Analysis of a turbine rim seal cavity via 3D-CFD using conjugated heat transfer approach
|
|
- Brandon Day
- 5 years ago
- Views:
Transcription
1 Analysis of a turbine rim seal cavity via 3D-CFD using conjugated heat transfer approach ZERELLI, N. - Heat Transfer Department MTU Aero Engines, Munich, Germany University: ISAE Institut Supérieur de l Aéronautique et de l Espace Toulouse, France The presented work makes a contribution to the European research effort MAGPI (main annulus gas path interactions). It deals with the computational fluid dynamics analysis of a turbine rim seal cavity. It is investigated through 3D-CFD (computational fluid dynamics) methods via the conjugated heat transfer approach. The flow and thermal behavior, is analyzed for different cavity configurations, i.e. with varying geometry and coolant mass flow rates. The different designs are evaluated on the basis of a thermal efficiency. Nomenclature Abbreviations 3D = three-dimensional CFD = computational fluid dynamics CHT = conjugated heat transfer, this corresponds to the baseline configuration SST = shear stress transport MAGPI = main annulus gas path interactions Subscripts _da = MAGPI model with modified cooling inlet position _seg = MAGPI model with leakage slot integration Variables C w = non-dimensional mass flow rate m& = mass flow rate, kg/s µ = dynamic viscosity, Pa. s P = power, W R = gas constant, with R=287 J/kg/K r = radius, m T hot = turbine inlet total temperature = 443 K T cool = mass-averaged cooling flow temperature = 287 K T wall = area-weighted static temperature on the cavity walls, K T total = total temperature, K v = fluid velocity υ = kinematic viscosity, m²/s Non-dimensional Numbers Re Φ = Rotational Reynolds Number y+ = n+ = non-dimensional wall distance 1
2 I I. Introduction N modern aero-engines approximately twenty percent of the of the main annulus gas is bled off to feed secondary air systems such as cooling and sealing flows. Their optimization is considered one of the most promising techniques to increase global engine efficiency. The accurate prediction of the stator, rotor and disc metal temperature is crucial for the reliable layout of such air systems. Above this, it allows the accurate calculation of thermal dilatation, gap clearance evolution, thermal stresses and hence component lifetime. The present study deals with a turbine stator well, providing the clearance between rotor discs and stator support ring. A cooling flow is bled off constantly into this inter-disc cavity in order to prevent hot gas ingress from the main gas path air and, hence, extensive disc heating. The flow behavior and thermal properties of rim seal cavities are characterized by complex flows due to interaction with the main annulus gas. In order to investigate this region a 3D CFD model of a 2-stage turbine, including its stator well, the metal rotor discs and the stator foot, is generated. It corresponds to a turbine test rig at the University of Sussex, in terms of geometry and operating conditions. The conjugated-heat-transfer (CHT) approach takes into account the thermal interaction between the fluid domain and the solid components. The method is a very promising way to achieve physically more coherent modeling of heat transfer in cavities, where interactions between heat convection in the fluid domain and heat conduction in the solid domain are expected to be noteworthy. At the interface between main annulus gas and secondary air systems, where strong temperature gradients occur, a conjugated approach is essential: it allows a fully modeled heat exchange along the solid-fluid interface, rather than fixed boundary conditions, and thus yields more reliable results. The project 1 is carried out in the framework of the European research effort MAGPI (main annulus gas path interactions), where the present study focuses on the first work-package Effects of Cooling System/Main Annulus Gas Interaction Rotor Heat Transfer. The MAGPI cavity is studied in different configurations: the first is the baseline configuration, which corresponds to the standard test rig and for which data validation will be performed in the near future. In a second setup, the cooling flow inlet is displaced further upstream, towards the upstream cavity wall. Finally, another configuration, which corresponds to a possible test rig setup, introduces a leakage slot in the upstream cavity that accounts for actual leakage flows in a typical turbine. Each setup is simulated at two coolant mass flow rates such that different cavity ingress/egress situations are analyzed: with a cooling mass flow of 30g/s the cavity is not fully sealed and annulus gas enters, ingress occurs; with a cooling mass flow of 60g/s, the cavity is sealed against hot gas ingress. The analysis focuses on the flow patterns as well as the heat transfer in the cavity. A non-dimensional parameter is defined in order to evaluate the cooling efficiency for the different cavity designs. The study is classified as a CFD - pre-study, the measurements from the corresponding test rig data are scheduled to be available in the near future. The numerical data will then undergo a validation process, which will include the matching of the boundary conditions to the test conditions. Previous analyses of other turbine and compressor rim seal cavities at MTU - Heat Transfer Department have shown that the employed solver allows the reliable simulation of rim seal cavities: this comprises the flow behavior and the heat transfer characteristics. The simulation of a turbine rather than a compressor rim seal usually yields physically more coherent results since typical for compressor operation phenomena such as stall and surge do not occur. It is hence concluded that a numerical investigation of the present turbine rim seal cavity is reasonable and expected to show coherent results during the validation process. 1 Cf. Ref [1] 2
3 II. Baseline MAGPI cavity A. Test Rig & Operating point The stator well test rig is located at the Thermo-Fluid Mechanics Research Centre at the University of Sussex 2. It comprises a two-stage axial flow turbine enclosed in an annular channel through which the mainstream gas flows. Each turbine stage includes 39 nozzle guide vanes and 78 rotor blades with a twisted profile and hence fully threedimensional flow. Figure 1 summarizes the geometry and inlet boundary conditions of the test section at the design point, with a rotational speed of rpm (1113,73 rad/s). In most aero-engines the stator foot is equipped with a honeycomb structure, since it presents an efficient means to further increase the sealing quality: UZKAN and LIPSTEIN (1986) 3 have shown that ingestion of external flow into the stator well can be lowered significantly by using honeycombs on the stator foot. The honeycombs are not included on the rig. However, in order to account for the beneficial effect on the sealing performance of the labyrinth seal, the distance between the stator foot and the labyrinth teeth is lowered (from 0.4mm originally to 0.3mm) for both, the test rig and the CFD model. B. Mesh and Physical Model The numerical model (cf. Figure 2) consists of a fluid and solid domain. The first includes two stator rows as well as both rotors and the cavity; the latter is composed of the rotor discs, stator foot and drive arm. The interface between rotating and stationary parts is the stage-interface frame-change/mixing model and performs circumferential averaging. The turbine model is axial-symmetric, strong circumferential variations are not expected since the combustion chamber is not part of the test rig. 2 Cf. Ref. [2] 3 Cf. Ref. [3] 3
