OJSC Aviadvigatel

Perm’, Russia

OJSC Aviadvigatel

Perm’, Russia
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Maslovskiy A.,Radar Technologies 2T ltd | Bakulin M.,Radar Technologies 2T ltd | Snitko M.,OJSC Aviadvigatel
Proceedings of the ASME Turbo Expo | Year: 2012

This article is devoted to the principles of construction of the microwave tip clearance measurement system in gas turbine engines and describes a microwave sensor that designed to operate in temperatures up to 1700C with a resolution of 0.05 mm. The sensor can effectively operate in dirty environments and has the ability to see through oil, combustion products, and other common contaminants. Also the article is devoted to the use of microwave measurement systems to solve other practical problems (measurements tip-timing, vibration, pressure and etc). The main applications of these systems are discussed on the basis of the plant tests and laboratory tests of aircraft turbine engines. Copyright © 2012 by ASME.

Sipatov A.M.,OJSC Aviadvigatel | Usanin M.V.,OJSC Aviadvigatel | Chuhlantseva N.O.,OJSC Aviadvigatel
16th AIAA/CEAS Aeroacoustics Conference (31st AIAA Aeroacoustics Conference) | Year: 2010

The experience of applying ANSYS-Fluent software to describe a noise sources generation process during jet flow numerical simulations has been presented. Applying various computational approaches was shown. Their influence on the quality of the obtained results was investigated. As an initial task the small amplitude Gauss impulse distribution along the straight-line rectangular channel was considered. Three different nozzles configurations (supersonic, subsonic and coaxial subsonic nozzles) were studied. For the last nozzle configuration the chevrons influence on the flow structure and on the noise level in the far field was investigated. The acceptable agreement of numerical results and experimental data was achieved for the subsonic test case. For the coaxial subsonic nozzle we obtained quantitative agreement. The main difficulty of the computational modeling consisted in avoiding the numerical instability when the low diffusion scheme was applied. © 2010 by OJSC Aviadvigatel. Published by the American Institute of Aeronautics and Astronautics, Inc.

Bersenev Y.V.,OJSC Aviadvigatel | Viskova T.A.,OJSC Aviadvigatel | Belyaev I.V.,Central Aerohydrodynamic Institute TsAGI | Palchikovskiy V.V.,Perm National Research Polytechnic Institute | And 3 more authors.
PNRPU Mechanics Bulletin | Year: 2016

Geometrical and mechanical parameters of multi-layer panels used as soundabsorbing liners in the ducts of aircraft engines are determined by acoustic impedance requirements of the liners. The requirements are stated based on the analysis of sound modes propagation in ducts and in particular in the inlet. Therefore, knowledge of the sound field modal structure in an intake duct is essential for the choice of geometrical and mechanical parameters (depth of layers, dimensions and forms of honeycomb chambers, percent open area, material of construction and core, type of glue and etc.) of sound-absorbing liners. Experimental determination of the modal structure can be made with a microphone array mounted inside or outside the duct. In the present work, a planar microphone array placed outside the inlet duct has been used for measuring spinning acoustic modes, and the obtained data was processed with the beamforming method. Spinning modes were produced by a special generator based on the inlet of PS-90 turbofan engine. Sound was generated by 34 acoustic drivers JBL 2451H placed around the circumference under the test rig. Tests were carried out without flow. Experimental investigations were performed in the brand new anechoic chamber of Perm National Research Polytechnic University. The measurement results show that planar beamforming method locates a spinning mode at a point, which position depends on the mode number (this phenomenon is similar to the results obtained with planar beamforming method for propeller or open rotor noise). The conclusion has been made that measurements with planar beamforming method of spinning modes radiated from an inlet allow, in principle, determining noise modal structure in the duct but practical implementation of the method for real aircraft engines requires special research. Localization of spinning modes at a point has to be taken into account in the analysis of aircraft engine noise sources measured with beamforming method. © PNRPU.

Semenov S.V.,Perm National Research Polytechnic Institute | Nikhamkin M.Sh.,Perm National Research Polytechnic Institute | Korepanova O.V.,OJSC Aviadvigatel | Berendorf Y.A.,OJSC Aviadvigatel
29th Congress of the International Council of the Aeronautical Sciences, ICAS 2014 | Year: 2014

The paper is dedicated to the features of aircraft engines rotor systems with supports stiffness anisotropy vibration characteristics experimental investigation. The problem of rational accelerometers mounting scheme is considered in particular. Informativity of two mounting schemes experimental comparison analysis is provided via model test rig and real gas turbine engine rotor dynamics experimental investigation.

Nazukin V.A.,Perm National Research Polytechnic Institute | Avgustinovich V.G.,OJSC Aviadvigatel
Proceedings of the ASME Turbo Expo | Year: 2014

At present, the key element of lean low NOx combustors is a premixer where swirlers are often used for intensification of mixing processes and further formation of required flow pattern in combustor liner. Swirling flow leads to significant effect of some parts of hardware on stream features and mixing quality, emergence of flashback and flame blowout, formation of complex eddy structures causing flow perturbations. Therefore, at design phase, it is necessary to pay great attention to aerodynamics of premixers. The most effective method of swirling flow analysis in real combustor design is computational fluid dynamics (CFD). The present work is dedicated to study the effect of some computational model parameters, such as a turbulence model, grid size on calculation results as well as the analysis of the flow pattern in real swirler. Comparison between the analysis and experimental data showed that use of Detached Eddy Simulation (DES) allows to defining flow structure more accurately rather than use of RANS (URANS) with SST turbulence model also the size of computational grid elements influences stability of vortex structures. Analysis of swirling flow in production combustor swirler showed presence of large number of different eddy structures that can be conditionally divided into three types relative to its location of origin and a propagation path. Further, features of each eddy type were subsequently defined. Comparison of calculated and experimental pressure fluctuations spectrums verified correctness of computations. It was also noted that for the studied construction there is not even qualitative agreement between the steady and the timeaveraged results of unsteady computations. Copyright © 2014 by ASME.

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