Exit Flow Research Articles

Effect of Rotation on Heat Transfer in AR = 2:1 and AR = 4:1 Channels Connected by a Series of Crossover Jets

Abstract Detailed heat transfer measurements using transient liquid crystal thermography were performed on a novel cooling design covering the mid-chord and trailing edge region of a typical gas turbine blade under stationary and rotating conditions. The test section comprised two channels with aspect ratio (AR) of 2:1 (mid-chord) and 4:1 (trailing edge), where the coolant was fed into the AR = 2:1 channel from the root. Rib turbulators with a pitch-to-rib height ratio (p/e) of 10 and rib height-to-channel hydraulic diameter ratio (e/Dh) of 0.075 were placed in the AR = 2:1 channel at an angle of 60 deg relative to the direction of flow. The coolant after entering this section was routed to the AR = 4:1 section through a set of crossover jets. The purpose of the crossover jets was to induce sideways impingement onto the pin fins that were placed in the 4:1 section to enhance heat transfer. The 4:1 section had a realistic trapezoidal shape that mimics the trailing edge of an actual gas turbine blade. The pin fins were arranged in a staggered array with a center-to-center spacing of 2.5 times the pin diameter in both spanwise and streamwise directions. The trailing edge section consisted of both radial and cutback exit holes for flow exit. Experiments were performed for the Reynolds number (Redh(AR=2:1)) of 20,000 at Rotation numbers (Rodh(AR=2:1)) of 0, 0.1, and 0.14. The channel-averaged heat transfer coefficient on trailing side was ∼28% (AR = 2:1) and ∼7.6% (AR = 4:1) higher than the leading side for Rotation number (Ro) of 0.1. It is shown that the combination of crossover jets and pin fins can be an effective method for cooling wedge-shaped trailing edge channels over axial cooling flow designs.

Bohm Criterion of Plasma Sheaths away from Asymptotic Limits.

The plasma exit flow speed at the sheath entrance is constrained by the Bohm criterion. The so-called Bohm speed regulates the plasma particle and power exhaust fluxes to the wall, and it is commonly deployed as a boundary condition to exclude the sheath region in quasineutral plasma modeling. Here the Bohm criterion analysis is performed in the intermediate plasma regime away from the previously known limiting cases of adiabatic laws and the asymptotic limit of infinitesimal Debye length in a finite-size system, using the transport equations of an anisotropic plasma. The resulting Bohm speed has explicit dependence on local plasma heat flux, temperature isotropization, and thermal force. Comparison with kinetic simulations demonstrates its accuracy over the plasma-sheath transition region in which quasineutrality is weakly perturbed and the Bohm criterion applies.

Numerical investigations on the effect of blade tip winglet on leakage flow loss reduction for a zero inlet swirl turbine rotor

AbstractThe tip leakage flow generates a large amount of aerodynamic losses in a zero inlet swirl turbine rotor (ZISTR), which directly uses the axial exit flow downstream of a combustion chamber without any nozzles. To reduce the tip leakage flow loss and improve the efficiency for the ZISTR, a front suction side winglet is employed on the blade tip, and the effect of winglet width is numerically investigated to explore its design space. It is found that, a suction side leading edge horseshoe vortex (SHV) on the blade tip plays a crucial role in mitigating the tip leakage flow loss. This SHV rotates in the reverse direction to the leakage vortex, so it tends to break the formation of the leakage vortex near the front part of suction side. With a larger winglet width, the SHV stays longer time on the blade tip and leaves it at a further downstream location. This increases the time and the contact area of the interaction between the SHV and the leakage vortex, so the leakage vortex is further weakened. Thus, the tip leakage flow loss is reduced, and the efficiency is improved. However, a larger winglet width also increases the heat load of the blade due to a larger blade surface area. The ZISTR designed with the winglet width equal to 2.1% blade pitch achieves a great trade-off between efficiency and heat load that the efficiency is improved by 0.85% at an expense of 1.2% increment of the heat load. Besides, for the blade using this winglet, the mechanical stress due to the centrifugal, aerodynamic and thermal load is acceptable for the engine application. This investigation indicates a great potential in the improvement of efficiency for the ZISTR using a blade tip winglet designed on the front suction side.