4 The meshes of the fluid domain are based on multi-block structured grids with hexagonal-volumes and have an overall size of nearly 3 million cells. It is refined in the regions of strong adverse pressure gradients, such as the cavity walls and the labyrinth region. The solid mesh is considerably coarser since only the energy conservation equation is solved in that region. With respect to the materials used for the solid region, the exact material data of the test rig is included in the numerical model: the stationary parts (nozzle guide vanes and the stator shrouds) are made of stainless steel, Type 304; the rotating parts (rotor discs and the drive arm) are made of titanium alloy, TiAl6V4. The Ansys-CFX solver is used for the simulations, all run in steady state. The physical model of the fluid domain is the total energy heat transfer model including the viscous term: it corresponds to a coupled solver, modeling the transport of enthalpy including kinetic effects. The heat transfer modes taken into account in the fluid domain are conduction, convection, turbulent mixing and viscous work. The turbulence model chosen for all the simulations is SST (shear stress transport) with automatic near-wall treatment: it is well adapted for meshes with important grid spacing variations and a flow field characterized by adverse pressure gradient conditions 4. The solid domain is solved via the Thermal Energy model, which accounts for heat conduction. Radiation is negligible and hence not included. C. Overview of cavity physics The most important effects associated to the flow behavior inside a cavity are presented briefly. Figure 3 shows the main types of flow that are typically identified in rim seal cavities. In a turbine the pressure decreases across a stage, and hence there is an important pressure differential between the upstream trench of the cavity and its downstream trench. This constantly entrains a mass flow across the labyrinth which depends on the magnitude of the pressure difference between the upstream and downstream chamber and on the seal gap height (i.e. the distance between labyrinth teeth and stator foot). Hot gas from the main gas path therefore ingresses the upstream chamber predominantly and exits through the downstream trench. This can only be prevented by providing a sealing mass flow in the upstream chamber. The design criterion for engines is to inject a higher mass flow than would be required to reach exact sealing. Apart from the hot gas ingestion and the coolant injection, a third zone is distinguished in the cavity: the core zone forms due to the so-called pumping effect of the rotor disc. The fluid is entrained by the disc and centrifugally accelerated. The flow over the disc becomes turbulent for rotational Reynolds Numbers above 3x10 5, where Re Φ describes the ratio of kinetic to viscous forces in a rotating environment. In the laminar flow regime, the nondimensional entrained mass flow rate amounts 5 : (1) 4 Cf. Ref. [6] 5 Cf. Ref. [4] 4
5 Where the rotational Reynolds-Number is defined as follows: The contribution of each type of zone (ingress/cooling/core flow) to the flow field in the upstream cavity, depends on the operating point. The shaft rotating speed defines the pressure loss across a stage - hence the pressure difference between upstream and downstream cavity chamber. The cooling mass flow rate is the second parameter and acts directly on the amount of hot gas ingress. (2) D. Results a) Flow field and mass flow rates The flow patterns and total pressure profiles of the MAGPI cavity are shown in Figure 4. It is found that the main recirculation zones form as expected: - at 30g/s cooling flow injection nearly 20g/s of hot main gas path air enter the cavity. The central flow in the upstream cavity is the air that is pumped by the rotor-1, where the fluid is accelerated along the disc. The cooling flow injected at the cavity bottom can clearly be distinguished in the flow pattern which indicates low mixing between the core zone and the coolant. The downstream cavity is dominated entirely by the pumped flow which entrains a single recirculation zone. - at 60g/s cooling flow injection the cavity is definitely sealed, in fact 10g/s exit the upstream cavity. Hence, there are only two important zones to be identified in the upstream chamber: the pumped flow and the coolant recirculation. Similarly to the 30g/s case the mixing between those zones is rather poor and the flow situation in the downstream chamber remains unchanged. b) Temperature distribution The study of the thermal behavior reveals that the previous assessment of the flow patterns is confirmed: the mixing is poor and the injected cooling flow circulates in the lower chamber. This is due to the pressure differential across the labyrinth which forces the coolant to either pass through the labyrinth immediately or remain close to the cavity bottom, the exception being the coolant close to the rotor disc. The centrifugal acceleration forces a certain amount of coolant to the upper cavity part, which is observed for both cooling mass flow rates. 5
6 Another important finding is that a significant amount of thermal energy is transmitted from the main gas path into the cavity through the metal components. This is observed very clearly at 60g/s cooling flow, since no hot gas ingress occurs and thermal energy transport through the metal is the only heat source. The heat conducted through the metal components has an important impact on the temperature in both chambers, where the upstream side is affected predominantly. The thermal energy is transmitted from the upstream chamber through the stator foot to the cooler downstream chamber at both coolant mass flow rates. The cavity s thermal behavior is mainly triggered by the presence of the pump effect and the associated recirculation zones. Natural convection is negligible compared to the centrifugal effects. In conclusion, the MAGPI model reacts as expected, and the results are physically coherent. III. Cavity with displaced cooling-inlet A. Model Definition In the baseline MAGPI cavity configuration, the axis of the cooling flow inlet tube is at 18mm distance to the upstream cavity wall. The tube diameter is 3mm at the intersection of cavity floor and inlet tube. In the modified configuration, the inlet of the cooling flow is displaced by 8mm (axis-baseline to axis-modified) which results in a distance between the displaced cooling flow axis and the upstream cavity wall of nearly 4mm (cf. Figure 6). This design modification is studied since a stronger reaction of the coolant to the centrifugal pick-up is considered to be beneficial to the overall heat transfer characteristics. The flow injection angle remains the same as in the previous configuration (with the coolant entering the cavity normal to the cavity floor and with the momentum of the inlet nozzle, rotating at operating speed). B. Results a) Flow field and mass flow rates The velocity profiles at 30g/s and 60g/s change markedly (cf. Figure 7 and Figure 8). The coolant which enters the cavity at proximity to the cavity wall immediately enters the region of pumped flow. Through the centrifugal acceleration the flow is propelled further along the disc and reaches a maximum velocity of 40m/s at 30g/s (compared to 20m/s in the baseline MAGPI-model) and 75m/s at 60g/s (compared to 40m/s in the baseline MAGPImodel). 6
