Aviadvigatel

Perm’, Russia

Aviadvigatel

Perm’, Russia
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Kurteyev V.A.,Research and Production Association ISKRA | Burdyugov S.I.,Research and Production Association ISKRA | Inozemtsev A.A.,Aviadvigatel | Lomaev V.I.,Mashinostroitel | And 3 more authors.
PNRPU Mechanics Bulletin | Year: 2017

The paper considers the problem of holding a torn blade of a turbojet fan to ensure safety for passengers and crews. It is concerned with one of the main trends in designing fans satisfying this requirement. The experimental and computational analysis of strength for several fan case designs is given. A difference between the calculation results and experimental data for metals with different plasticity is presented. We outlined and described the well-known procedures of calculating metal armoured protection, specified its common disadvantage which is neglecting the material ultimate strain. We suggested the calculation procedure for the metal case which takes the material ultimate strain in account including the boundary value of the material ultimate strain dividing metals on rigid and flexible ones with the calculated formulas of the armoured wall. A good convergence is revealed between the calculation data based on the proposed correlations and the experimental results for Ti and Al alloys. We described the structural design, analyzed strength and the rate of impact absorption by a separated blade using a specially developed goffered hood (a cover) made of the high-strength cloth which can be installed on any fan case made of either metal or polymer composite materials (PCM) without principal changes in the structural configuration. The calculated advantages of using the developed goffered hood design in comparison with the conventional one have been shown. The efficiency has been estimated with respect to applying aluminum alloys as a production material for a fan case being an alternative to the titanium ones. Experimental equipment for testing full-size cases is proposed. The disadvantages of the testing equipment for model cases have been outlined. We analyzed the problem of PCM application for a load-carrying case which is cut by fan blades when one blade is torn away. The engineering estimation of using PCM in a fan case and the solutions aiming to increase the ballistic resistance of PCM cases have been presented. © PNRPU.


Venediktov V.D.,CIAM | Krupa V.G.,CIAM | Rudenko S.V.,CIAM | Nepomnyashchiy A.D.,CIAM | And 2 more authors.
28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012 | Year: 2012

Some results of calculated and experimental investigations of the high loading single-stage cooled high-pressure turbine (HPT) for a turbofan engine of the civil aviation are shown in this paper. Some results of calculated investigation of the intermediate duct (ID) located between the investigated HPT and the multi-stage low pressure turbine (LPT) are also shown in this paper. Investigations of the HPT were conducted within the experimental module, which includes HPT + ID + first-stage nozzle block of the LPT + guide vane (GV) with the heated air at its inlet.


Vladimirovich B.Y.,Aviadvigatel | Anatolievich C.V.,Aviadvigatel | Andreevna G.N.,Institute of Continuous Medium Mechanics
18th International Congress on Sound and Vibration 2011, ICSV 2011 | Year: 2011

The submitted report is a reaction on few deep-rooted assertions, such as the idea that first resonance frequency of 2-layerd liner with depths of layers hi and h2 is close to resonance frequency of 1-layerd liner hl+h2 depth and the same perforation. Besides, another popular idea is that the second resonance frequency of 2-layerd liner may be determined as a resonance of one of it's component layers. Unfoundedness of these statements could be proved from experiment impedance responses on installation "Interferometer". However the problem we are interested in is: whether it is possible to define exactly and simple enough the resonance frequencies of mul-tilayered liners, basing on resonances of their component layers and using mechanical analogy? More over, how to develop an analytical technique to construct multilayered liners with a necessary ratio of resonance frequencies? The answers for these questions are obtained from comparison analytical and experimental results. Copyright © (2011) by the International Institute of Acoustics & Vibration.


