Relevant bibliographies by topics / Compressor optimisation

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Compressor optimisation'

Author: Grafiati
Published: 19 February 2023

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Journal articles on the topic "Compressor optimisation"

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Beckers, Jarl, Diederik Coppitters, Ward De Paepe, Francesco Contino, Joeri Van Mierlo, and Björn Verrelst. "Multi-Fidelity Design Optimisation of a Solenoid-Driven Linear Compressor." Actuators 9, no. 2 (May 11, 2020): 38. http://dx.doi.org/10.3390/act9020038.

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Improved management and impermeability of refrigerants is a leading solution to reverse global warming. Therefore, crank-driven reciprocating refrigerator compressors are gradually replaced by more efficient, oil-free and hermetic linear compressors. However, the design and operation of an electromagnetic actuator, fitted on the compression requirements of a reciprocating linear compressor, received limited attention. Current research mainly focuses on the optimisation of short stroke linear compressors, while long stroke compressors benefit from higher isentropic and volumetric efficiencies. Moreover, designing such a system focuses mainly on the trade-off between number of copper windings and the current required, due to the large computational cost of performing a full geometric design optimisation based on a Finite Element Method. Therefore, in this paper, a computationally-efficient, multi-objective design optimisation for six geometric design parameters has been applied on a solenoid driven linear compressor with a stroke of 44.2 mm. The proposed multi-fidelity optimisation approach takes advantage of established models for actuator optimisation in mechatronic applications, combined with analytical equations established for a solenoid actuator to increase the overall computational efficiency. This paper consists of the multi-fidelity optimisation algorithm, the analytic model and Finite Element Method of a solenoid and the optimised designs obtained for optimised power and copper volume, which dominates the actuator cost. The optimisation results illustrate a trade-off between minimising the peak power and minimising the volume of copper windings. Considering this trade-off, an intermediate design is highlighted, which requires 33.3% less power, at the expense of an increased copper volume by 5.3% as opposed to the design achieving the minimum copper volume. Despite that the effect of the number of windings on the input current remains a dominant design characteristic, adapting the geometric parameters reduces the actuator power requirements significantly as well. Finally, the multi-fidelity optimisation algorithm achieves a 74% reduction in computational cost as opposed to an entire Finite Element Method optimisation. Future work focuses on a similar optimisation approach for a permanent magnet linear actuator.
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Goryachkin, E. S., V. N. Matveev, G. M. Popov, O. V. Baturin, and Yu D. Novikova. "Optimisation Method for Multistage Compressors." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 3 (138) (September 2021): 38–59. http://dx.doi.org/10.18698/0236-3941-2021-3-38-59.

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The paper presents an algorithm for seeking an optimal blade configuration for multistage axial-flow compressors. The primary tool behind the algorithm is 3D CFD simulation, augmented by commercial optimisation software. The core of the algorithm involves feeding an initial data vector to the parametric simulation module so as to form a "new" blade geometry, which is then transferred to 3D computational software. The results obtained are further processed in a program that implements the algorithm for seeking the optimum and forms a new input data vector to achieve the set goal. We present a method of parametrically simulation the blade shape, implemented in a software package, making it possible to describe the shape of the compressor blade profiles using a minimum number of variables and to automatically change the shape in the optimisation cycle. The algorithm developed allows the main parameters of compressor operation (efficiency, pressure ratio, air flow rate, etc.) to be improved by correcting the profile shape and relative position of the blades. The algorithm takes into account various possible constraints. We used the method developed to solve practical problems of optimising multistage axial compressors of gas turbine engines for various purposes, with the number of compressor stages ranging from 3 to 15. As a result, the efficiency, pressure ratio and stability margin of gas turbine engines were increased
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Cyklis, Piotr, and Przemysław Młynarczyk. "An innovative simulation method for the estimation of the nozzle pressure pulsation attenuation." Journal of Vibration and Control 23, no. 16 (December 13, 2015): 2690–703. http://dx.doi.org/10.1177/1077546315619534.

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Pressure pulsations in volumetric compressor manifolds have a high impact on compression power requirement and the reliability of manifold operation. These pulsations induce vibrations, noise, and in some cases, mechanical failure of piping or compressor valves. For pressure pulsation attenuation, different types of mufflers are applied using a design based upon the Helmholtz resonator approach. This design is particularly effective for constant revolution speed compressors. For contemporary applications of variable revolution speed compressors, other pressure pulsation attenuation methods are needed. It is known that different shapes of nozzles can attenuate pressure pulsations, however, they unfortunately increase the compressor power at the same time. The main criterion for nozzle selection is achieving pressure pulsation attenuation that is as high as possible whilst having the lowest possible effect on compressor power. In this paper, innovative computational fluid dynamics (CFD) simulation methodology is applied for the optimisation of nozzle shape and size. The steady flow simulation results correspond with compressor power consumption and impulse flow simulation results are related to pressure pulsation attenuation. This method has been validated on the basis of the experimental results for three different nozzle geometries. For experimental validation, nozzles have been mounted in the variable speed screw compressor discharge manifold.
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Xu, Cheng, and Ryoichi S. Amano. "Empirical Design Considerations for Industrial Centrifugal Compressors." International Journal of Rotating Machinery 2012 (2012): 1–15. http://dx.doi.org/10.1155/2012/184061.