7 Another important aspect of the modified flow field is the fact that, independently of the cooling mass flow rate, there are no longer two separate zones distinguishing the core flow and the coolant flow. Both zones merge into each other, creating one main vortex in the upstream cavity. The downstream cavity chamber remains nearly unaffected. The overall increase in velocity has a significant effect on the ingress/egress situation of the cavity: the total pressure in the stationary frame is higher due to the acceleration of the coolant along the rotor1-disc. This in turn decreases the pressure differential between the main gas path and the upstream trench and hence the pressure differential between the chambers, as can be seen in Figure 9-LH. Therefore, less leakage flow passes through the labyrinth, thus less hot gas ingestion occurs at the upstream trench (cf. Figure 9 RH). b) Temperature distribution & Wall heat flux The modified flow paths in the upstream cavity strongly influence the total temperature distribution (cf. Figure 10). Immediate mixture between the cooling and core flow occurs throughout the entire upstream chamber, other than in the standard configuration where two separate zones remain. This causes the average fluid total temperature to drop significantly, particularly in the upstream cavity. This is due to two effects: first, with the displaced cooling inlet the majority of the coolant remains in the upstream chamber rather than directly passing through the labyrinth. Secondly, the total pressure increase in the upstream chamber results in a lower pressure difference across the labyrinth, which causes less hot gas to be ingested. 7
8 In the 60g/s simulation (cf. Figure 11), the fluid temperature drop is more equilibrated between upstream and downstream chamber. In this configuration the cavity is sealed, no hot gas ingestion occurs, and the coolant fills the upstream chamber entirely and also passes through the labyrinth causing the temperature to drop in both chambers significantly. The modification of the drive-arm cooling inlet position implies fundamental changes in the flow field which have a very beneficial effect on hot gas ingestion. Both, fluid and solid temperatures, decrease significantly: at lower mass flow rates the impact on the fluid temperature is concentrated in the upstream chamber, where at higher cooling mass flow injection the fluid temperature reduction is more equilibrated between both chambers. In the solid components the impact of the varying mass flow rate is less noticeable. A general design aim for such cavities can thus be extracted as follows: in order to benefit from the pump effect to the maximum extent it is most desirable to position the cooling flow inlet as close as possible to the rotor disc. IV. Cavity with integrated leakage slot A. Model Definition In the baseline MAGPI cavity configuration, no purge flow enters the cavity. This corresponds to one of several configurations in which the tests will be run on the actual turbine test rig. In the upstream cavity, however, so-called leakage slots can be opened which results in a small flow from the back-plate. Hence, with the integration of a leakage slot, additional test configurations are modeled. The geometry of the segmented slots, i.e. one vertical slot per sector, is illustrated in Figure 12. The slot length is 6mm, the slot height is 12mm and the width is 0.3mm. The boundary condition assigned to the new segmented slot part is an inlet with a specific mass flow rate at 300K. The mass flow rate entering the domain corresponds to a quarter of the cooling flow. B. Results The analysis of the flow patterns and fluid temperatures needs to be performed carefully, since two effects are overlapping: first, the cool second air inlet in the upstream cavity presents an additional heat sink. Secondly, integrating the leakage flow adds an airflow to the overall injected mass flow which automatically reduces the amount of hot gas ingestion when compared to the baseline model. 8
9 a) Flow field and mass flow rates The velocity profiles change slightly in the 30g/s simulation. Very locally, where the 7.5g/s purge flow enters, the velocity increases (cf. Figure 13Erreur! Source du renvoi introuvable.). This small zone does not present an important obstruction to the main flow paths in the cavity and is accorded an immediate centrifugal acceleration along the rotor1-disc. Generally, the flow paths are not affected compared to the baseline cavity; however, kinetic energy of the core zone is lost partially as the leakage flow enters normal direction the cavity wall. As expected, no effect is noticed in the downstream chamber. The velocity profiles at 60g/s cooling mass flow are shown in Figure 14. It is observed that the purge-flow bubble, forming in proximity to the segmented slot, eventually fully merges with the core zone. This influences the interaction between the core zone and the cooling flow recirculation, which is easily observed through the velocity vectors at the interface of the two zones. Their exchange increases the radial momentum of the core zone, entrained by the pump-effect. This momentum is conserved and, other than in the 30g/s case, results in an overall velocity increase of the core zone also near the stator foot. b) Temperature distribution The thermal analysis of the MAGPI_seg model shows that, even at small mass flow rate, the influence of the purge flow on the fluid total temperature is noteworthy in the upstream chamber. This occurs mainly near the cavity wall, the average fluid total temperature reduction amounts 3.7K. However, it needs to be taken into consideration that the leakage slot air enters the cavity at cooling flow temperature. 9
10 At 60g/s the higher mass flow rate of cool air dominates the overall cavity temperature. Better mixing between the zones core flow and coolant flow also has an important impact on the fluid total temperature. The injection of additional coolant presents a second zone of cooling flow and therefore lowers the fluid temperature. V. Thermal efficiency In order to compare the cavity configurations on an objective basis, a thermal efficiency is defined. The cooling performance is evaluated for five surfaces defining the cavity walls: two rotating walls, the labyrinth region and two stationary walls. The inlet and cooling flow temperatures serve as a reference and the efficiency is defined as described in equation (3). T hot = turbine inlet total temperature = 443 K T cool = mass-averaged cooling flow temperature = 287 K T wall = area-weighted static temperature on the cavity walls The results for both mass flow rates are shown in Figure 18. It is found that particularly for the sections of highest temperature, i.e. rotor 1 disc (Rot1) and the stator upstream side (Sta1), the modification of the cooling inlet position is noteworthy. When comparing the MAGPI_seg model with the other configurations it needs to be taken into account that the absolute amount of injected flow is higher than in the other configurations; the effect on the thermal efficiency is most noticeably in the 60g/s case. (3) In conclusion, the modification of the cooling flow inlet position shows the maximum rise in performance: not only does it yield the highest increase in thermal efficiency, but it also has an advantageous effect on the hot gas ingestion. 10