Effect of inflow conditions on transonic turbine airfoil limit loading

To better understand airfoil limit loading and the effect inflow conditions have on local efficiency, a computational fluid dynamic investigation was performed for four different transonic turbine airfoils under sub-critical, critical, and supercritical conditions. A computational baseline was established using data previously collected at the Pratt and Whitney Canada High-Speed Wind Tunnel at Carleton University near design conditions using the Reynolds-Averaged Naiver-Stokes shear stress transport k − ω turbulence model with γ transition. The effects of inflow conditions on aerodynamic performance were examined by varying incidence by ± 20°, mainstream turbulence intensity from 5 to 20% and mainstream turbulent length scale from 1 to 100% of the airfoil pitch. Quantitative data of mass-flow averaged Mach numbers, mass-flow averaged flow angles, surface isentropic Mach number distributions and mass-flow averaged total pressure loss coefficients were collected and are presented alongside flow visualizations of numerical Schlieren images to allow for a detailed description of the entire flow domain. Similar to previous experimental work the limit loading pressure ratio and the mass-flow averaged outlet flow angle were strongly correlated with the airfoil outlet metal angle. The influence of inflow conditions was minimal on the exit flow profile with the exception of the mass-flow averaged total pressure loss coefficients. Results show incidence variation to change the total pressure loss coefficient depending on the airfoil, whereas, turbulence intensity and turbulent length scale predicted a drastic increase in loss with increased turbulence level for all airfoils considered.

Achieving superior carbon transfer efficiency and pH control using membrane carbonation with a wide range of CO2 contents for the coccolithophore Emiliania huxleyi

The economic viability of microalgal-derived products relies on rapid CO2 transfer in a cost-effective manner. Many industrial gas streams contain concentrated CO2 that, if converted to useful products, would lower greenhouse gas emissions and valorize the wasted CO2. Membrane carbonation (MC) uses non-porous hollow-fiber gas-transfer membranes to deliver CO2 without bubble formation, which makes it possible to achieve a high carbon-transfer efficiency (CTE). However, inert gasses in the industrial streams (e.g., N2, O2, and H2O) can significantly lower the CO2-delivery rate. The means to overcome the buildup of inert gases in the membrane lumen is to manage the distal end of the membranes to sweep out inert gases while not wasting significant CO2. A MC-venting strategy was evaluated for CO2 inputs from 5% to 100%. Abiotic tests using a restricted exit flow could achieve >95% CTEabiotic for industrial CO2 streams. When integrated with semi-continuous cultivation of a marine coccolithophore, Emiliania huxleyi, CO2 delivery and venting were on-demand based on a pH set points and pH-actuated feed and venting valves. MC using the venting strategy achieved 100% CTEbiotic when delivering 100% and 50% CO2, which was better than 50% CTEbiotic obtained from pH-controlled sparging of 100% CO2-sparging. E. huxleyi consistently fixed ~80% of the delivered CO2 into biomass, and the remaining ~20% to calcite coccoliths. The compact size of MC modules, stable pH control, and no shear forces from bubble agitation during the CO2 delivery made MC an ideal match for cultivation of coccolithophores, which are sensitive to shear forces and pH fluctuations.