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Computational Fluid Dynamics (CFD) has been extensively used in centrifugal compressor design. CFD provides further optimisation opportunities for the compressor design rather than designing the centrifugal compressor. The experience-based design process still plays an important role for new compressor developments. The wide variety of design subjects represents a very complex design world for centrifugal compressor designers. Therefore, some basic information for centrifugal design is still very important. The impeller is the key part of the centrifugal stage. Designing a highly efficiency impeller with a wide operation range can ensure overall stage design success. This paper provides some empirical information for designing industrial centrifugal compressors with a focus on the impeller. A ported shroud compressor basic design guideline is also discussed for improving the compressor range.
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Najjaran, Ahmad, Saleh Meibodi, Zhiwei Ma, Huashan Bao, and Tony Roskilly. "Experimentally Validated Modelling of an Oscillating Diaphragm Compressor for Chemisorption Energy Technology Applications." Energies 16, no. 1 (January 2, 2023): 489. http://dx.doi.org/10.3390/en16010489.

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This study presents a detailed dynamic modelling and generic simulation method of an oscillating diaphragm compressor for chemisorption energy technology applications. The geometric models of the compressor were developed step by step, including the diaphragm movement, compressor dimensions, chamber areas and volumes and so on. The detailed mathematical model representing the geometry and kinematics of the diaphragm compressor was combined with the motion equation, heat transfer equation and energy balance equation to complete the compressor modelling. This combination enables the novel compressor model to simultaneously handle the simulation of momentum and energy balance of the diagram compressor. Furthermore, an experimental apparatus was set up to investigate and validate the present modelling and the simulation method. The performance of the compressor was experimentally evaluated in terms of the mass flow rate of the compressor at various compression ratios. Additionally, the effects of different parameters such as the inlet temperature and ambient temperature at various compressor ratios on the compressor performance were investigated. It was found reducing the inlet temperature from 40 to 5 °C at a constant pressure results in the enhancement of the compressor flow rate up to 14.7%. The compressor model proposed and developed in this study is shown to be not only able to accurately deal with the complexity of the dynamic behaviour of the compressor working flow but is also capable of effectively representing diaphragm compressors for analysis and optimisation purposes in various applications.
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Basha, Nausheen, Ahmed Kovacevic, and Sham Rane. "Analysis of Oil-Injected Twin-Screw Compressor with Multiphase Flow Models." Designs 3, no. 4 (December 16, 2019): 54. http://dx.doi.org/10.3390/designs3040054.

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Growing demands for energy are motivating researchers to conduct in-depth analysis of positive displacement machines such as oil-injected screw compressors which are frequently used in industrial applications like refrigeration, oil and gas and air compression. The performance of these machines is strongly dependent on the oil injection. Optimisation of oil has a great energy saving potential by both increasing efficiency and reducing other impacts on the environment. Therefore, a three-dimensional, transient computational fluid dynamics study of oil injection in a twin-screw compressor is conducted in this research. This study explores pseudo single-fluid multiphase (SFM) models of VOF (Volume of Fluid) and a mixture for their capability to predict the performance of the oil-injected twin screw compressor and compare this with the experimental values. SCORGTM (Screw Compressor Rotor Grid Generator) is used to generate numerical grids for unstructured solver Fluent with the special interface developed to facilitate user defined nodal displacement (UDND). The performance predictions with both VOF and mixture models provide accurate values for power consumption and flow rates with low deviation between computational fluid dynamics (CFD) and the experiment at 6000 RPM and 7.0 bar discharge pressure. In addition, the study reflects on differences in predicting oil distribution with VOF, mixture and Eulerian-Eulerian two-fluid models. Overall, this study provides an insight into multiphase flow-modelling techniques available for oil-injected twin-screw compressors comprehensively accounting for the details of oil distribution in the compression chamber and integral compressor performance.
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Chen, Q. J., and K. T. Ooi. "Geometric Optimisation of a Coupled Vane Compressor." IOP Conference Series: Materials Science and Engineering 1180, no. 1 (September 1, 2021): 012028. http://dx.doi.org/10.1088/1757-899x/1180/1/012028.

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Gallar, Luis, Manuel Arias, Vassilios Pachidis, and Riti Singh. "Stochastic axial compressor variable geometry schedule optimisation." Aerospace Science and Technology 15, no. 5 (July 2011): 366–74. http://dx.doi.org/10.1016/j.ast.2010.08.010.