11 VI. Conclusion A general conclusion is derived from the sensitivity study concerning geometry modifications to the baseline cavity: any measure which increases the level of mixing of the two main zones, i.e. core and coolant flow, is to be encouraged. It allows the best-possible use of the very costly cooling flow and therefore increases the performance of the cooling system. The two design modifications studied in this project have proven to act as motors entraining the mixture, where the cooling flow inlet displacement has the maximum effect. As explained previously, this is due to the most efficient exploitation of the pump effect, a natural source of kinetic energy. In terms of future exploitability of the numerical results, the simulations have yielded physically coherent results which can be used for a validation study. The use of the conjugated heat transfer approach has shown to not only be possible, even for a rather large CFD model, but very promising when it comes to investigating the details of the fluid temperature in the cavity. Acknowledgments The author thanks the Heat Transfer Department of MTU AeroEngines in Munich, where this work was conducted, for the continuous support and gratefully acknowledges the permission for publication. Reports, Theses, and Individual Papers References 1 ZERELLI, N. Fluid Flow and Heat Transfer in Rim Seal Cavities a conjugated 3D-CFD study (2008) Master of Science Thesis: Germany, Munich ² STEFANIS, V. Annual Report: Turbine Stator Well Heat Transfer (2003) University of Sussex, Thermo-Fluid Mechanics Research Centre ³ UZKAN, T.; LIPSTEIN, N.J. Effects of honeycomb-shaped walls on the flow regime between a rotating disk and a stationary Wall (1986) ASME International Gas Turbine Conference & Exhibit: Germany, Düsseldorf 4 OWEN J.M.; ROGERS R.H. Flow and Heat Transfer in Rotating-Disc Systems Volume 1 Rotor-Stator Systems (1989) : Taunton, England: Research Studies Press Ltd. 5 MAGPI-Documentation: MAGPI, Part B, 12 July Validation Report: CFX-VAL10/0602: MENTER, F.R. (2002) 11
APPLICATION OF STAR-CCM+ TO TURBOCHARGER MODELING AT BORGWARNER TURBO SYSTEMS
APPLICATION OF STAR-CCM+ TO TURBOCHARGER MODELING AT BORGWARNER TURBO SYSTEMS BorgWarner: David Grabowska 9th November 2010 CD-adapco: Dean Palfreyman Bob Reynolds Introduction This presentation will focus
More informationTurbostroje 2015 Návrh spojení vysokotlaké a nízkotlaké turbíny. Turbomachinery 2015, Design of HP and LP turbine connection
Turbostroje 2015 Turbostroje 2015 Návrh spojení vysokotlaké a nízkotlaké turbíny Turbomachinery 2015, Design of HP and LP turbine connection J. Hrabovský 1, J. Klíma 2, V. Prokop 3, M. Komárek 4 Abstract:
More informationEffect of Stator Shape on the Performance of Torque Converter
16 th International Conference on AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 16 May 26-28, 2015, E-Mail: asat@mtc.edu.eg Military Technical College, Kobry Elkobbah, Cairo, Egypt Tel : +(202) 24025292
More informationStudy on Flow Fields in Variable Area Nozzles for Radial Turbines
Vol. 4 No. 2 August 27 Study on Fields in Variable Area Nozzles for Radial Turbines TAMAKI Hideaki : Doctor of Engineering, P. E. Jp, Manager, Turbo Machinery Department, Product Development Center, Corporate
More informationDesign and Test of Transonic Compressor Rotor with Tandem Cascade
Proceedings of the International Gas Turbine Congress 2003 Tokyo November 2-7, 2003 IGTC2003Tokyo TS-108 Design and Test of Transonic Compressor Rotor with Tandem Cascade Yusuke SAKAI, Akinori MATSUOKA,
More informationEngineering Success by Application of STAR-CCM+ for Modern Gas Turbine Design
STAR Japanese Conference 2013 December 3, Yokohama, Japan Engineering Success by Application of STAR-CCM+ for Modern Gas Turbine Design Norbert Moritz, Karsten Kusterer, René Braun, Anis Haj Ayed B&B-AGEMA
More informationComputational flow field analysis of a Vertical Axis Wind Turbine
Computational flow field analysis of a Vertical Axis Wind Turbine G.Colley 1, R.Mishra 2, H.V.Rao 3 and R.Woolhead 4 1 Department of Engineering & Technology Huddersfield University Queensgate Huddersfield,
More informationAnalysis of Air Flow and Heat Transfer in Ventilated Disc Brake Rotor with Diamond Pillars
International Journal of Current Engineering and Technology E-ISSN 2277 4106, P-ISSN 2347 5161 2016 INPRESSCO, All Rights Reserved Available at http://inpressco.com/category/ijcet Research Article Analysis
More informationPlasma Assisted Combustion in Complex Flow Environments
High Fidelity Modeling and Simulation of Plasma Assisted Combustion in Complex Flow Environments Vigor Yang Daniel Guggenheim School of Aerospace Engineering Georgia Institute of Technology Atlanta, Georgia
More informationCFD Investigation of Influence of Tube Bundle Cross-Section over Pressure Drop and Heat Transfer Rate
CFD Investigation of Influence of Tube Bundle Cross-Section over Pressure Drop and Heat Transfer Rate Sandeep M, U Sathishkumar Abstract In this paper, a study of different cross section bundle arrangements
More informationMarc ZELLAT, Driss ABOURI and Stefano DURANTI CD-adapco
17 th International Multidimensional Engine User s Meeting at the SAE Congress 2007,April,15,2007 Detroit, MI RECENT ADVANCES IN DIESEL COMBUSTION MODELING: THE ECFM- CLEH COMBUSTION MODEL: A NEW CAPABILITY
More informationCOMPUTATIONAL FLOW MODEL OF WESTFALL'S 2900 MIXER TO BE USED BY CNRL FOR BITUMEN VISCOSITY CONTROL Report R0. By Kimbal A.
COMPUTATIONAL FLOW MODEL OF WESTFALL'S 2900 MIXER TO BE USED BY CNRL FOR BITUMEN VISCOSITY CONTROL Report 412509-1R0 By Kimbal A. Hall, PE Submitted to: WESTFALL MANUFACTURING COMPANY May 2012 ALDEN RESEARCH
More informationChapter 7: Thermal Study of Transmission Gearbox
Chapter 7: Thermal Study of Transmission Gearbox 7.1 Introduction The main objective of this chapter is to investigate the performance of automobile transmission gearbox under the influence of load, rotational
More informationAN INVESTIGATION IN RADIAL GAP AIR-RIDING SEALS FOR AERO-ENGINES
AN INVESTIGATION IN RADIAL GAP AIR-RIDING SEALS FOR AERO-ENGINES Shubham Kumar, Seamus Garvey and Hervé Morvan The University of Nottingham, Nottingham, United Kingdom E-Mail: Shubham.Kumar@nottingham.ac.uk
More informationNovember 8, 2018 GAS TURBINE ENGINE SECONDARY FLOW SYSTEMS
November 8, 2018 GAS TURBINE ENGINE SECONDARY FLOW SYSTEMS Agenda 1 What is Secondary Flow? Purpose for the Secondary Flow Systems Chargeable Vs Nonchargeable Flows Seals Selection and Leakage Effects
More informationChapter 6 Predictions of Platform Adiabatic Effectiveness
Chapter 6 Predictions of Platform Adiabatic Effectiveness The turbine platform is relied upon to deal with significant amounts of thermal and mechanical stress as the blade rotates at relatively high rotational
More informationEngineering Success by Application of Star-CCM+ for Modern Gas Turbine Design
March 18 th, 2014, Vienna, Austria STAR Global Conference Engineering Success by Application of Star-CCM+ for Modern Gas Turbine Design Karsten Kusterer B&B-AGEMA GmbH, Aachen, Germany Ryozo Tanaka Kawasaki
More informationFLOW AND HEAT TRANSFER ENHANCEMENT AROUND STAGGERED TUBES USING RECTANGULAR VORTEX GENERATORS
FLOW AND HEAT TRANSFER ENHANCEMENT AROUND STAGGERED TUBES USING RECTANGULAR VORTEX GENERATORS Prabowo, Melvin Emil S., Nanang R. and Rizki Anggiansyah Department of Mechanical Engineering, ITS Surabaya,
More informationEffects of Dilution Flow Balance and Double-wall Liner on NOx Emission in Aircraft Gas Turbine Engine Combustors
Effects of Dilution Flow Balance and Double-wall Liner on NOx Emission in Aircraft Gas Turbine Engine Combustors 9 HIDEKI MORIAI *1 Environmental regulations on aircraft, including NOx emissions, have
More informationFoundations of Thermodynamics and Chemistry. 1 Introduction Preface Model-Building Simulation... 5 References...
Contents Part I Foundations of Thermodynamics and Chemistry 1 Introduction... 3 1.1 Preface.... 3 1.2 Model-Building... 3 1.3 Simulation... 5 References..... 8 2 Reciprocating Engines... 9 2.1 Energy Conversion...