Online Spatio-Temporal Crowd Flow Distribution Prediction for Complex Metro System

As a key mission of the modern traffic management, crowd flow prediction (CFP) benefits in many tasks of intelligent transportation services. However, most existing techniques focus solely on forecasting entrance and exit flows of metro stations that do not provide enough useful knowledge for traffic management. In practical applications, managers desperately want to solve the problem of getting the potential passenger distributions to help authorities improve transport services, termed as crowd flow distribution (CFD) forecasts. Therefore, to improve the quality of transportation services, we proposed three spatiotemporal models to effectively address the network-wide CFD prediction problem based on the online latent space (OLS) strategy. Our models take into account the various trending patterns and climate influences, as well as the inherent similarities among different stations that are able to predict both CFD and entrance and exit flows precisely. In our online systems, a sequence of CFD snapshots is used as the training data. The latent attribute evolutions of different metro stations can be learned from the previous trend and do the next prediction based on the transition patterns. All the empirical results demonstrate that the three developed models outperform all the other state-of-the-art approaches on three large-scale real-world datasets.

Wake characteristics of a steam turbine rotor tip linear cascade blade in subsonic flow

Experimental investigations have been carried out on a steam turbine rotor tip linear cascade to determine the effect of Mach number on the flow and total pressure losses at zero degree of incidence. Static pressure distribution on the blade surfaces have been measured. Exit flow survey has been carried out using a precalibrated five hole probe at the corresponding Mach number. The exit Mach number has been varied from 0.27 to 0.52. The effect of Mach number on various parameters such as lift coefficient, total pressure loss coefficient, mass averaged exit flow parameters and wake parameters has been found to be small. Wake self-similarity has been observed for velocity profiles at all Mach numbers. The wake half widths and integral thicknesses increase slowly with Mach number. Shape factors are in the range of 1.1 to 1.4, indicating turbulent boundary layers on the suction and pressure surfaces of the blade.

Effect of Internal Effusion on Aerothermal Performance of a Three-Pass Channel Roughened by Angled Ribs and Pin-Fins with Lateral Flow Exit

Effect of Internal Effusion on Aerothermal Performance of a Three-Pass Channel Roughened by Angled Ribs and Pin-Fins with Lateral Flow Exit

Prototyping a spinning adsorber submerged filter for continuous removal of wastewater contaminants

Adsorption process is widely used for the removal of wastewater contaminants. Classic adsorption units are fixed beds and membrane filtration systems. In this work a novel configuration of a bench scale spinning adsorber submerged filter is proposed. Different prototypes of cylindric, truncated cone or prismatic spinning adsorbers were studied using activated carbon of different particle sizes GAC (1.5 mm, Granulated), μGAC (0.475 mm, microGranulated), and cPAC (0.237 mm, coarse Powder) as adsorbent, and azorubine as model adsorbate. High maximum azorubine adsorptions per unit mass of adsorbent of 214, 225 and 275 mg/g for GAC, μGAC and cPAC, respectively, were obtained using the Langmuir isotherm adsorption model. Batch adsorption followed pseudo-second order kinetics, and adsorbate uptake rate increased with decreasing adsorbent particle size. Best adsorption unit was a tank equipped with a spinning rectangular prism adsorber prototype all made of stainless-steel woven wire filter of 180 mesh size. Running at 600 rpm and filled with a high cPAC concentration (25 g/L), adsorber can remove azorubine at similar rates that the use of free moving cPAC. Adsorber unit can run in continuous mode and works even better as a novel spinning submerged filter where filtered flow exits from a central pipe axis. This integrated adsorption-submerged filtration operation mode offer the possibility of adding a high initial dose or a continuous dosing of adsorbent in the tank, increasing the adsorbent concentration of the unit. This system can also offer novel opportunities for wastewater contaminants removal using different adsorbent materials located separately.