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Kumar, A., A. Kovacevic, S. A. Ponnusami, S. Patil, S. Abdan, and N. Asati. "On performance optimisation for oil-injected screw compressors using different evolutionary algorithms." IOP Conference Series: Materials Science and Engineering 1267, no. 1 (November 1, 2022): 012021. http://dx.doi.org/10.1088/1757-899x/1267/1/012021.

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Energy consumed for pressurizing air makes a significant proportion of total electrical energy consumption worldwide. To reduce the carbon footprint, it is necessary to have air compressors, which can operate efficiently over a large range of pressures and flow including full load and part load conditions. Several studies have been performed in this area including some which monitor the performance of a large number of compressors to develop strategies for their designs. This paper focuses on the design optimisation of geometrical and oil parameters of oil-injected screw compressors using different evolutionary algorithms such as genetic algorithm (GA), covariance matrix adaptation evolution strategy (CMA-ES), and so on. A comparison of the performance of these algorithms is presented. SCORG and GT-SUITE (commercial software tools for screw compressor thermodynamic simulations and optimisation) are used in the integrated model producing promising results. Feasibility of the optimum outcomes generated by these algorithms is critically evaluated from machine and system design point of view. Finally, in the context of optimisation presented here, the simplex converges fastest as compared to other algorithms. In the future study, the system design limitations are to be incorporated as constraints for the optimisation along with the objective to improve energy efficiency.
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Natig Abbasov, Natig Abbasov, and Eldar Umudov Eldar Umudov. "DESIGN OF CENTRIFUGAL COMPRESSOR IMPELLER FOR OPTIMAL EFFICIENCY." ETM - Equipment, Technologies, Materials 09, no. 01 (January 22, 2022): 121–30. http://dx.doi.org/10.36962/etm09012022121.

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A new methodology is proposed to use comprehensive up-to-date commercial software tools for Heat Exchanger Network (HEN) reliability modelling and optimisation. The idea behind this proposal is that to apply the combination of specific HEN optimisation and reliability software packages has several advantages over the commonly used approach. There is a variety of features that need to be taken into account to choose the right software tool. The HEN design has a significant impact on reliability issues and this should be considered. There are many related issues and features - the robustness, the type of welding, the increment of maximum mechanical resistance, the impact on manufacturing costs, reduction of lost opportunity costs caused by exchanger outages, troubleshooting of heating exchanger problems by operators etc. Fouling should be analysed as it has a significant impact on maintenance issues. Up to 30 % decrease of maintenance costs can be achieved annually by applying advanced reliability results and determining heat exchanger failure causes. These analyses include the investigation of failure causes, prediction of future probabilities of failures, cleaning planning and scheduling and the calculation of reliability and maintainability. Keywords: heat exchangers, modelling and optimisation, design of network, oil refinery, heat recovery systems.
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Dissertations / Theses on the topic "Compressor optimisation"

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Burman, Jörgen. "Design optimisation of aeroengine compressor blades." Licentiate thesis, Luleå, 2001. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-25824.

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Optimisation of multistage axial compressors is a time-demanding challenge in large need of effective methods. Traditionally, the design has been based on "trial-and-error" procedures, which count on the skills and experience of the designer to suggest redesigns that are likely to yield improvements. While design by "trial-and-error" usually yield acceptable solutions, automatic shape optimisation will assist in finding the optimal design and shorten the design cycle. This thesis considers issues that have to be solved before automatic shape optimisation of compressor blades can be performed, as well as a demonstration of the developed methods suitability for optimising 2D compressor blades. In paper A the geometry parameterisation of compressor blades is studied. Non-Uniform Rational B-Splines (NURBS) are used for the basic geometry description. The profile shape is then described in terms of traditional parameters, e.g. throat and maximum thickness, and an optimisation algorithm is used to adjust the NURBS parameters until the requested values of the traditional parameters are obtained. In paper B the presence of numerical noise in the objective function is investigated. The occurrence of numerical noise is related to the discretisation of the partial differential equations describing the flow. The truncation error in the flow equations together with the discontinuous change in the grid as the geometry is modified will produce a small amplitude "wave-pattern" imposed on the objective function. Two optimisation techniques, a response surface model and a gradient based method, are used to study how the solution is affected by the numerical noise when minimising the pressure drop in an axisymmetric contraction. In paper C the geometry definition using implicit design variables (paper A) is combined with a response surface model (paper B) to optimise the performance of a 2D compressor blade for a jet engine. The results show that the geometry modification strategy using implicit design variables can be used for optimisation. However, more experience is necessary before a definite conclusion can be drawn to claim that using these design parameters are superior to using the control points of the NURBS.
Godkänd; 2001; 20070314 (ysko)
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Rattanakit, Rattanachai. "Optimisation of the aluminium compressor impeller machining process." Thesis, University of Birmingham, 2013. http://etheses.bham.ac.uk//id/eprint/4044/.

