13th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics最新文献

{"title":"Instantaneous flow field measurements in the interstage section between a fan and the outlet guiding vanes at different axial positions","authors":"Robert K.J. Meyer, S. Håkansson, W. Hage, L. Enghardt","doi":"10.29008/ETC2019-330","DOIUrl":"https://doi.org/10.29008/ETC2019-330","url":null,"abstract":"The unsteady flow field of a representative fan stage was measured by DLR using hot-wire anemometry. The hot-wire measuring technique allows to determine unsteady flow structures (e.g. the wake of each individual rotor blade). The phase-resolved mean flow velocities as well as the fluctuation components values of the velocity were determined, which then led to the computation of the local turbulence distribution in the flow field. The measurements were performed at different axial positions up- and downstream of the fan. The calculated local turbulence distribution of the flow downstream of the rotating blades shows an increase of the turbulence intensity from about 0.8% to 3% outside of the wake to about 4% up to 24 % in the wake flow depending on the operating point. The measured data also gives a good impression of the mixing process of the wakes with increasing axial distance downstream of the rotor.","PeriodicalId":268187,"journal":{"name":"13th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics","volume":"76 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126716532","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Unconventional centrifugal bladeless turbine for low power range turboexpander applications","authors":"M. Smirnov, Aleksandr Sebelev, Natalia N. Kuklina, G. A. Fokin, N. Zabelin","doi":"10.29008/ETC2019-114","DOIUrl":"https://doi.org/10.29008/ETC2019-114","url":null,"abstract":"Turboexpander generation technology is a promising solution for both CO2 emission reduction and providing autonomous auxiliary power for gas letdown stations and some technological processes. Nevertheless, its further development faces challenges to date due to several major restrictions: 1. long payback period of plants with conventional turbines; 2. significant annual fluctuations of gas inlet parameters; 3. high demands of conventional turbines for working fluid cleanliness. In order to address the abovementioned issues bladeless centrifugal reaction turbine may be introduced for turboexpander systems within power range up to 350 kWt. This turbine is a variation of so-called Segner wheel known for centuries. Its efficiency is lower comparing with the conventional rotary machines, but remains appropriate within the specific conditions of turboexpander application. Having proposed a conceptual design of a turbine the paper then highlights main features of its aerodynamics and kinematics. A comparison of the proposed turbine and axial transonic one is carried out within a wide range of pressure ratios as typical operating conditions. A centrifugal turbine advantage is highlighted which is an ability to generate comparable power as conventional ones while having lower cost and higher mud and erosion resistance.","PeriodicalId":268187,"journal":{"name":"13th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126915242","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Experimental investigation on performance of a control stage turbine under partial admission","authors":"A. Berger, Thomas Polklas, O. Brunn, F. Joos","doi":"10.29008/ETC2019-135","DOIUrl":"https://doi.org/10.29008/ETC2019-135","url":null,"abstract":"Operation of industrial steam turbines under partial admission is usually implemented in order to cope with fluctuations in demand while maintaining a high efficiency. Subject of the article presented is the experimental investigation of the performance and efficiency of a control stage operated with air, under partial admission. Furthermore, the steady state blade loading distribution on the stator in a free passage and at the entry into a not admitted passage is observed. For the experiment, the single-staged axial-flow turbine is operated with varying shaft speed, pressure ratio and admission rate, realized by flow blockaging. Two rotationally symmetric stator endwall designs are tested: a plane and a contoured endwall. Reducing the admission rate at part load decreases the efficiency, especially at high circumferential velocities as precedent investigations showed. Pumping and mixing loss behaviour shows a different scale across the performance map. To prove CFD Simulations, results of the blade loading distribution on the stator are acquired.","PeriodicalId":268187,"journal":{"name":"13th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics","volume":"111 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114650554","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"3D inverse problem solution used to redesign six-stage highly loaded high pressure compressor with the view of designed parameters achievement","authors":"V. Mileshin, I. K. Orekhov, P. Kozhemyako, S. K. Shchipin","doi":"10.29008/etc2019-202","DOIUrl":"https://doi.org/10.29008/etc2019-202","url":null,"abstract":"Flow structure and integral performances for a six-stage high pressure compressor (HPC) are found based on 3D viscous through-flow computation within RANS aided by the modified S.K. Godunov's implicit scheme, “3D-IMP-MULTI” software developed at CIAM. To increase the surge margin a decision was made to modify (R1) operates on the left branch of the characteristic line in the mode with a detached shock. To increase the surge margin a decision was made to modify R1, R3, R4 and R6 of HPC on the basis of 3D inverse problem solution by “3D-INVERSE.EXBL” software developed at CIAM. Results of HPC computations with the modified R1, R3, R4 and R6 showed an increase in the surge margin by 14.0%. Comparison of numerical and experimental data for individual stages and for the whole modified HPC are to be presented for verification of the numerical method of HPC performance computation and redesign.","PeriodicalId":268187,"journal":{"name":"13th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121603695","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Optimization of a carbon-fiber composite blade of a counter-rotating fan for aircraft engines","authors":"T. Schmid, T. Lengyel-Kampmann, T. Schmidt, E. Nicke","doi":"10.29008/ETC2019-432","DOIUrl":"https://doi.org/10.29008/ETC2019-432","url":null,"abstract":"Achieving higher efficiency and less weight is the most important target for future engine development. New lightweight materials like fiber reinforced composites should be applied for the fan blading to reduce the weight. The aerodynamic efficiency should be improved simultaneously. A method that achieves both targets is presented in this paper. This method was carried out on the counter-rotating integrated shrouded propfan (called CRISP), which is a possible future fan concept for ultra-high bypass ratio engines (Gorke et al., 2012). The underlying paper investigates the effects of a numerically optimized multi-ply composite for a given application of a fan blade on its aerodynamic and structural mechanical properties. To determine the effects of different multi-ply composite structures, two structural mechanical preliminary studies with different materials are performed, whereby only the first of the two rotors is considered and the blade geometry remains fixed. Both studies, one with a symmetrical multi-ply structure and the other with a completely free multi-ply composite, showed big advantages through adapted fiber alignments in the optimized multi-ply composites. In a subsequent multidisciplinary optimization with CFD and FEM calculation processes of the complete fan stage, both, the parameters of the 3D blade geometry and the fiber alignments were free. Hence, it was possible to examine the effect of the free parameters in the fiber alignment on the aerodynamic and mechanical potential.","PeriodicalId":268187,"journal":{"name":"13th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125201286","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Thermodynamic analysis of the net power oxy-combustion cycle","authors":"A. Rogalev, Vladimir Kindra, S. Osipov, N. Rogalev","doi":"10.29008/etc2019-030","DOIUrl":"https://doi.org/10.29008/etc2019-030","url":null,"abstract":"This study presents the thermodynamic analysis results of the NET Power cycle featuring nearly 100% CO2 capture level. Significant initial pressure, low turbine pressure ratio, recuperation of heat in regenerator allow achieving very high net efficiency. The cycle design parameters are set up on the basis of the component technologies of today’s state-of-the-art gas turbines. The models of cooled gas turbine compartment and multi-flow high temperature regenerator were developed. The potential pinch points were analyzed. An influence of turbine inlet temperature and pressure, turbine outlet pressure, turbine coolant temperature, cooling water temperature on cycle efficiency was estimated. The performance penalty due to the oxygen production and carbon dioxide capture was examined. For the optimal parameters, the net efficiency of the NET Power cycle is 56.5%. An influence of equipment characteristics adopted in simulation such as turbine and compressor polytropic efficiency on the results was estimated. The sensitivity analysis of the main cycle parameters was provided.","PeriodicalId":268187,"journal":{"name":"13th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125667819","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Neural network topology for wind turbine analysis","authors":"A. Gaymann, Giorgio Schiaffini, M. Massini, F. Montomoli, A. Corsini","doi":"10.29008/ETC2019-174","DOIUrl":"https://doi.org/10.29008/ETC2019-174","url":null,"abstract":"In this work Artificial Neural Networks (ANN) are used for a multi-target optimization of the aerodynamics of a wind turbine blade. The Artificial Neural Network is used to build a meta-model of the blade, which is then optimized according to the imposed criteria. The neural networks are trained with a data set built by a series of CFD simulations and their configuration (number of neurons and layers) selected to improve performances and avoid over-fitting. The basic configuration of the airfoil is the profile S809, which is commonly used in horizontal axis wind turbines (HAWT), equipped with a Coanda jet. The design position and momentum of the jet are optimized to maximize aerodynamic efficiency and minimize the power required to activate the Coanda Jet.","PeriodicalId":268187,"journal":{"name":"13th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics","volume":"51 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129740910","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Comparison of different models for determination of erosion wear in centrifugal pumps","authors":"F. Hankeln, S. Riedelbauch","doi":"10.29008/ETC2019-037","DOIUrl":"https://doi.org/10.29008/ETC2019-037","url":null,"abstract":"Due to long operating time, the efficiency of centrifugal pumps is decreasing gradually. A decreasing efficiency can be originated from different wearing processes, why a detailed knowledge of these processes and their influence can be advantageous for a smooth operating behavior. In this context the erosion