Vibration Characteristics of a Hydroelectric Generating System with Different Hydraulic-Mechanical-Electric Parameters in a Sudden Load Increasing Process

In a sudden load increasing process (SLIP), the hydroelectric generating system (HGS) experiences a severe vibration response due to the sudden change of the hydraulic-mechanical-electric parameters (HMEPs). The instability of HGS limits the ability of sudden load increase, and its flexibility and reliability are reduced. Thus, in this study, a new transient nonlinear coupling model of HGS is proposed, which couples the hydro-turbine governing system (HTGS) and the hydro-turbine generator shafting system (HGSS) with the hydraulic-mechanical-electric coupling force, rotating speed, flow rate, hydro-turbine torque, electromagnetic torque, and guide vane opening. By using numerical simulation, the influences of different HMEPs on the vibration characteristics of HGS in SLIP are analyzed. The result shows that, compared with stable operating conditions, the vibration amplitude of HGS increases sharply in SLIP. The increase of the sudden load increasing amount, blade exit flow angle, mass eccentricity and excitation current, and the decrease in guide bearing stiffness and average air gap between the stator and rotor cause abnormal vibration of different degrees in the HGS. Hydraulic factors have the greatest influence on the nonlinear dynamic behavior of HGS. The maximum vibration amplitude of HGS in SLIP is increased by 70.46%, compared with that under stable operating conditions. This study provides reasonable reference for the analysis of the nonlinear dynamic behavior of HGS in SLIP under the multiple vibration sources.

Evacuation trials from a double-deck electric train unit: Experimental data and sensitivity analysis

Passenger trains represent a challenging environment in emergencies, with specific evacuation conditions resulting from the typical layout and interior design inherent to public transportation vehicles. This paper describes a dataset obtained in a full-scale controlled experiment emulating the emergency evacuation of a double-deck electric unit railcar carried out in Prague in 2018. 15 evacuation trials involving 91 participants were conducted under various evacuation scenarios considering different compositions of passenger crowd, exit widths, and exit types (egress to a high platform, to an open rail line using stairs, and a 750 mm jump without any supporting equipment). The study’s main goals were to collect experimental data on the movement conditions in the railcar and to study the impact of various boundary conditions on evacuation process and total evacuation time. Movement characteristics (exit flows, speeds) and human behaviour (pre-movement activities, exiting behaviours) were also analysed. The data obtained was used to validate and adjust a Pathfinder model to capture important aspects of evacuation from the railcar. Furthermore, a series of simulations using this model was performed to provide sensitivity analysis of the influence of crowd composition, exit width, and exit type on total evacuation time. As a key finding, we can conclude that for the case of a standard exit path (platform or stairs) the width of the main exit had the greatest impact on total evacuation time, however, crowd composition played the prevailing role in evacuation scenarios involving a jump.

Investigation of inner cavitation and nozzle exit flow patterns for elliptical orifice GDI injectors with various aspect ratios

The non-circular orifice has potential ability to increase the fuel spray and mixing quality. While the application of non-circular orifice in the GDI injection system hasn't been reported yet. The inner flow behaviors have great impact on the spray and mixing quality. Therefore, Volume of Fluid (VOF) and Large Eddy Simulation (LES) method are introduced to investigate the effects of non-circular orifices cross section shapes of GDI injector on the inner flow patterns and nozzle exit flow parameters. From the results, the total vapor phase volume fraction of the elliptical orifice is smaller than that in the circular one. The vapor phase fraction of elliptical orifice decreases with the increase of aspect ratio, and the vapor phase volume fraction of the elliptical E4 orifice is the smallest. In addition, the critical cavitation point of circular orifice is earlier than that of elliptical orifice, which indicated that the circular orifice is more prone to cavitate than the elliptical one. Finally, the discharge coefficient of circular orifice is the smallest among all orifices. The velocity coefficient of elliptical E4 orifice is the minimum under the cavitation conditions, while the elliptical E4 orifice held the largest area coefficient among other orifices.