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The research involved the optimisation of various machining operations for the manufacture of automotive turbocharger impellers. Phase 1 work comprised a capability study of the Al-Si C355 impeller machining process within Doncasters Sterling. The results highlighted that both C\(_p\) and C\(_{pk}\) values were generally above the automotive industry standard of 1.66 and that current processes were capable of producing parts to specification. Benchmark testing of TiN coated WC and PCD tooling against uncoated WC was undertaken in Phase 2 experiments. While the PCD tools showed significant improvement, the TiN coated tools were inferior in terms of thrust force, torque and workpiece surface roughness when compared against the uncoated WC tools. Phase 3 research evaluated the performance of advanced diamond like carbon (DLC) coatings against WC when blind-hole drilling C355 and reaming 6082-T6 aluminium alloys. Benefits in terms of extended tool life and reduced material adhesion/BUE were observed when drilling and reaming using the commercial Graphit-iC™ coating. The performance of CVD diamond coated and PCD tools were also assessed with the latter showing lower wear rates with negligible workpiece adhesion/BUE compared to WC in both drilling and reaming experiments. The former however failed catastrophically at high cutting speeds during drilling.
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Chan, Kuan Yoong. "Investigation and performance optimisation of multi compressor refrigeration system." Thesis, Brunel University, 2002. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.247504.

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Boyle, R. J. "Valve design optimisation for a 3-cylinder semi-hermetic reciprocating refrigeration compressor." Thesis, University of Strathclyde, 1985. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.381314.

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Jiang, Zongchuan. "Integration of CAD, CAM and computer aided inspection for the development of complex shaped products." Thesis, Glasgow Caledonian University, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.364776.

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Ahmed, Noukhez. "Performance evaluation and optimisation of vaneless diffuser of various shapes for a centrifugal compressor." Thesis, University of Huddersfield, 2018. http://eprints.hud.ac.uk/id/eprint/34684/.

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In recent years, diesel engines with reduced emissions and low fuel consumption have been developed worldwide for the purpose of environmental protection and energy conservation. Turbochargers are playing an important role in these modern engines by providing power boost to the engine. A turbocharger comprises of three major parts i.e. the turbine stage, the bearing housing and the compressor stage. Turbocharger designers are continuously seeking for compact stage designs, while maintaining the stage performance. A turbocharger’s compressor stage comprises of various parts i.e. inlet, impeller, diffuser and volute. The diffuser is an important section of the turbocharger compressor stage that plays a key role in increasing the isentropic efficiency of the stage. The diffuser converts the kinetic energy imparted to the flow by the impeller, into static pressure rise, which inturn increases the isentropic efficiency of the stage. The shape of a diffuser is conventionally simple in design. Modifications to the diffuser geometry can lead to higher efficiencies and compact designs of the compressor stage. The present study focuses on the use of advanced computational techniques, such as Computational Fluid Dynamics (CFD), to analyse the effects of diffuser modifications on the local flow features, and the global performance parameters. A baseline diffuser configuration, consisting of a parallel wall diffuser, is numerically analysed to establish the accuracy of CFD based predictions. Various diffusers’ geometrical configurations have been analysed in the present study, both qualitatively and quantitatively. These geometrical configurations cover a wide range, such as diverging, tilting and curving of the diffuser walls. These parametric investigations aid to improve the compressor stage performance and make it more compact. The first aim of the study is to quantify the increase in the stage performance by diverging the straight wall vaneless diffuser passage. This is carried out by diverging the shroud wall (i.e. increasing the outlet-to-inlet width ratio) and varying the location of the divergence point on the shroud wall. The results obtained depict that the effect of increasing the diffuser’s outlet-to-inlet width ratio is dominant in comparison with the location of the wall divergence point. Moreover, increase in diffuser’s outlet-to-inlet width ratio increases the downstream area ratio of the diffuser, causing the flow to separate and creating flow recirculation near the hub wall. This creates restriction to the flow and causes air blockage. Furthermore, shifting the wall divergence point towards the outlet of the diffuser relocates the flow separation point closer to the diffuser exit. The second aim of this study is to analyse the effects of tilted diffuser walls on the flow variables within the compressor stage of the turbocharger. Tilting diffuser walls provides an increased streamwise length to the flow. Furthermore, divergence is applied to the diffuser hub wall in order to increase the outlet-to-inlet width ratio. This makes the turbocharger compressor stage compact in design, while maintaining the stage performance, which is the current requirement of the automotive sector. Design of Experiments, using Taguchi method, has been incorporated in this study to define the scope of the numerical work. The results obtained show that the diffuser with both titled and diverged walls together, performs optimally as compared to the other configurations considered. The third aim of this study is to use curved diffuser walls in order to make the design more compact. Divergence to the hub wall is also applied to enhance the performance of the compressor stage. Various configurations of curvilinear diffuser walls have been considered for numerical analysis. The local flow field analysis has been carried out, quantifying the effects of the geometrical parameters on the stage performance. The results depict that a curved diffuser model reduces the losses within the diffuser passage, but there is negligible effect on the stage efficiency. However, when the divergence is applied to the hub wall of the curved diffuser, there is significant increase in the stage efficiency. Based on these investigations, a turbocharger’s compressor stage can be designed for a compact design and optimal efficiency.
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Clemen, Carsten. "Entwicklung eines Verfahrens für den dreidimensionalen Entwurf von Rotoren in Axialverdichtern." Doctoral thesis, Saechsische Landesbibliothek- Staats- und Universitaetsbibliothek Dresden, 2009. http://nbn-resolving.de/urn:nbn:de:bsz:14-qucosa-23436.