More informationCFD ANALYSIS ON LOUVERED FIN
CFD ANALYSIS ON LOUVERED FIN P.Prasad 1, L.S.V Prasad 2 1Student, M. Tech Thermal Engineering, Andhra University, Visakhapatnam, India 2Professor, Dept. of Mechanical Engineering, Andhra University, Visakhapatnam,
More informationInvestigation of Radiators Size, Orientation of Sub Cooled Section and Fan Position on Twin Fan Cooling Packby 1D Simulation
Investigation of Radiators Size, Orientation of Sub Cooled Section and Fan Position on Twin Fan Cooling Packby 1D Simulation Neelakandan K¹, Goutham Sagar M², Ajay Virmalwar³ Abstract: A study plan to
More informationTHERMAL MANAGEMENT OF AIRCRAFT BRAKING SYSTEM
ABSTRACT THERMAL MANAGEMENT OF AIRCRAFT BRAKING SYSTEM Shivakumar B B 1, Ganga Reddy C 2 and Jayasimha P 3 1,2,3 HCL Technologies Limited, Bangalore, Karnataka, 560106, (India) This paper presents the
More informationNumerical simulation of detonation inception in Hydrogen / air mixtures
Numerical simulation of detonation inception in Hydrogen / air mixtures Ionut PORUMBEL COMOTI Non CO2 Technology Workshop, Berlin, Germany, 08.03.2017 09.03.2017 Introduction Objective: Development of
More informationInvestigation of converging slot-hole geometry for film cooling of gas turbine blades
Project Report 2010 MVK160 Heat and Mass Transport May 12, 2010, Lund, Sweden Investigation of converging slot-hole geometry for film cooling of gas turbine blades Tobias Pihlstrand Dept. of Energy Sciences,
More informationMarc ZELLAT, Driss ABOURI, Thierry CONTE and Riyad HECHAICHI CD-adapco
16 th International Multidimensional Engine User s Meeting at the SAE Congress 2006,April,06,2006 Detroit, MI RECENT ADVANCES IN SI ENGINE MODELING: A NEW MODEL FOR SPARK AND KNOCK USING A DETAILED CHEMISTRY
More informationTHE EFFECT OF BLADE LEAN ON AN AXIAL TURBINE STATOR FLOW HAVING VARIOUS HUB TIP RATIOS. Dr. Edward M Bennett
THE EFFECT OF BLADE LEAN ON AN AXIAL TURBINE STATOR FLOW HAVING VARIOUS HUB TIP RATIOS Dr. Edward M Bennett ABSTRACT The effect of simple lean on an axial turbine stator was examined using a threedimensional
More informationComparison of Swirl, Turbulence Generating Devices in Compression ignition Engine
Available online atwww.scholarsresearchlibrary.com Archives of Applied Science Research, 2016, 8 (7):31-40 (http://scholarsresearchlibrary.com/archive.html) ISSN 0975-508X CODEN (USA) AASRC9 Comparison
More informationCONJUGATE HEAT TRANSFER ANALYSIS OF HELICAL COIL HEAT EXCHANGE USING CFD
CONJUGATE HEAT TRANSFER ANALYSIS OF HELICAL COIL HEAT EXCHANGE USING CFD Rudragouda R Patil 1, V Santosh Kumar 2, R Harish 3, Santosh S Ghorpade 4 1,3,4 Assistant Professor, Mechanical Department, Jayamukhi
More informationNUMERICAL INVESTIGATION OF PISTON COOLING USING SINGLE CIRCULAR OIL JET IMPINGEMENT
NUMERICAL INVESTIGATION OF PISTON COOLING USING SINGLE CIRCULAR OIL JET IMPINGEMENT BALAKRISHNAN RAJU, CFD ANALYSIS ENGINEER, TATA CONSULTANCY SERVICES LTD., BANGALORE ABSTRACT Thermal loading of piston
More informationScroll Compressor Oil Pump Analysis
IOP Conference Series: Materials Science and Engineering PAPER OPEN ACCESS Scroll Compressor Oil Pump Analysis To cite this article: S Branch 2015 IOP Conf. Ser.: Mater. Sci. Eng. 90 012033 View the article
More informationEFFECT OF SURFACE ROUGHNESS ON PERFORMANCE OF WIND TURBINE
Chapter-5 EFFECT OF SURFACE ROUGHNESS ON PERFORMANCE OF WIND TURBINE 5.1 Introduction The development of modern airfoil, for their use in wind turbines was initiated in the year 1980. The requirements
More informationCorso di Motori Aeronautici
Corso di Motori Aeronautici Mauro Valorani Laurea Magistrale in Ingegneria Aeronautica (MAER) Sapienza, Università di Roma Anno Accademico 2011-12 Sett. 13: Conclusioni 1 FP7 Aero Engine Scenario ERS Strategy
More informationDEVELOPMENT OF TIP CLEARANCE FLOW DOWNSTREAM OF A ROTOR BLADE WITH COOLANT INJECTION FROM A TIP TRENCH
DEVELOPMENT OF TIP CLEARANCE FLOW DOWNSTREAM OF A ROTOR BLADE WITH COOLANT INJECTION FROM A TIP TRENCH Debashis Dey Department of Aerospace Engineering The Pennsylvania State University University Park,
More informationTHE INSTITUTE OF PAPER CHEMISTRY, APPLETON, WISCONSIN
THE INSTITUTE OF PAPER CHEMISTRY, APPLETON, WISCONSIN HIGH SPEED PHOTOGRAPHY OF THE DISK REFINING PROCESS Project 2698 Report 5 To The Technical Division Fourdrinier Kraft Board Group of the American Paper
More informationNUMERICAL INVESTIGATION OF FLUID FLOW AND HEAT TRANSFER CHARACTERISTICS ON THE AERODYNAMICS OF VENTILATED DISC BRAKE ROTOR USING CFD
THERMAL SCIENCE: Year 2014, Vol. 18, No. 2, pp. 667-675 667 NUMERICAL INVESTIGATION OF FLUID FLOW AND HEAT TRANSFER CHARACTERISTICS ON THE AERODYNAMICS OF VENTILATED DISC BRAKE ROTOR USING CFD by Thundil
More informationMETHANE/OXYGEN LASER IGNITION IN AN EXPERIMENTAL ROCKET COMBUSTION CHAMBER: IMPACT OF MIXING AND IGNITION POSITION
SP2016_3124927 METHANE/OXYGEN LASER IGNITION IN AN EXPERIMENTAL ROCKET COMBUSTION CHAMBER: IMPACT OF MIXING AND IGNITION POSITION Michael Wohlhüter, Victor P. Zhukov, Michael Börner Institute of Space
More informationPulsation dampers for combustion engines
ICLASS 2012, 12 th Triennial International Conference on Liquid Atomization and Spray Systems, Heidelberg, Germany, September 2-6, 2012 Pulsation dampers for combustion engines F.Durst, V. Madila, A.Handtmann,
More informationNumerical Study on the Flow Characteristics of a Solenoid Valve for Industrial Applications
Numerical Study on the Flow Characteristics of a Solenoid Valve for Industrial Applications TAEWOO KIM 1, SULMIN YANG 2, SANGMO KANG 3 1,2,4 Mechanical Engineering Dong-A University 840 Hadan 2 Dong, Saha-Gu,
More informationOptimization of Packed Tower Inlet Design by CFD Analysis. Dana Laird Koch-Glitsch, Inc.