Grinev M.A.,Aviadvigatel | Anoshkin A.N.,Perm National Research Polytechnic Institute | Pisarev P.V.,Perm National Research Polytechnic Institute | Yu Zuiko V.Y.,Perm National Research Polytechnic Institute | Shipunov G.S.,Perm National Research Polytechnic Institute
PNRPU Mechanics Bulletin | Year: 2015

Today the composite materials are widely used in aviation industry for load bearing elements of aircraft engines. The following problems need to be solved for an effective composite application: Firstly, choosing the optimal reinforcing scheme for main working area of construction, and secondly, realizing the stress-strain analysis for the most loaded zones with complex geometry such as joints, layer crossings and area connections. The present work is devoted to detailed stress-strain analysis of composite outlet guide vane (OGV) for aircraft engine. The 3D problem formulation of mechanics of anisotropic laminated composite for strength prediction was given. The technological scheme of laying out anisotropic plies and fastening method were taken into account in the model. The scheme of reinforcing for OGV was determined in the previous researches. The maximum stress criterion was used for estimation of strength margin. The numerical simulation of this problem was carried out by finite element method (FEM) with ANSYS Workbench software. Due to the high dimensionality of FE model, the high-performance computing complex was used. The in-depth layered analysis of stressstrain state of the structure was made. The special focus was made on the areas with twisted layers near the flange of vane where the initiation of high interlaminar stresses is most likely to take place. An estimate of the influence of fastening conditions on the stress state for OGV was obtained. It was shown that interlaminar shear stresses are the most dangerous. It was found that the VKU-39 material and [0°/±45°] reinforcing scheme allow to provide the double strength margin under working loads for developed OGV. © PNRPU.


Grinev M.A.,Aviadvigatel | Anoshkin A.N.,Perm National Research Polytechnic Institute | Pisarev P.V.,Perm National Research Polytechnic Institute | Zuiko V.Y.,Perm National Research Polytechnic Institute | Shipunov G.S.,Perm National Research Polytechnic Institute
PNRPU Mechanics Bulletin | Year: 2015

Today the world trend in aircraft engine industry is the replacement of metal alloys to composite materials which allows a significant weight reduction and increase of product performance. The use of composites not only for lightly loaded elements, but for the critical parts such as the fan blades and outlet guide vanes (OGV) is already researched and implemented. Outlet guide vanes (OGV) also called flow straightening vanes, are radially disposed behind the fan to straighten out the airflow to reduce losses in the outer contour of the engine. Design and manufacturing techniques development for composite outlet guide vane is a complex scientific and engineering problem including modeling, simulation and design of composite structure, specifying its design features and reinforcement schemes, choosing materials and optimal manufacturing techniques. Such giants of aviation industry as GeneralElectric, Rolls-Royce, SNECMA are seriously engaged in this problem. Therefore, manufacturing composite outlet guide vane for new domestic PD-14 aviation propulsion, scheduled for installation on the short-range and mid-range jet aircraft MS-21 is a very important problem. It's easy to show that the use of polymeric composite materials (PCM) instead of metal in OGV can lead to decrease of engine weight for up to 8-10 kg. The goal of this work is the implementation of CAD/CAE technologies for engineering analysis of composite outlet guide vanes of PD-14 engine. The three-dimensional model of OGV for stress-strain analysis was developed in Siemens NX CAD-system. The numerical simulation of mechanical behavior of OGV made of balanced textile CFRP under the static pressure was carried out with ANSYS Workbench software. The technique of static strength prediction was examined. The developed numerical model allows analyzing the effective stress-strain fields in whole volume and its components in each layer separately. The four reinforcement schemes were reviewed. It was shown that the quasi-isotropic reinforcement scheme also called "black aluminum" is an optimal choice for obtaining the high strength and stiffness properties of OGV. The results of numerical simulation confirm the preliminary estimations of the effectiveness of composite materials application in the design of OGV obtained by the authors earlier. © PNRPU.


Inozemtsev A.A.,Aviadvigatel | Tikhonov A.S.,Aviadvigatel | Sendyurev C.I.,Aviadvigatel | Samokhvalov N.Y.,Aviadvigatel
Thermal Engineering (English translation of Teploenergetika) | Year: 2013

A new design of the first-stage nozzle vane for the turbine of a prospective gas-turbine engine is considered. The blade's thermal state is numerically simulated in conjugate statement using the ANSYS CFX 13.0 software package. Critical locations in the blade design are determined from the distribution of heat fluxes, and measures aimed at achieving more efficient cooling are analyzed. Essentially lower (by 50-100 C) maximal temperature of metal has been achieved owing to the results of the performed work. © 2013 Pleiades Publishing, Ltd.

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