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Die heutige und zukünftige Entwicklung beim Entwurf von Axialverdichtern für die Anwendung in Flugzeugtriebwerken ist immer stärker davon geprägt, ein möglichst großes Druckverhältnis mit möglichst wenigen Stufen zu erzeugen. Ziel ist es, möglichst viel Leistung mit möglichst geringem Gewicht umzusetzen, um die Effizienz der Maschine weiter zu verbessern. Um dies zu erreichen, muss eine Erhöhung der Stufendruckverhältnisse und damit eine Erhöhung der Stufenbelastung in Kauf genommen werden. Die höhere Belastung hat jedoch einen Anstieg der Verluste aufgrund der stärker werdenden Sekundärströmungen zur Folge, und wirkt sich zunächst negativ auf die Stabilität und den Wirkungsgrad der Maschine aus. Diese negativen Effekte können nur durch eine Weiterentwicklung der Schaufelgeometrie kompensiert werden. Hierbei stoßen die derzeit benutzten Entwurfsmethoden jedoch an ihre Grenzen. Aus diesem Grund wurde ein neues Verfahren für den dreidimensionalen Entwurf von Rotoren in Axialverdichtern entwickelt. In dieser Arbeit wird dessen Entwicklung präsentiert. Das Verfahren umfasst die systematische Anwendung von Pfeilung und V-Stellung, sowie die dreidimensionale inverse Berechnung der radialen Skelettlinienverteilung. Um damit eine Verbesserung des Rotorwirkungsgrades zu erreichen, müssen vor allem die kritischen wand- bzw. spaltnahen Bereiche optimal an die Strömungsumgebung angepasst werden. Die vorliegende Arbeit beschreibt ausführlich die theoretischen Grundlagen der Rotorströmung und des Rotorentwurfs. Basierend darauf werden für die Umsetzung eines vollständigen dreidimensionalen Schaufelentwurfs zwei Panelverfahren zur Berechnung der dreidimensionalen jedoch reibungslosen Strömung, zur Lösung der Nachrechen- bzw. der Entwurfsaufgabe, entwickelt. Die Panelverfahren werden angewandt, um eine Methodik für den effektiven Einsatz von Pfeilung, V-Stellung und inverser Skelettlinienberechnung für den dreidimensionalen Rotorentwurf festzulegen. Die gewonnenen Erkenntnisse werden anschließend für den Entwurf eines hochbelasteten Rotors in einem einstufigen Niedergeschwindigkeitsverdichter nach dieser neuen Entwurfsmethodik genutzt. Anhand von Ergebnissen aus Rechnungen und Messungen für diesen Rotor wird die Wirksamkeit des Verfahrens demonstriert
The recent and future design of axial compressors for aero engines is strongly affected by the aim to generate a high pressure ratio with less stages to increase power and reduce weight to achieve an improved efficiency. This can only be achieved when the stage pressure ratio is raised which leads to increased stage loading. But the higher stage loading results in higher losses caused by stronger secondary flows. This has a negative effect on compressor stability and efficiency. To counteract the negative effects enhanced blade geometries are necessary. With the recently used design methods this is hardly to achieve. For that reason a new method for the three-dimensional design of rotors and stators in axial compressors has been developed. This report summarizes that work. The method accounts for the systematic application of sweep and dihedral as well as the three-dimensional inverse calculation of the camber-line distributions along blade height. To achieve improved efficiency the regions close to the end-walls and the tip and hub gap have to be adapted to the flow environment. The recent report described in detail the theoretical background of the compressor blade flow and compressor blade design. Based on that, two inviscid panel methods for the fully three-dimensional design of compressor blades are described. The panel methods are applied to define a methodology for the effective application of sweep, dihedral and inverse camber-line calculation in a three-dimensional blade design process. Afterwards the findings are used to design a highly-loaded single-stage low-speed research compressor rotor. The validity of the presented design method is proven with CFD and test results
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Bethel, David. "Optimisation of still image compression techniques." Thesis, University of Bath, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.242523.