39e Optimization of Packed Tower Inlet Design by CFD Analysis Dana Laird Koch-Glitsch, Inc. Brian Albert ExxonMobil Research and Engineering (formerly with Koch-Glitsch, Inc.) Carol Schnepper John Zink
More informationEffect of concave plug shape of a control valve on the fluid flow characteristics using computational fluid dynamics
Effect of concave plug shape of a control valve on the fluid flow characteristics using computational fluid dynamics Yasser Abdel Mohsen, Ashraf Sharara, Basiouny Elsouhily, Hassan Elgamal Mechanical Engineering
More informationINVESTIGATION OF HEAT TRANSFER CHARACTERISTICS OF CIRCULAR AND DIAMOND PILLARED VANE DISC BRAKE ROTOR USING CFD
SDRP JOURNAL OF NANOTECHNOLOGY & MATERIAL SCIENCE. INVESTIGATION OF HEAT TRANSFER CHARACTERISTICS OF CIRCULAR AND DIAMOND PILLARED VANE DISC BRAKE ROTOR USING CFD Research AUTHOR: A.RAJESH JUNE 2017 1
More informationDesign of A New Non-Contact Screw Seal and Determination of Performance Characteristics
Proceedings of the World Congress on Momentum, Heat and Mass Transfer (MHMT 16) Prague, Czech Republic April 4 5, 2016 Paper No. ENFHT 114 DOI: 10.11159/enfht16.114 Design of A New Non-Contact Screw Seal
More informationFinite Element Analysis on Thermal Effect of the Vehicle Engine
Proceedings of MUCEET2009 Malaysian Technical Universities Conference on Engineering and Technology June 20~22, 2009, MS Garden, Kuantan, Pahang, Malaysia Finite Element Analysis on Thermal Effect of the
More informationEnhance the Performance of Heat Exchanger with Twisted Tape Insert: A Review
Enhance the Performance of Heat Exchanger with Twisted Tape Insert: A Review M.J.Patel 1, K.S.Parmar 2, Umang R. Soni 3 1,2. M.E. Student, department of mechanical engineering, SPIT,Basna, Gujarat, India,
More informationCFD Analysis and Comparison of Fluid Flow Through A Single Hole And Multi Hole Orifice Plate
CFD Analysis and Comparison of Fluid Flow Through A Single Hole And Multi Hole Orifice Plate Malatesh Barki. 1, Ganesha T. 2, Dr. M. C. Math³ 1, 2, 3, Department of Thermal Power Engineering 1, 2, 3 VTU
More informationInternational Journal of Scientific & Engineering Research, Volume 5, Issue 7, July-2014 ISSN
ISSN 9-5518 970 College of Engineering Trivandrum Department of Mechanical Engineering arundanam@gmail.com, arjunjk91@gmail.com Abstract This paper investigates the performance of a shock tube with air
More informationTank mixing systems with liquid jet mixing nozzles
Tank mixing systems with liquid jet mixing nozzles Liquid jet mixing nozzles Körting liquid jet mixing nozzles are the main components of tank mixing systems which can be applied for continuous as well
More informationImpacts of Short Tube Orifice Flow and Geometrical Parameters on Flow Discharge Coefficient Characteristics
Impacts of Short Tube Orifice Flow and Geometrical Parameters on Flow Discharge Coefficient Characteristics M. Metwally Lecturer, Ph.D., MTC, Cairo, Egypt Abstract Modern offset printing machine, paper
More informationDevelopments in Modern Aero-Engines to minimize the Impact of Bleed Air
Developments in Modern Aero-Engines to minimize the Impact of Bleed Air Dr. Dieter Peitsch Rolls-Royce Deutschland Ltd. & Co. KG Dahlewitz, Germany Contact: dieter.peitsch@rolls-royce.com Outline Why is
More informationCoupled Simulation of Multiphase Fluid Flow & Multiple Body Motion: Oil Flow in a Rotating Spur-gear System
Coupled Simulation of Multiphase Fluid Flow & Multiple Body Motion: Oil Flow in a Rotating Spur-gear System Christine Klier, Matthias Banholzer, Kathleen Stock, Ludwig Berger Oil flow in a rotating spur-gear
More informationFlow Controlled Core Overview
Flow Controlled Core Overview Hanna Reiss, Snecma Safran Group Introduction High BPR and/or new architectures will require highly loaded, efficient and operable HPC (+20/25% vs. in-service compressor)
More informationUse of Flow Network Modeling for the Design of an Intricate Cooling Manifold
Use of Flow Network Modeling for the Design of an Intricate Cooling Manifold Neeta Verma Teradyne, Inc. 880 Fox Lane San Jose, CA 94086 neeta.verma@teradyne.com ABSTRACT The automatic test equipment designed
More informationAdvanced Aerodynamic Design Technologies for High Performance Turbochargers
67 Advanced Aerodynamic Design Technologies for High Performance Turbochargers TAKAO YOKOYAMA *1 KENICHIRO IWAKIRI *2 TOYOTAKA YOSHIDA *2 TORU HOSHI *3 TADASHI KANZAKA *2 SEIICHI IBARAKI *1 In recent years,
More informationCFD Simulation of a Scroll Compressor Oil Pumping System
Purdue University Purdue e-pubs International Compressor Engineering Conference School of Mechanical Engineering 2000 CFD Simulation of a Scroll Compressor Oil Pumping System J. de Bernardi Danfoss Maneurop
More informationThis thesis is protected by copyright which belongs to the author.