induced by solid particles in a centrifugal pump is investigated with the help of computational fluid dynamics. The erosion wear is calculated with two different models. Furthermore, the location of erosion wear and the influence of using a one-way and fully coupled solid phase are investigated. The results show similar locations and distributions of the predicted erosion damage for both examined models. The variation of the particle concentration suggests the assumption that a one-way coupling leads to inaccurate results for high solid concentrations. At least the investigations show an approximated linear scaling of the erosion rate density with the particle concentration and the prevailing volume flow.","PeriodicalId":268187,"journal":{"name":"13th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics","volume":"16 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116391512","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Influence of the numerical strategy on wall-resolved LES of a compressor cascade","authors":"D. Papadogiannis, S. Mouriaux, J. Cagnone, K. Hillewaert, F. Duchaine, S. Hiernaux","doi":"10.29008/ETC2019-418","DOIUrl":"https://doi.org/10.29008/ETC2019-418","url":null,"abstract":"The design of turbomachinery relies on inexpensive, steady-state Reynolds Averaged Navier-Stokes (RANS) predictions. However, turbomachinery flows are complex with various phenomena that can be difficult to predict with RANS. Large Eddy Simulations (LES), resolving the larger scales of turbulence, appear as an attractive alternative. However, correctly resolving turbulence is challenging as numerical schemes with the correct diffusion and dispersion properties are required. The main numerical strategy employed is the Finite Volume approach on structured or unstructured grids. More recently, Finite Element-like methods, intrinsically extending up to very high orders, such as the Discontinuous Galerkin, have emerged. However, few comparisons have been made between these approaches to assess their impact on the LES predictions of turbomachinery. In this work, wall-resolved LES of a realistic linear compressor cascade is performed using three solvers, each employing one of the strategies mentionned. The results highlight that while all three approaches predict similar overall aerodynamic losses, differences in the transition mechanisms and in the turbulent kinetic energy levels are revealed.","PeriodicalId":268187,"journal":{"name":"13th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics","volume":"150 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116345089","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Radial Turbine Global Design for Liquid Rocket Engine Application","authors":"A. Leto","doi":"10.29008/etc2019-324","DOIUrl":"https://doi.org/10.29008/etc2019-324","url":null,"abstract":"The present work aims to show a methodology for estimating the compact radial turbine performance prediction for expander cycle rocket engine application, avoiding a detailed fluid dynamics analysis. Radial turbines find nowadays-widespread use in turbochargers for automotive applications, but their use in aerospace applications has not so frequently been reported. This turbine type represents a viable alternative to the axial turbine, used for space engine application, specifically for the required power generation by the turbo pump feed system. In the expander rocket engine, the performance of the impulse turbines and of the velocity compounding of impulse turbines are limited due to the low expansion ratio. Therefore, the use of a radial turbine, which is characterized by a higher efficiency with a low-pressure ratio, would be more suitable for this motor type. The design of a turbomachine system is a very complex engineering operation, which can be looked upon as an iterative procedure made of various steps. The flow that through a turbine is complex and many mechanisms of the flow losses in turbine, have not be known well. The computational fluid dynamics CFD simulations is based on complex three-dimensional viscous methods, which require considerable iterations and, therefore time, in order to obtain an improvement of the geometry, through the convergence to an acceptable solution often not optimal. Radial Turbine Global Design RTGD is based on one-dimensional models able to predict the global design of the machine based on the combination of empirical and experimental loss models, able to provide a good performance estimate with reduced times. In this work, the loss models are analyzed and developed to obtain useful thermodynamic and geometrical information, necessary for an optimization CFD simulation. The RTGD code according to the type of fuel, hydrogen, methane or kerosene, determines the optimal velocity triangles, on the mean line, to minimize the overall dimensions, the losses, the flow rate and the pressure ratio, in order to maximize turbine performance for liquid rocket engine application. The model developed have the objective to estimate the efficiency and optimization of the parameters related to it, and losses prediction. In conclusion, the results obtained through simplified models based on engineering methods able to predict the turbomachine main characteristics must not be neglected, because are fundamental nowadays for next analysis detailed  of viscous flow phenomena on the blade by CFD simulations, thanks to the modern computers computing power.","PeriodicalId":268187,"journal":{"name":"13th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics","volume":"320 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127627699","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}