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Handcock, Jason Anthony. "Video compression techniques and rate-distortion optimisation." Thesis, University of Bristol, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.326726.

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Ghisu, Tiziano. "Robust aerodynamic design optimisation of compression systems." Thesis, University of Cambridge, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.611418.

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Books on the topic "Compressor optimisation"

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Techniques avancées pour bases de données. Paris: Dunod, 1985.

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Book chapters on the topic "Compressor optimisation"

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Karger, Kai, and Dieter Bestle. "Parametric Blending and FE-Optimisation of a Compressor Blisk Test Case." In Computational Methods in Applied Sciences, 257–66. Cham: Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-11541-2_16.

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Olhofer, Markus, Bernhard Sendhoff, Toshiyuki Arima, and Toyotaka Sonoda. "Optimisation of a Stator Blade Used in a Transonic Compressor Cascade with Evolution Strategies." In Evolutionary Design and Manufacture, 45–54. London: Springer London, 2000. http://dx.doi.org/10.1007/978-1-4471-0519-0_4.

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Hoeltgen, Laurent, and Joachim Weickert. "Why Does Non-binary Mask Optimisation Work for Diffusion-Based Image Compression?" In Lecture Notes in Computer Science, 85–98. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-14612-6_7.

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Hämmerle-Uhl, Jutta, Michael Karnutsch, and Andreas Uhl. "Evolutionary Optimisation of JPEG2000 Part 2 Wavelet Packet Structures for Polar Iris Image Compression." In Progress in Pattern Recognition, Image Analysis, Computer Vision, and Applications, 391–98. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-41822-8_49.

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Itoh, Hayato, Atsushi Imiya, and Tomoya Sakai. "Relaxed Optimisation for Tensor Principal Component Analysis and Applications to Recognition, Compression and Retrieval of Volumetric Shapes." In Mathematics and Visualization, 165–200. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-91274-5_8.

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"Energy production and distribution Decision-making support for maintenance optimisation of natural gas compressor stations." In Safety and Reliability: Methodology and Applications, 1169–76. CRC Press, 2014. http://dx.doi.org/10.1201/b17399-162.

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Shirinov, A., and S. Oberbeck. "Optimisation of the high vacuum side channel pump." In 7th International Conference on Compressors and their Systems 2011, 81–92. Elsevier, 2011. http://dx.doi.org/10.1533/9780857095350.2.81.

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Rayneau-Kirkhope, D., Y. Mao, and R. Farr. "Optimisation of hierarchical structures for compression bearing applications." In Engineering Optimization 2014, 341–46. CRC Press, 2014. http://dx.doi.org/10.1201/b17488-61.

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Belič, Aleš, Igor Škrjanc, Damjana Zupančič-Božič, and Franc Vrečer. "Optimisation of compression parameters with Al-based mathematical models." In Formulation Tools for Pharmaceutical Development, 229–61. Elsevier, 2013. http://dx.doi.org/10.1533/9781908818508.229.

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Okhuahesogie, O. F., J. Stewart, M. J. W. Riley, F. Heyes, and P. Roach. "A 1-D analytical code for the design and multi-objective optimisation of high-pressure compressors within two-stage turbochargers for marine applications." In 11th International Conference on Turbochargers and Turbocharging, 125–35. Elsevier, 2014. http://dx.doi.org/10.1533/978081000342.125.

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Conference papers on the topic "Compressor optimisation"

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Cowan, Adrian. "Fleet-Wide Compressor Optimisation." In SPE Asia Pacific Oil & Gas Conference and Exhibition. Society of Petroleum Engineers, 2014. http://dx.doi.org/10.2118/171480-ms.

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John, Alistair, Guglielmo Vivarelli, Ning Qin, and Shahrokh Shahpar. "Using Feature-Based Mesh Adaptation to Improve the Adjoint Optimisation of Transonic Compressor Blades." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15351.

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Abstract The benefit of mesh adaptation to improve the optimisation process of turbomachinery components is here demonstrated for the first time. Mesh movement is used to automatically cluster and align the cells with significant flow features such as shocks, shock-induced separation and wakes for every geometry tested during a transonic compressor blade optimisation. Using mesh movement means that the same size grid is used while significantly improving the accuracy of the simulation and resulting adjoint gradients. A method is demonstrated to automatically carry out feature based mesh movement during every step of an adjoint optimisation process. Optimisations are carried out using the adaptation method and also using the starting mesh as a comparison. It is shown that (when tested on a very fine grid) the adaptation-optimisation process results in a better design, due to more accurate flow and gradient prediction throughout the optimisation process. A cost breakdown of the process is given to show that using adaptation during the optimisation process only increases the overall optimisation cost by a small amount, but results in greater efficiency of the final blade design.
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Gallar, L., M. Arias, V. Pachidis, and P. Pilidis. "Compressor Variable Geometry Schedule Optimisation Using Genetic Algorithms." In ASME Turbo Expo 2009: Power for Land, Sea, and Air. ASMEDC, 2009. http://dx.doi.org/10.1115/gt2009-60049.