A University of Sussex DPhil thesis Available online via Sussex Research Online: http://sro.sussex.ac.uk/ This thesis is protected by copyright which belongs to the author. This thesis cannot be reproduced
More informationHERCULES-2 Project. Deliverable: D8.8
HERCULES-2 Project Fuel Flexible, Near Zero Emissions, Adaptive Performance Marine Engine Deliverable: D8.8 Study an alternative urea decomposition and mixer / SCR configuration and / or study in extended
More informationPerformance analysis of an axial exhaust diffuser downstream of an un-shrouded turbine
Advances in Fluid Mechanics X 419 Performance analysis of an axial exhaust diffuser downstream of an un-shrouded turbine R. Blanco 1 & S. Farokhi 2 1 MAN Diesel & Turbo Schweiz AG, Zürich, Switzerland
More informationCOMPRESSIBLE FLOW ANALYSIS IN A CLUTCH PISTON CHAMBER
COMPRESSIBLE FLOW ANALYSIS IN A CLUTCH PISTON CHAMBER Masaru SHIMADA*, Hideharu YAMAMOTO* * Hardware System Development Department, R&D Division JATCO Ltd 7-1, Imaizumi, Fuji City, Shizuoka, 417-8585 Japan
More informationInvestigation for Flow of Cooling Air through the Ventilated Disc Brake Rotor using CFD
International Journal of Thermal Technologies E-ISSN 2277 4114 2015 INPRESSCO, All Rights Reserved Available at http://inpressco.com/category/ijtt/ Research Article Investigation for Flow of Cooling Air
More information(1) Keywords: CFD, helicopter fuselage, main rotor, disc actuator
SIMULATION OF FLOW AROUND FUSELAGE OF HELICOPTER USING ACTUATOR DISC THEORY A.S. Batrakov *, A.N. Kusyumov *, G. Barakos ** * Kazan National Research Technical University n.a. A.N.Tupolev, ** School of
More informationFSI and Modal Analysis of Elastic Ring Squeeze Film Damper for Small Gas Turbine Engines
FSI and Modal Analysis of Elastic Ring Squeeze Film Damper for Small Gas Turbine Engines Thennavarajan Subramanian 1*, Jeyaraj P 2, Manikandan L P 3, S S Kulkarni 4, Soumendu Jana 5 Technical Officer,
More informationFEDSM NUMERICAL AND EXPERIMENTAL FLOW ANALYSIS OF A CRYOGENIC POWER RECOVERY TURBINE
Proceedings of FEDSM 98 1998 ASME Fluids Engineering Division Summer Meeting June 1-5, 1998, Washington, DC FEDSM98-4988 NUMERICAL AND EXPERIMENTAL FLOW ANALYSIS OF A CRYOGENIC POWER RECOVERY TURBINE Nick
More informationTemperature Field in Torque Converter Clutch
3rd International Conference on Mechanical Engineering and Intelligent Systems (ICMEIS 2015) Temperature Field in Torque Converter Clutch Zhenjie Liu 1, a, Chao Yi 1,b and Ye Wang 1,c 1 The State Key Laboratory
More information51. Heat transfer characteristic analysis of negative pressure type EGR valve based on CFD
51. Heat transfer characteristic analysis of negative pressure type EGR valve based on CFD Guannan Hao 1, Sen Zhang 2, Yiguang Yin 3 Binzhou University, Binzhou, China 1 Corresponding author E-mail: 1
More informationPressure Drop Distribution in Smooth and Rib Roughened Square Channel with Sharp 180 Bend in the Presence of Guide Vanes
International Journal of Rotating Machinery, 10: 99 114, 2004 Copyright c Taylor & Francis Inc. ISSN: 1023-621X print DOI: 10.1080/10236210490276692 Pressure Drop Distribution in Smooth and Rib Roughened
More informationTransactions on Modelling and Simulation vol 10, 1995 WIT Press, ISSN X
Flow characteristics behind a butterfly valve M. Makrantonaki," P. Prinos,* A. Goulas' " Department of Agronomy, Faculty of Technological Science, University of Thessalia, Greece * Hydraulics Laboratory,
More informationInnovative Centrifugal Compressor Design
Innovative Centrifugal Compressor Design L. Tarnowski TURBOMECA groupe SAFRAN INTRODUCTION SP2 : IRA (Intercooled Recuperative Aero-engine) Task 2.2.5 HP Centrifugal Compressor Design The challenge is
More informationExperimental Testing of a Rotating Detonation Engine Coupled to Nozzles at Conditions Approaching Flight
25 th ICDERS August 2 7, 205 Leeds, UK Experimental Testing of a Rotating Detonation Engine Coupled to Nozzles at Conditions Approaching Flight Matthew L. Fotia*, Fred Schauer Air Force Research Laboratory
More informationSports Car Brake Cooling Simulation with CAD-Embedded CFD
Automotive Sports Car Brake Cooling Simulation with CAD-Embedded CFD By Mike Gruetzmacher, FloEFD Product Specialist, Mentor Graphics B rake cooling is a crucial area in motorsport and sports car engineering.
More informationABSTRACT 1. INTRODUCTION
1260, Page 1 Patrice BONNEFOI 1, Philippe DUGAST 2, Jean de BERNARDI 3 1 Danfoss CC, Advanced Technology, Trévoux, France 33 (0)4 74 00 28 29, p.bonnefoi@danfoss.com 2 Danfoss CC, Advanced Technology,
More informationNumerical research on hydrodynamic characteristics of end cover of pressure exchanger
IOP Conference Series: Materials Science and Engineering PAPER OPEN ACCESS Numerical research on hydrodynamic characteristics of end cover of pressure exchanger To cite this article: L Jiao et al 2016
More informationPredictions of Cooling From Dirt Purge Holes Along the Tip of a Turbine Blade
Proceedings of ASME Turbo Expo 2003 Power for Land, Sea, and Air June 16 19, 2003, Atlanta, Georgia, USA GT2003-38251 Predictions of Cooling From Dirt Purge Holes Along the Tip of a Turbine Blade E. M.
More informationLoad Analysis and Multi Body Dynamics Analysis of Connecting Rod in Single Cylinder 4 Stroke Engine
IJSRD - International Journal for Scientific Research & Development Vol. 3, Issue 08, 2015 ISSN (online): 2321-0613 Load Analysis and Multi Body Dynamics Analysis of Connecting Rod in Single Cylinder 4
More informationFlow Simulation of Diesel Engine for Prolate Combustion Chamber
IJIRST National Conference on Recent Advancements in Mechanical Engineering (RAME 17) March 2017 Flow Simulation of Diesel Engine for Prolate Combustion Chamber R.Krishnakumar 1 P.Duraimurugan 2 M.Magudeswaran
More informationNumerical Investigation of the Gas Leakage through the Piston-Cylinder Clearance of Reciprocating Compressors
Purdue University Purdue e-pubs International Compressor Engineering Conference School of Mechanical Engineering 2014 Numerical Investigation of the Gas Leakage through the Piston-Cylinder Clearance of
More informationIAC-15-C4.3.1 JET INDUCER FOR A TURBO PUMP OF A LIQUID ROCKET ENGINE
IAC-15-C4.3.1 JET INDUCER FOR A TURBO PUMP OF A LIQUID ROCKET ENGINE Martin Böhle Technical University Kaiserslautern, Germany, martin.boehle@mv.uni-kl.de Wolfgang Kitsche German Aerospace Center (DLR),
More informationUniversity of Huddersfield Repository
University of Huddersfield Repository Colley, Gareth, Mishra, Rakesh, Rao, H.V. and Woolhead, R. Performance evaluation of three cross flow vertical axis wind turbine configurations. Original Citation
More informationAerodynamically induced power loss in hard disk drives
