Log in

Relevant bibliographies by topics / Turbulent flow in gas turbines

Contents

Journal articles
Dissertations / Theses
Books
Book chapters
Conference papers
Reports

Academic literature on the topic 'Turbulent flow in gas turbines'

Author: Grafiati

Published: 4 June 2021

Last updated: 7 February 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Turbulent flow in gas turbines.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Turbulent flow in gas turbines"

1

Winkler, Dieter, Weiqun Geng, Geoffrey Engelbrecht, Peter Stuber, Klaus Knapp, and Timothy Griffin. "Staged combustion concept for gas turbines." Journal of the Global Power and Propulsion Society 1 (September 27, 2017): CVLCX0. http://dx.doi.org/10.22261/cvlcx0.

Full text

Abstract:

AbstractGas turbine power plants with high load flexibility are particularly suitable to compensate power fluctuations of wind and solar plants. Conventional gas turbines suffer from higher emissions at low load operation. With the objective of improving this situation a staged combustion system has been investigated. At low gas turbine load an upstream stage (first stage) provides stable combustion at low emissions while at higher loads the downstream stage (second stage) is started to supplement the power. Three injection geometries have been studied by means of computational fluid dynamics (CFD) simulations and atmospheric tests. The investigated geometries were a simple annular gap, a jet-in-cross-flow configuration and a lobe mixer. With CFD simulations the quality of mixing of second stage fresh gas with first stage exhaust gas was assessed. The lobe mixer showed the best mixing quality and hence was expected to also be the best variant in terms of combustion. However atmospheric combustion tests showed lower emissions for the jet-in-cross-flow configuration. Comparing flame photos in the visible and ultraviolet (UV) range suggest that the flame might be lifted off for the lobe mixer, leading to insufficient time for carbon monoxide (CO) burnout. CFD analysis of turbulent flame speed, turbulence and strain rates support the hypotheses of lifted off flame. Overall the staged concept was found to show very promising results not only with natural gas but also with natural gas enriched with propane or hydrogen. The investigations showed that apart from having an efficient and compact mixing of the two stages it is also very important to design the flow field such that the second flame can be anchored properly in order to achieve compact flames with sufficient time for CO burnout.

APA, Harvard, Vancouver, ISO, and other styles

2

Rusanov, Andrii V., Viktor L. Shvetsov, Anna I. Kosianova, et al. "The Gas-Dynamic Efficiency Increase of the K-300 Series Steam Turbine Control Compartment." Journal of Mechanical Engineering 23, no. 4 (2020): 6–13. http://dx.doi.org/10.15407/pmach2020.04.006.

Full text

Abstract:

The paper proposes ways to increase the efficiency of nozzle control for steam power turbines of the K-300 series, that, along with the K-200 series turbines, form the basis of thermal energy in Ukraine. The object of study is considered to be the control compartment (CC) of the high-pressure cylinder (HPC) of the K-325-23.5 steam turbine. In the paper, the calculation and design of the control compartment of the steam turbine was performed using the complex methodology developed in IPMach NAS of Ukraine, that includes methods of different levels of complexity, from one-dimensional to models for calculation of spatial viscous flows, as well as analytical methods for spatial geometries of flow parts description based on limited number of parameterized values. The complex design methodology is implemented in the IPMFlow software package, which is a development of the FlowER and FlowER–U software packages. A model of a viscous turbulent flow is based on the numerical integration of an averaged system of Navier-Stokes equations, for the closure of which the two-term Tamman equation of state is used. Turbulent phenomena were taken into account using a SST Menter two-parameter differential turbulence model. The research was conducted for six operation modes in the calculation area, which consisted of more than 3 million cells (elementary volumes), taking into account the interdiscand diaphragm leakage. According to the results of numerical studies of the original control compartment of the K-325-23.5 steam turbine, it is shown that the efficiency in the flow part is quite low in all operation modes, including the nominal one (100% power mode), due to large losses of kinetic energy in the equalization chamber, as well as inflated load on the first stage. On the basis of the performed analysis of gas-dynamic processes, the directions of a control compartment flow part modernization are formed and themodernization itself is executed. In the new flow part, compared to the original one, there is a favorable picture of the flow in all operation modes, which ensures its high gas-dynamic efficiency. Depending on the mode, the efficiency of the control compartment increased by 4.9–7.3%, and the capacity increased by 1–2 MW. In the nominal mode (100% mode) the efficiency of the new control compartment, taking into account the interdisc and overbandage leakage, is 91%.