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Variable geometry blade rows in axial compressors are devised to fulfil different requirements. Main objectives include their role as a “part speed crutch” to push the front stages out of surge at low spool speeds, modulation of the power output in industrial machines — given the fact that the spool needs to run at synchronous speed with the electric generator frequency — and they can also be re-staggered to attain a modified capacity (usually upflowed) of the same baseline compressor. The operating schedule of the variable vanes is typically obtained from expensive and time consuming performance rig tests in which a large number of possible combinations are compared. In principle, the final choice is dictated by the pursuit of high efficiency at high rotational speeds and increased surge margin at low speeds where large excursions away from the design point are expected. The aim of this work is to integrate a validated genetic algorithm optimiser within an industry proprietary mean line compressor performance prediction code to maximise the machine efficiency while keeping an adequate user-defined value of the surge margin. In so doing, an optimised variable geometry schedule is derived, together with a modified range of rotational speeds for each given operating point. Nevertheless, aware of the detrimental consequences to the whole engine performance that the new arrangement can cause, the whole engine response for the new settings has been investigated. In this regard and to a first order, the working line on the compressor map is considered unaffected by the setting of the variable vanes and the effect of the spool speed variation on the turbine operation is accounted for by a reduction in turbine efficiency proportional to any fall in the shaft speed. Results for a state of the art eight stage compressor show a marked improvement for the coupled compressor-turbine efficiency particularly at low spool speeds for a sensible value of the surge margin. Free from the surge margin constraint the efficiency is further increased at the expense of a hindered compressor operational stability. The work is intended to continue with the incorporation of bleeds and power off take in the calculations for the sake of a greater applicability of the tool.
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Ghisu, Tiziano, Massimiliano Molinari, Geoffrey Parks, William Dawes, Jerome Jarrett, and P. Clarkson. "Axial Compressor Intermediate Duct Design and Optimisation." In 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-1868.

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Voß, Christian, Marcel Aulich, Burak Kaplan, and Eberhard Nicke. "Automated Multiobjective Optimisation in Axial Compressor Blade Design." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-90420.

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This paper presents an automated multiobjective design methodology for the aerodynamic optimisation of turbomachinery blades. In this approach several operating-points of the compressor are considered and the flow-characteristics of the different flow-solutions are combined to one or more objective functions. The optimisation strategy is based on multiobjective asynchronous evolutionary algorithms (MOEA’S) which are accelerated using additive local neural networks and kriging procedures. Common operators: Mutation, Crossover and Differential-Evolution are used to create a new population. In addition to these common operators the optimisation runs temporarily on the response-surface created by the neural networks and/or kriging-processes respectively. Only the Pareto-optimal solutions obtained from this metamodel are evaluated using the numerical expensive flow-solver. Therefore, the response-surface is just a new operator that creates auspicious members. One of the main differences between the presented code to usual and traditional MOEA’S is the selection of parents. While traditional codes choose potential parents of a new population from the previous population, the current method selects parents from the database of all evaluated members. This approach allows the user to run the optimisation asynchronously and with a smaller size of population, treducing numerical costs, without influencing the diversity of the optimal solutions over the whole Pareto-front. This aspect is very important when evaluating very complex and/or discontinuous fronts.
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Cuciumita, Cleopatra, Alistair John, Ning Qin, and Shahrokh Shahpar. "Structurally Constrained Aerodynamic Adjoint Optimisation of Highly Loaded Compressor Blades." In ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gt2021-59717.

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Abstract Adjoint aerodynamic optimisation has recently gained increased popularity for turbomachinery applications due to the large number of parameters that can be used without incurring additional major computational costs. This work presents an adjoint based aero-structural optimisation method having efficiency as the objective function and maximum von Mises stress set as a constraint. The full optimisation loop was set up with free-form deformation for geometry parametrisation. A response surface was created beforehand for computing the maximum von Mises stress using a meshless method. A discrete adjoint approach was used to obtain the gradients of the objective function with respect to each design parameter, while the constraint gradients were computed using finite differences. A sequential least squares programming algorithm was used as the optimizer. Tests carried out on a highly loaded compressor blade showed that the method successfully increases the efficiency by more than 3% while maintaining the maximum stress under the imposed value. The results also showed that the constrained optimisation loses about 1% in potential efficiency gain compared to the same optimisation process without stress constraint. Overall, the work provides a methodology for conducting structurally constrained adjoint aerodynamic optimisation that can be applied for large number of design parameters while maintaining low computational costs. It also provides reference for constructing and selecting a response surface to be used in the optimisation process.
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Selvaraji, M., Sam P. Joseph, and N. Nirmal. "Optimization of Labyrinth Seal for Screw Compressor." In ASME/JSME 2007 Thermal Engineering Heat Transfer Summer Conference collocated with the ASME 2007 InterPACK Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/ht2007-32275.

