under consideration, obtained in the anechoic chamber of CIAM C-3A acoustic test facility. Comparison was performed for first three harmonics of tone noise for each of conditions. It showed satisfactory qualitative and quantitative agreement between the results of the simulation and the experiment.

Numerical and Experimental Investigation of Acoustic Characteristics of Model Ultra High Bypass Ratio Counter Rotating Fan

2018 ◽  
Author(s):  
Anton Rossikhin ◽  
Iaroslav Druzhinin ◽  
Iurii Khaletskii ◽  
Victor Mileshin
Keyword(s):  
Strong Influence ◽  
Aircraft Engine ◽  
Quantitative Agreement ◽  
Computational Investigation ◽  
Test Rig ◽  
Acoustic Characteristics ◽  
Operational Conditions ◽  
3 Dimensional ◽  
Numerical Investigations ◽  
Bypass Ratio

A computational investigation of acoustic characteristics of model ducted counter-rotating fan COBRA-1 with ultra-high bypass ratio BPR = 20, developed in CIAM in the framework of European Project COBRA (Innovative Counter rOtating fan system for high Bypass Ratio Aircraft engine), is presented in the paper. Calculations of acoustic characteristics of the fan were performed at five operational conditions. For three of them the sums of rotation frequencies of rotors corresponded to those expected for approach conditions, and they differed from each other by relations between frequencies of rotors, and for other two the sums of rotation frequencies corresponded to cutback and sideline operational conditions. Numerical investigations were conducted using the method of 3D numerical calculation of interaction between fan rows implemented in 3DAS (3 Dimensional Acoustics Solver) CIAM in-house solver. The data were compared with the results of the experiments conducted in the CIAM test rig C-3A. The results of comparison show satisfactory qualitative and, in some positions of microphones, quantitative agreement between the results of the simulation and the experiment. Both results demonstrate strong influence of relation between rotation frequencies of rotors on acoustic characteristics and significant dominance of noise radiated from the nozzle over the noise radiated from the inlet.

Numerical Modeling of the Hydrodynamic Performance of Hydrofoils for Auxiliary Propulsion of Ships in Regular Head-Waves

2017 ◽  
Author(s):  
Tamer M. Ahmed ◽  
Yousri Welaya ◽  
Serag M. Abdulmotaleb
Keyword(s):  
Frequency Domain ◽  
Static Method ◽  
Dynamic Stall ◽  
Hydrodynamic Performance ◽  
Frequency Domain Method ◽  
Hull Form ◽  
Hydrodynamic Analysis ◽  
3 Dimensional ◽  
Head Waves ◽  
Regular Head Waves

In this paper, a detailed hydrodynamic analysis of the thrust generated by an oscillating hydrofoil is presented. The hydrofoil is mounted at the bow of a platform supply vessel as a means of auxiliary propulsion and, is vertically oscillating due to the ship’s heave and pitch motions in head-waves. Firstly, responses of the ship without hydrofoil are obtained using a 3-dimensional frequency-domain panel method. The responses of the ship with hydrofoil are then obtained by taking into account the extra forces and moments due to the presence of the foil. Secondly, three methods are used to calculate the average generated thrust, namely: a quasi-static method, a simplified frequency-domain method and, a dynamic stall method. All three methods are compared and appraised against numerical/experimental data available in the literature, for a similar hull form.

scholarly journals Velocity model building by 3D frequency-domain, full-waveform inversion of wide-aperture seismic data

Geophysics ◽  
2008 ◽  
Vol 73 (5) ◽  
pp. VE101-VE117 ◽  
Author(s):  
Hafedh Ben-Hadj-Ali ◽  
Stéphane Operto ◽  
Jean Virieux
Keyword(s):  
High Resolution ◽  
Frequency Domain ◽  
Distributed Memory ◽  
Waveform Inversion ◽  
Steepest Descent Method ◽  
Frequency Domain Method ◽  
Full Waveform Inversion ◽  
Direct Solver ◽  
Velocity Models ◽  
Full Waveform

We assessed 3D frequency-domain (FD) acoustic full-waveform inversion (FWI) data as a tool to develop high-resolution velocity models from low-frequency global-offset data. The inverse problem was posed as a classic least-squares optimization problem solved with a steepest-descent method. Inversion was applied to a few discrete frequencies, allowing management of a limited subset of the 3D data volume. The forward problem was solved with a finite-difference frequency-domain method based on a massively parallel direct solver, allowing efficient multiple-shot simulations. The inversion code was fully parallelized for distributed-memory platforms, taking advantage of a domain decomposition of the modeled wavefields performed by the direct solver. After validation on simple synthetic tests, FWI was applied to two targets (channel and thrust system) of the 3D SEG/EAGE overthrust model, corresponding to 3D domains of [Formula: see text] and [Formula: see text], respectively. The maximum inverted frequencies are 15 and [Formula: see text] for the two applications. A maximum of 30 dual-core biprocessor nodes with [Formula: see text] of shared memory per node were used for the second target. The main structures were imaged successfully at a resolution scale consistent with the inverted frequencies. Our study confirms the feasibility of 3D frequency-domain FWI of global-offset data on large distributed-memory platforms to develop high-resolution velocity models. These high-velocity models may provide accurate macromodels for wave-equation prestack depth migration.

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