APA, Harvard, Vancouver, ISO, and other styles

3

Jones, W. P., M. N. Sodha, and J. J. McGuirk. "Calculation of the Flow in a Sector of an Annular Combustor." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power Engineering 203, no. 3 (1989): 187–93. http://dx.doi.org/10.1243/pime_proc_1989_203_026_02.

Full text

Abstract:

Calculations have been made of the isothermal flow field within a sector of an annular combustion chamber representative of the type to be found in small gas turbines. The complex combustor geometry is described using a Cartesian finite difference mesh within which the physical domain boundaries are represented in a piecewise linear fashion. The k-s turbulence model is used to describe turbulent transport. Overall the calculated and measured flow fields are found to be in reasonable agreement and in the primary zone measured velocity profiles are reproduced to within an acceptable accuracy.

APA, Harvard, Vancouver, ISO, and other styles

4

Kvasha, Yu A. "Calculation of a 3D turbulent flow in aircraft gas turbine engine ducts." Technical mechanics 2020, no. 4 (2020): 65–71. http://dx.doi.org/10.15407/itm2020.04.065.

Full text

Abstract:

This work is devoted to the development of approaches to the numerical simulation of 3D turbulent gas flows in different ducts of aircraft gas turbine engines, in particular in inlet device ducts. Inlet devices must provide large values of the total pressure recovery factor and flow uniformity at the engine compressor inlet. The aim of this work is the verification of the operability of a technique developed earlier for the calculation of the parameters of a 3D turbulent flow in complex-shape ducts. The basic approach is a numerical simulation of 3D turbulent gas flows on the basis of the complete averaged Navier¬–Stokes equations and a two-parameter turbulence model. The proposed technique of numerical simulation of a 3D gas flow was tested by calculating a 3D laminar flow in a square pipe bent at a right angle. The calculated flow pattern is in satisfactory agreement with the experimental data on the flow structure in a pipe elbow reported in the literature. Based on a numerical simulation of a 3D turbulent flow in the air duct of one of the air intake configurations for an aircraft turboprop engine, the efficiency of that configuration is assessed. The calculated flow parameter nonuniformity at the air intake outlet, i. e., at the compressor inlet, is compared with that obtained earlier for another air intake configuration for the same engine. It is pointed out that the air intake configuration considered earlier provides a much more uniform flow parameter distribution at the engine compressor inlet. On the whole, this work shows that the quality of subsonic air intakes for aircraft gas turbine engines can be assessed using the proposed numerical technique of 3D gas flow simulation. The results obtained may be used in the aerodynamic improvement of inlet devices for aircraft engines of different types.

APA, Harvard, Vancouver, ISO, and other styles

5

Radomsky, R. W., and K. A. Thole. "Measurements and Predictions of a Highly Turbulent Flowfield in a Turbine Vane Passage." Journal of Fluids Engineering 122, no. 4 (2000): 666–76. http://dx.doi.org/10.1115/1.1313244.

Full text

Abstract:

As highly turbulent flow passes through downstream airfoil passages in a gas turbine engine, it is subjected to a complex geometry designed to accelerate and turn the flow. This acceleration and streamline curvature subject the turbulent flow to high mean flow strains. This paper presents both experimental measurements and computational predictions for highly turbulent flow as it progresses through a passage of a gas turbine stator vane. Three-component velocity fields at the vane midspan were measured for inlet turbulence levels of 0.6%, 10%, and 19.5%. The turbulent kinetic energy increased through the passage by 130% for the 10% inlet turbulence and, because the dissipation rate was higher for the 19.5% inlet turbulence, the turbulent kinetic energy increased by only 31%. With a mean flow acceleration of five through the passage, the exiting local turbulence levels were 3% and 6% for the respective 10% and 19.5% inlet turbulence levels. Computational RANS predictions were compared with the measurements using four different turbulence models including the k-ε, Renormalization Group (RNG) k-ε, realizable k-ε, and Reynolds stress model. The results indicate that the predictions using the Reynolds stress model most closely agreed with the measurements as compared with the other turbulence models with better agreement for the 10% case than the 19.5% case. [S0098-2202(00)00804-X]

APA, Harvard, Vancouver, ISO, and other styles

6

Gerendas, M., and S. Wittig. "Experimental and Numerical Investigation on the Evaporation of Shear-Driven Multicomponent Liquid Wall Films." Journal of Engineering for Gas Turbines and Power 123, no. 3 (2001): 580–88. http://dx.doi.org/10.1115/1.1362663.

