Agency: Cordis | Branch: FP7 | Program: CP-FP | Phase: AAT.2013.4-2.;AAT.2013.1-1. | Award Amount: 5.83M | Year: 2013
Virtual prototyping (VP) is a key technology for environmental friendly and cost effective design in the aircraft industry. However, the underlying analysis and simulation tools (for loads, stresses, emissions, noise), are currently applied with a unique set of input data and model variables, although realistic operating conditions are a superposition of numerous uncertainties under which the industrial products operate (uncertainties on operational conditions, on geometries resulting from manufacturing tolerances, numerical error sources and uncertain physical model parameters). Major new developments in this new scientific area of Uncertainty Management and Quantification (UM and UQ) and Robust Design methods (RDM) are needed to bridge the gap towards industrial readiness, as the treatment of uncertainties enables a rigorous management of performance engagements and associated risks. This is the main objective of the UMRIDA project, which has the following action lines: Address major challenges in UQ and RDM to develop and apply new methods able to handle large numbers of simultaneous uncertainties, generalized geometrical uncertainties in design and analysis within a turn-around time acceptable for industrial readiness in VP systems. To respond to the validation requirements of UQ and RDM, a new generation of database, formed by industrial challenges (provided by the industrial partners), and more basic test cases, with prescribed uncertainties, is proposed. The methods developed will be assessed quantitatively towards the industrial objectives on this database, during the project and at two open workshops. The gained experience will be assembled in a Best Practice Guide on UQ and RDM. It is anticipated that the UMRIDA project will have a major impact on most of the EU objectives for air transport, by enabling design methods to take into account uncertainty based risk analysis.
Agency: Cordis | Branch: FP7 | Program: CP-SICA | Phase: NMP.2012.2.2-3 | Award Amount: 4.10M | Year: 2013
This project is focused to advance considerably the efficiency of power generation in gas turbine processes by the development of improved thermal barrier coated parts or components of significantly improved performance as well as software products providing optimized process parameters. The proposed project addresses the following scientific and technological issues: New TBC formulations with long-term stability, more resistant under extremely severe operating conditions (e.g. creep, fatigue, thermal-mechanical fatigue, oxidation and their interactions, at high service temperatures) thus the maximum application temperature will be higher (e.g.1450-1500oC) and so performance during energy generation. Flexible and cost effective production systems based mainly on thermal spray (SPS/SPPS, APS, HVOF) but also EB-PVD in order to realize patterned functional TBCs with improved properties. Application of structural analysis and fluid simulation software, including radiation, combustion, heat transfer, fluid-structure interactions and conjugate heat transfer models for the development of detailed models for the operational performance and prediction of spallation phenomena and failure. Environmentally friendly process using chemical formulations free of hazardous and toxic solvents. The aim of this project is the development of materials, methods and models suitable to fabricate, monitor, evaluate and predict the performance and overall energy efficiency of novel thermal barrier coatings for energy generative systems. By the radical improvement of the performance (working temperature, lifetime etc) of materials in service, by the application of novel thermal barrier coatings, structural design and computational fluid simulations a significant improvement in energy efficiency and cost effectiveness will be achieved.
Zaev I.A.,RAS Research Center Kurchatov Institute |
Potapkin B.V.,OOO Kintekh Laboratory |
Fedorov S.A.,OAO NPO Saturn |
Kuprik V.V.,OAO NPO Saturn
Russian Aeronautics | Year: 2014
A model of the burner of low-emission combustion chamber for the stationary A. Lyul’ka Saturn AL-31ST gas turbine drive has been developed and verified. By comparing the calculation results based on the model developed and the experimental measurements, it has been shown that this model can be used for estimating the pollutant emission from the combustion chamber being modeled. The basic requirements to computational models, which are necessary to provide an adequate accuracy of engineering simulation of pollutant emission from low-emission combustion chambers, have been formulated based on the analysis of calculation results. © 2014, Allerton Press, Inc.
Poletaev V.A.,Solovev Rybinsk State Aviation Engineering University |
Tsvetkov E.V.,OAO NPO Saturn
Russian Engineering Research | Year: 2016
A design method is proposed for automated processes used in the manufacture of gas-turbine blades. As an example, the manufacture of stator blades for a gas turbine is considered. A multifunctional numerically controlled grinding machine is used in the example. © 2016, Allerton Press, Inc.
Ryabov A.A.,Sarov Engineeering Center |
V.i. Romanov,Sarov Engineeering Center |
Rechkin V.N.,Sarov Engineeering Center |
Shmotin Yu.N.,OAO NPO Saturn |
Veselov A.V.,OAO NPO Saturn
Russian Aeronautics | Year: 2011
A computational technique, developed for analysis of strength, stability and low-cycle durability of GTE exhaust frame complex structure under operational and emergency loads is described. The presented technique, based on the ANSYS and STAR-CD engineering analysis software, and self-design software can improve the accuracy and efficiency of calculations, and reduce efforts on finite element mesh development, performing calculations and processing of results. © 2011 Allerton Press, Inc.
Gur'yanov A.I.,Rybinsk State Aviation Technical University |
Evdokimov O.A.,Rybinsk State Aviation Technical University |
Piralishvili S.A.,Rybinsk State Aviation Technical University |
Veretennikov S.V.,Rybinsk State Aviation Technical University |
And 2 more authors.
Russian Aeronautics | Year: 2015
We performed the computational and analytical estimation of parameters and formulated the recommendations for conversion of the combustion chamber of the E70/8 RD engine combustion chamber to associated petroleum gas and oil. © 2015, Allerton Press, Inc.
Logunov A.V.,OAO NPO Saturn |
Shmotin Y.N.,OAO NPO Saturn |
Danilov D.V.,OAO NPO Saturn
Russian Metallurgy (Metally) | Year: 2015
The criteria that determine the operating ability of nickel superalloys are described. The binary Ni–W, W–Re, and Re–Ni phase diagrams are analyzed to find concentration characteristics and the probability of formation of β, α, and other undesirable phases based on refractory elements from a γ solid solution. The NewPhacomp method is corrected for single-crystal nickel superalloys. Additional criteria are introduced to estimate the probability of decomposition of the hardening γ’ phase and the precipitation of embrittling lamellar η and δ compounds from this phase. © 2015, Pleiades Publishing, Ltd.