Experimental Flowfield Analyses of Installed Subsonic Jet–Pylon Interaction

This paper presents an experimental investigation into the flowfield of single-stream jets blocked by internal and external rigid nozzle structures. The jets studied include axisymmetric round and annular jets and asymmetric blocked pylon jets. The pylon nozzles tested have three different thicknesses, reducing the exit flow area by 5, 10, and 20%. Hot-wire anemometry is used to record the unsteady velocity field both at the nozzle exit and up to 10 jet diameters downstream. Installation effects, created by mounting a wing section close to the jet, and forward-flight effects are also considered. The nominal Mach numbers studied are and 0.6 for the jet flow, and , 0.1, and 0.2 for the flight stream. Results show that the nozzle blockages 1) redirect the jet toward the wing, 2) increase the entrainment rate in locations far downstream of the nozzle exit, 3) produce dominant effects compared to the change of entrainment induced by the presence of the wing, and 4) considerably increase the normalized turbulence intensity generated in in-flight conditions.

Evaluating the Influence of Rotor-Casing Eccentricity on Turbine Efficiency Including Time-Resolved Flow Field Measurements

Abstract The clearance that exists between the casing and turbine blade tips is one of the key drivers of efficiency in gas turbine engines. For this reason, engine manufacturers utilize precise manufacturing techniques and may use clearance control systems to minimize tip clearances to reduce associated losses. Despite these efforts, turbines typically exhibit some nominal casing ovality or rotor-casing eccentricity, and changes to blade tip clearance during operation commonly occur due to thermal and mechanical stresses. The present study investigates non-axisymmetric tip clearance effects by creating a rotor-casing eccentricity in a one-stage axial test turbine operating in a continuous-duration mode at engine-relevant conditions with engine representative hardware. A magnetic levitation bearing system was leveraged to move the turbine shaft to vary the rotor-casing eccentricity without test section disassembly. The results of this study indicate that rotor-casing eccentricity does not affect overall turbine efficiency over the range that was tested, but does locally influence efficiency and the rotor exit flow field. Comparisons of flow angle and secondary flow kinetic energy (SKE) agreed with previous studies and existing analytical methods, respectively. Collectively, these results indicate that tip clearance can be studied locally on an eccentric rotor.

Rancang Bangun Sistem Informasi Inventory Untuk Mengontrol Persediaan Pada PT.Gotrans Logistics International

Inventory system is a system for managing inventory in the warehouse. Inventory system is now widely used by companies developing in general. Especially in terms of data management stuff. PT.Gotrans Logistics company engaged in delivery in the province of Riau where the activity of good and effective performance must be maintained and improved. Like managing, search, entry and exit flow of goodsand report the data items when it’s needed. Based on these problems, the company has a desire to better utilize information technology through the development of an inventory system, because the system of data management activities good in storage at this time have not felt up by the company. This inventory system using metode Waterfall. UML (Unified Modeling Language) as a data flow model. PHP programming language, and database MySQL. The system is built with the concept of user friendly, so the system is made with an easy to understand interface and made attractive.

Torque Around Axial Direction on Rotating Detonation Engines

A rotating detonation engine (RDE) generates a continuous thrust with one or more rotating detonation waves. Because of the velocity on the order of kilometers/second, the reaction zone is relatively small. Therefore, the RDE realizes a short combustion chamber length. However, the detonation waves induce an azimuthal motion of propellant, resulting in torque around the thrust axis. Because the motion does not contribute to the thrust, the torque is important in terms of performance loss. Herein, we conducted combustion tests with a six-axis force sensor to simultaneously measure torque and thrust. A comparison of detonation waves captured by high-speed camera revealed that the torque followed the direction and was offset when the waves existed in both of two directions simultaneously, which indicates the possibility of controlling the torque. Under a mass flow rate at and an equivalence ratio at , when the azimuthal component of shear force was of the thrust, of the total kinetic energy of the exit flow was distributed to the azimuthal component of velocity and did not contribute to the thrust. We therefore concluded that the effect of the azimuthal motion on the RDE’s performance was small.