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There is a growing demand for compressed air in the industry for various applications. Majority of industrial requirements is in line with screw compressor operating range. Design and construction of screw compressors are demanding tasks that require advanced calculations and theoretical knowledge. Clearances play a major role in the performance and reliability aspects of a screw compressor. Seals are provided in compressors to fit around rotor shafts in order to prevent the leakage of lubricating oil and working medium. However there is a small clearance between the seal and rotor shaft, which can cause potential leakage of the working medium. The performance of the compressor is directly related to the leakage rate through the seals. The labyrinth seal is a special type of seal, used in screw compressors and turbo-machinery for sealing purpose. Labyrinth seal is a non-contacting type seal that uses a tortuous path to minimize the gas leakage. The pressure drop occurs at each labyrinth tooth as the medium is squeezed between the labyrinth tooth and the rotor. The leakage through the seal is directly related to the labyrinth profile and also the clearance between the rotor and the labyrinth tooth. The present work is carried out to reduce the leakage through the labyrinth seal by optimising the tooth profile and operating clearances. Heat transfer analysis is carried out on the housing of the labyrinth seal to find out the boundary temperature of the seal. Also the heat transfer analysis on the labyrinth seal followed by Thermo-structural analysis is carried out to find out the accurate operating clearance of the seal. By using CFD as a tool, the optimisation is carried out on different design configurations of labyrinth seal by comparing the deviation in leakage rates. Effect of rotor speed, width of seal and pressure ratio on air leakage rate is also investigated. A set of labyrinth seals has been designed based on the above optimisation and tested in the compressor. The results have been compared with the CFD prediction.
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Schlaps, R. C., S. Shahpar, and V. Gümmer. "Automatic Three-Dimensional Optimisation of a Modern Tandem Compressor Vane." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-26762.

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In order to increase the performance of a modern gas turbine, compressors are required to provide higher pressure ratio and avoid incurring higher losses. The tandem aerofoil has the potential to achieve a higher blade loading in combination with lower losses compared to single vanes. The main reason for this is due to the fact that a new boundary layer is generated on the second blade surface and the turning can be achieved with smaller separation occurring. The lift split between the two vanes with respect to the overall turning is an important design choice. In this paper an automated three-dimensional optimisation of a highly loaded compressor stator is presented. For optimisation a novel methodology based on the Multipoint Approximation Method (MAM) is used. MAM makes use of an automatic design of experiments, response surface modelling and a trust region to represent the design space. The CFD solutions are obtained with the high-fidelity 3D Navier-Stokes solver HYDRA. In order to increase the stage performance the 3D shape of the tandem vane is modified changing both the front and rear aerofoils. Moreover the relative location of the two aerofoils is controlled modifying the axial and tangential relative positions. It is shown that the novel optimisation methodology is able to cope with a large number of design parameters and produce designs which performs better than its single vane counterpart in terms of efficiency and numerical stall margin. One of the key challenges in producing an automatic optimisation process has been the automatic generation of high-fidelity computational meshes. The multi block-structured, high-fidelity meshing tool PADRAM is enhanced to cope with the tandem blade topologies. The wakes of each aerofoil is properly resolved and the interaction and the mixing of the front aerofoil wake and the second tandem vane are adequately resolved.
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Belli, M., M. Stumbo, and D. Vinarova. "Thermodynamic Analysis and Optimisation of Mixed Fluid Turbine Power Plants." In ASME 1999 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/imece1999-0868.

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Abstract This paper discusses the thermodynamics of power cycles where steam or water are mixed with air to improve the performance of stationary gas turbine cycles. A general computer simulation program is presented; several components (compressor, combustor, turbine, recovery boiler, saturator, recuperator, inter-cooler, after-cooler) are modelled obtaining a transfer function between in-coming and out-coming fluids. Coupled with this simulation program, an optimisation is carried out using a decomposition strategy based on the second law of thermodynamic and a concept for costing the components of the cycles. A large number of decision variables can by optimised with enhanced convergence to an optimum. As results, a large number of simulations and optimisations are performed for three different plants (STIG, HAT and a cycle with water injection both in the compressor and in the combustor). A wide number of comparisons shows the difference between the cycles and the power level at which each plant gives the lowest exergoeconomic costs.
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Ranc, Lucas, Catherine Le Blanc, Ji-Ping Zou, Xavier Levecq, Frédéric Druon, and Dimitrios N. Papadopoulos. "Multispectral wavefront sensor for Petawatt class compressor alignment and optimisation." In Advanced Solid State Lasers. Washington, D.C.: OSA, 2019. http://dx.doi.org/10.1364/assl.2019.jm5a.30.

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