Full text

Abstract:

The presented work is concerned with two-phase flows similar to those in prefilming airblast atomizers and combustors employing film vaporization. Correlations for the multicomponent mixture properties and models for the calculations of the multicomponent evaporation were implemented in a well tested elliptic finite-volume code GAP-2D (S. Wittig et al., 1992, “Motion and Evaporation of Shear-Driven Liquid Films in Turbulent Gas,” ASME J. Eng. Gas Turbines Power 114, pp. 395–400) utilizing time-averaged quantities, k,ε turbulence model, wall functions, and curve-linear coordinates in the gas phase, adiabatic or diabatic conditions at the film plate, partially turbulent velocity profile, uniform temperature, and a rapid mixing approach in the wavy film. This new code GAP-2K was tested for stability, precision, and grid independence of the results by applying it to a turbulent hot air flow over a two-component liquid film, a mixture of water and ethanol in different concentrations. Both simulations and experiments were carried out over a wide range of inlet conditions, such as inlet pressure (1–2.6 bar), inlet temperature (298–573 K), inlet air velocity (30–120 m/s), initial liquid flow rate (0.3–1.2 cm2/s), and initial ethanol concentration (20–75 percent mass). Profiles of temperature, gas velocity, and concentration of the evaporating component normal to the film, and the development of the film temperature, the static pressure, the liquid flow rate, and the liquid compound along the film plate have been measured and compared with the simulation, showing a good match.

APA, Harvard, Vancouver, ISO, and other styles

7

Lock, Gary D., Michael Wilson, and J. Michael Owen. "Influence of Fluid Dynamics on Heat Transfer in a Preswirl Rotating-Disk System." Journal of Engineering for Gas Turbines and Power 127, no. 4 (2004): 791–97. http://dx.doi.org/10.1115/1.1924721.

Full text

Abstract:

Modern gas turbines are cooled using air diverted from the compressor. In a “direct-transfer” preswirl system, this cooling air flows axially across the wheel space from stationary preswirl nozzles to receiver holes located in the rotating turbine disk. The distribution of the local Nusselt number Nu on the rotating disk is governed by three nondimensional fluid-dynamic parameters: preswirl ratio βp, rotational Reynolds number Reϕ, and turbulent flow parameter λT. This paper describes heat transfer measurements obtained from a scaled model of a gas turbine rotor-stator cavity, where the flow structure is representative of that found in the engine. The experiments reveal that Nu on the rotating disk is axisymmetric except in the region of the receiver holes, where significant two-dimensional variations have been measured. At the higher coolant flow rates studied, there is a peak in heat transfer at the radius of the preswirl nozzles associated with the impinging jets from the preswirl nozzles. At lower coolant flow rates, the heat transfer is dominated by viscous effects. The Nusselt number is observed to increase as either Reϕ or λT increases.

APA, Harvard, Vancouver, ISO, and other styles

8

Golomb, Richard, Vivek Sahai, and Dah Yu Cheng. "A New Tailpipe Design for GE Frame-Type Gas Turbines to Substantially Lower Pressure Losses." Journal of Turbomachinery 125, no. 1 (2003): 128–32. http://dx.doi.org/10.1115/1.1515335.

Full text

Abstract:

Many GE frame gas turbines have a unique 90-deg tailpipe exhaust system that contains struts, diffusers, and turning vanes. As confirmed in a recent report by GE and other authors, it is known in the industry that this tailpipe design has large pressure losses. In this recent report a pressure loss as high as 60 in. of water (0.15 kgs/sqcm) was cited. Due to the flow separations they create, the report indicates that the struts can cause very high-pressure losses in the turbine. The report also states that these pressure losses can vary with different turbine load conditions. Cheng Fluid Systems and Cheng Power Systems have conducted a study aimed at substantially reducing these pressure losses. Flow control technology introduced to the refinery industry, i.e., the Cheng Rotation Vane (CRV) and the Large Angle Diffuser (LAD) can be used to mitigate the flow separation and turbulence that occurs in turns, bends, and large sudden expansions. Specifically the CRV addresses the flow separations in pipe turns, and the LAD addresses the flow problems that occur with large sudden expansion areas. The paper will introduce the past experience of the CRV and LAD, and will then use computer simulations to show the flow characteristics around a new design. First, the study meticulously goes through the entire GE exhaust system, starting with the redesign of the airfoil shape surrounding the struts. This new design has a larger angle of attack and minimizes the flow separations over a much wider operating range. Second, the pros and cons of the concentric turning vanes are studied and it is shown that they are more flow restrictive, rather than flow enhancing. Third, it is shown that the highly turbulent rectangular box-type exhaust ducting design, substantially contributes to high noise levels and pressure losses. In this paper a completed design will be shown that incorporates a new airfoil shape for the struts, and by using CRV flow technology in combination with the LAD flow technology, the pressure recovery can be enhanced. If the pressure losses could be reduced by 40 inches of water (0.10 kgs/sqcm), the turbine efficiency could be increased by 5%, and the power output could be increased by 6%.