Microsyst Technol (2005) 11: 741 746 DOI 10.1007/s00542-005-0575-8 TECHNICAL PAPER Sung-Oug Cho Æ Seung-Yop Lee Æ Yoon-Chul Rhim Aerodynamically induced power loss in hard disk drives Received: 30 June
More informationFlow and Heat Transfer Analysis of an Inlet Guide Vane with Closed-loop Steam Cooling
International Conference on Intelligent Systems Research and Mechatronics Engineering (ISRME 2015) Flow and Heat Transfer Analysis of an Inlet Guide Vane with Closed-loop Steam Cooling Siping Zhai 1, Chao
More informationin ultra-low NOx lean combustion grid plate
CFD predictions of aerodynamics and mixing in ultra-low NOx lean combustion grid plate flame stabilizer JOSÉ RAMÓN QUIÑONEZ ARCE, DR. ALAN BURNS, PROF. GORDON E. ANDREW S. SCHOOL OF CHEMICAL AND PROCESS
More informationCFD Analysis of an Energy Scavenging Axial Flow Micro Turbine using Automotive Exhaust Gases
International Conference of Advance Research and Innovation (-014) CFD Analysis of an Energy Scavenging Axial Flow Micro Turbine using Automotive Exhaust Gases Chitrarth Lav, Raj Kumar Singh Department
More informationEnhanced Heat Transfer Surface Development for Exterior Tube Surfaces
511 A publication of CHEMICAL ENGINEERING TRANSACTIONS VOL. 32, 2013 Chief Editors: Sauro Pierucci, Jiří J. Klemeš Copyright 2013, AIDIC Servizi S.r.l., ISBN 978-88-95608-23-5; ISSN 1974-9791 The Italian
More informationA Computational Study of Axial Compressor Rotor Casing Treatments and Stator Land Seals
Virginia Commonwealth University VCU Scholars Compass Theses and Dissertations Graduate School 2006 A Computational Study of Axial Compressor Rotor Casing Treatments and Stator Land Seals Charles C. Cates
More information[Rao, 4(7): July, 2015] ISSN: (I2OR), Publication Impact Factor: 3.785
IJESRT INTERNATIONAL JOURNAL OF ENGINEERING SCIENCES & RESEARCH TECHNOLOGY CFD ANALYSIS OF GAS COOLER FOR ASSORTED DESIGN PARAMETERS B Nageswara Rao * & K Vijaya Kumar Reddy * Head of Mechanical Department,
More informationCorresponding Author, Dept. of Mechanical & Automotive Engineering, Kongju National University, South Korea
International Journal of Mechanical & Mechatronics Engineering IJMME-IJENS Vol:15 No:04 62 A Study on Enhancing the Efficiency of 3-Way Valve in the Fuel Cell Thermal Management System Il Sun Hwang 1 and
More information17/11/2016. Turbomachinery & Heat Transfer Laboratory Faculty of Aerospace Engineering Technion Israel Institute of Technology, Israel
17/11/2016 Turbomachinery & Heat Transfer Laboratory Faculty of Aerospace Engineering Technion Israel Institute of Technology, Israel 1 Motivation New challenges rise due to increase in demands from small
More informationNumerical Simulation on the Pattern Factor of the Annular Combustor
Numerical Simulation on the Pattern Factor of the Annular Combustor Balakrishnan B.M 1, Mohana Priya G 2, Revathi M 3 Department of Mechanical Engineering, Mahendra Engineering College, Salem, India 1
More informationStatic And Modal Analysis of Tractor Power Take Off (PTO) Gearbox Housing
Static And Modal Analysis of Tractor Power Take Off (PTO) Gearbox Housing Gopali S Lamani 1, Prof: S.R.Basavaraddi 2, Assistant Professor, Department of Mechanical Engineering, JSPM NTC RSSOER,India1 Professor,
More informationMARINE FOUR-STROKE DIESEL ENGINE CRANKSHAFT MAIN BEARING OIL FILM LUBRICATION CHARACTERISTIC ANALYSIS
POLISH MARITIME RESEARCH Special Issue 2018 S2 (98) 2018 Vol. 25; pp. 30-34 10.2478/pomr-2018-0070 MARINE FOUR-STROKE DIESEL ENGINE CRANKSHAFT MAIN BEARING OIL FILM LUBRICATION CHARACTERISTIC ANALYSIS
More informationOptimisation of Double Pipe Helical Tube Heat Exchanger and its Comparison with Straight Double Tube Heat Exchanger
DOI 1.17/s432-16-261-x ORIGINAL CONTRIBUTION Optimisation of Double Pipe Helical Tube Heat Exchanger and its Comparison with Straight Double Tube Heat Exchanger Rashid Kareem 1 Received: 3 June 214 / Accepted:
More informationAircraft Propulsion Technology
Unit 90: Aircraft Propulsion Technology Unit code: L/601/7249 QCF level: 4 Credit value: 15 Aim This unit aims to develop learners understanding of the principles and laws of aircraft propulsion and their
More informationVisualization of Flow and Heat Transfer in Tube with Twisted Tape Consisting of Alternate Axis
2012 4th International Conference on Computer Modeling and Simulation (ICCMS 2012) IPCSIT vol.22 (2012) (2012) IACSIT Press, Singapore Visualization of Flow and Heat Transfer in Tube with Twisted Tape
More informationFlow Characteristics in an Augmentation Channel of a Direct Drive Turbine for Wave Power Generation
The 10 th Asian International Conference on Fluid Machinery 21 st 23 rd October 2009, Kuala Lumpur Malaysia Paper ID: AICFM0131 Flow Characteristics in an Augmentation Channel of a Direct Drive Turbine
More informationSimulation Studies on the Effect of Porous Twisted Plate Inserts on the Performance of Fire Tube Steam Packaged Boiler
Simulation Studies on the Effect of Porous Twisted Plate Inserts on the Performance of Fire Tube Steam Packaged Boiler S. Hassan *,a, M. K. Roslim b and R. M. Zain c Mechanical Engineering Department,
More informationANALYSIS OF BLADES OF AXIAL FLOW FAN USING ANSYS. Mahajan Vandana N.,* Shekhawat Sanjay P.
Research Article ANALYSIS OF BLADES OF AXIAL FLOW FAN USING ANSYS. Mahajan Vandana N.,* Shekhawat Sanjay P. Address for Correspondence Department of Mechanical Engg. S.S.B.T s College of Engg. and Technology,
More informationSmoke Reduction Methods Using Shallow-Dish Combustion Chamber in an HSDI Common-Rail Diesel Engine
Special Issue Challenges in Realizing Clean High-Performance Diesel Engines 17 Research Report Smoke Reduction Methods Using Shallow-Dish Combustion Chamber in an HSDI Common-Rail Diesel Engine Yoshihiro
More informationNumerical Simulation of Gas Turbine Can Combustor Engine
Numerical Simulation of Gas Turbine Can Combustor Engine CH UMAMAHESHWAR PRAVEEN 1*, A HEMANTH KUMAR YADAV 2 1. Engineer, CDG BOEING Company, Chennai, India. 2. B.Tech Aeronautical Engineer 2012 passout,
More informationIMPROVING BOILER COMBUSTION USING COMPUTATIONAL FLUID DYNAMICS MODELLING
REFEREED PAPER IMPROVING BOILER COMBUSTION USING COMPUTATIONAL FLUID DYNAMICS MODELLING VAN DER MERWE SW AND DU TOIT P John Thompson, Sacks Circle, Bellville South, 7530, South Africa schalkv@johnthompson.co.za
More informationP. Teufel and A. Böhmer, ABB Turbo Systems, SIMULIA Customer Conference Thrust Collar Bearing Optimization using Isight
P. Teufel and A. Böhmer, ABB Turbo Systems, SIMULIA Customer Conference 2012 Thrust Collar Bearing Optimization using Isight May 23, 2012 Thrust Collar Bearing Optimization Using Isight Contents Turbocharging:
More information