The value of additional data for public transport origin–destination matrix estimation

Passenger origin–destination data is an important input for public transport planning. In recent years, new data sources have become increasingly common through the use of the automatic collection of entry counts, exit counts and link flows. However, collecting such data can be sometimes costly. The value of additional data collection hence has to be weighed against its costs. We study the value of additional data for estimating time-dependent origin–destination matrices, using a case study from the London Piccadilly underground line. Our focus is on how the precision of the estimated matrix increases when additional data on link flow, destination count and/or average travel distance is added, starting from origin counts only. We concentrate on the precision of the most policy-relevant estimation outputs, namely, link flows and station exit flows. Our results suggest that link flows are harder to estimate than exit flows, and only using entry and exit data is far from enough to estimate link flows with any precision. Information about the average trip distance adds greatly to the estimation precision. The marginal value of additional destination counts decreases only slowly, so a relatively large number of exit station measurement points seem warranted. Link flow data for a subset of links hardly add to the precision, especially if other data have already been added.

Characteristics of shock tube generated compressible vortex rings at very high shock Mach numbers

Compressible vortex rings are usually formed at the open end of a shock tube. They show exciting flow phenomena during their formation, evolution, and propagation depending on the shock Mach number (Ms) and exit flow conditions. This study considers high shock tube pressure ratio (PR) cases showing hitherto unknown, spectacular flow structures. With hydrogen as a driver section gas at high PR, a supersonic compressible vortex ring having vortex ring Mach number (Mv) >1 is obtained for the first time. The formation of multiple triple points and the corresponding slipstream shear layers and, thus, multiple counter-rotating vortex rings (CRVRs) behind the primary vortex ring at different radial locations, in addition to the usual CRVRs, appears to be a unique characteristic for high Mach number vortex rings. During the formation stage, a vortex layer of reverse circulation than that of the primary vortex ring gets generated from the outer wall of the shock tube. The instability of such a vortex layer creates another series of opposite circulation vortices, which later interfere with the primary vortex core considerably. Also, a near stationary slipstream vortex and multiple fast-moving tiny vortices of opposite circulation to the slipstream vortex are observed near the central zone. Mechanisms for the formation of these complex vortical structures are identified. The implications of these phenomena on the vortex ring's geometric and kinematic characteristics, such as ring diameter, core diameter, circulation, and translational velocity, are discussed in detail, illustrating their differences with low vortex ring Mach number cases considering 0.31 < Mv < 1.08.

Experimental Investigation of Wash Fluid Preheating on the effectiveness of online Compressor Washing in a Suction Tunnel Compressor Cascade

Online compressor washing is a promising method of preventing/ recovering the effects of fouling on the compressor blades. However, proper strategies need to be implemented for online compressor washing to be effective since it is conducted when the engine is in operation. This study presents an experimental investigation of wash fluid preheating on the effectiveness of online compressor washing in a suction wind tunnel compressor cascade. Crude oil was uniformly applied on the compressor cascade blade surfaces using a roller brush, and carborundum particles were ingested into the tunnel to create accelerated fouled blades. Demineralized water was preheated to 500C using the heat coil provided in the tank. Washing of the fouled blades were conducted using single flat fan nozzle, where the preheated and non preheated demineralized water were used separately to wash the fouled blades. When fouled blades washed with preheated demineralized and the non-preheated were compared, it was observed that there was little or no difference in terms of total pressure loss coefficient and exit flow angle. However, when the fouled and washed cases were compared, there was a significant difference in total pressure loss coefficient and exit flow angle.

Dimensionless Numbers Relationships for Outer Air Seal of Low Pressure Turbine

The dimensional analysis and the numerical parametric study of the typical outer air seal from a low-pressure turbine were performed in the framework of the presented paper. The most crucial variables for the flow through the outer air seal were identified and further dimensionless numbers were derived. The dependent quantities resulting from the analysis were: the axial Reynolds number (formulated with the bulk velocity, corresponding to the mass flow through the seal), the outlet swirl ratio (incorporating the exit flow angle, important for mixing) and the windage heating (related to the internal losses). Additionally, the discharge coefficient was cross-checked enabling further comparison with the available literature. The comprehensive numerical parametric study included all important contributors for the flow through the seal with a parameter operating range appropriate for engine outer air seals.