APA, Harvard, Vancouver, ISO, and other styles

9

Bohn, D., and J. Gier. "The Effect of Turbulence on the Heat Transfer in Closed Gas-Filled Rotating Annuli." Journal of Turbomachinery 120, no. 4 (1998): 824–30. http://dx.doi.org/10.1115/1.2841795.

Full text

Abstract:

Higher turbine inlet temperatures are a common measure for increasing the thermal efficiency of modern gas turbines. This development leads not only to the need for more efficient turbine blade cooling but also to the requirement for a more profound knowledge of the mechanically and thermally stressed parts of the rotor. For determining thermal stresses from the temperature distribution in the rotor of a gas turbine, one has to encounter the convective transfer in rotor cavities. In the special case of an entirely closed gas-filled rotating annulus, the convective flow is governed by a strong natural convection. Owen and other researchers have found that the presence of turbulence and its inclusion in the modeling of the flow causes significant differences in the flow development in rotating annuli with throughflow, e.g., different vortex structures. However, in closed rotating annuli there is still a lack of knowledge concerning the influence of turbulence. Based on previous work, in this paper the influence of turbulence on the flow structure and on the heat transfer is investigated. The flow is investigated numerically with a three-dimensional Navier–Stokes solver, based on a pressure correction scheme. To account for the turbulence, a low-Reynolds-number k–ε model is employed. The results are compared with experiments performed at the Institute of Steam and Gas Turbines. The computations demonstrate that turbulence has a considerable influence on the overall heat transfer as well as on the local heat transfer distribution. Three-dimensional effects are discussed by comparing the three-dimensional calculation with a two-dimensional calculation of the same configuration and are found to have some impact.

APA, Harvard, Vancouver, ISO, and other styles

10

MERAD, Asmae BOUANANI, and Mama BOUCHAOUR. "MODELING AND SIMULATION OF THE VERTICAL AXIS WIND TURBINE BY QBLADE SOFTWARE." Algerian Journal of Renewable Energy and Sustainable Development 2, no. 02 (2020): 181–88. http://dx.doi.org/10.46657/ajresd.2020.2.2.11.

Full text

Abstract:

The use of wind energy has no harmful effects on the environment. This makes it a clean energy that is a real alternative to the problem of nuclear waste management and greenhouse gas emissions. Vertical axis wind turbines have prospective advantages in the field of domestic applications, because they have proven effectual in urban areas where wind flow conditions are intermittent, omnidirectional, unsteady and turbulent. The wind cannot ensure a regular energy supply without optimising the aerodynamics of the blades. This article presents a reminder about wind energy and wind turbines, especially the VAWT type wind turbines and also gives a presentation on the aerodynamic side of VAWT by studying the geometry and aerodynamic characteristics of the blade profiles with the acting forces and also the explanation of the DMS multiple flow tube model. This work also gives the different simulation methods to optimize the behaviour of the blades from the selected NACA profiles; the analysis first goes through the design of the blades by the design and simulation software Qblade which is used to calculate also the forces on the blade and the coefficients of lift, drag and fineness. At the end of this article we have the DMS simulation of the VAWT turbines, by determining the power coefficient and the power collected by the turbine to select the wind turbine adapted to a well characterized site.

APA, Harvard, Vancouver, ISO, and other styles

More sources

Dissertations / Theses on the topic "Turbulent flow in gas turbines"

1

Hofeldt, Albert John. "The investigation of naturally-occurring turbulent spots using thin-film gauges." Thesis, University of Oxford, 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.318831.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Bobba, Mohan Krishna. "Flame stabilization and mixing characteristics in a stagnation point reverse flow combustor." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/26502.

Full text

Abstract:

Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2008.<br>Committee Chair: Seitzman, Jerry; Committee Member: Filatyev, Sergei; Committee Member: Jagoda, Jechiel; Committee Member: Lieuwen, Timothy; Committee Member: Shelton, Samuel; Committee Member: Zinn, Ben. Part of the SMARTech Electronic Thesis and Dissertation Collection.

APA, Harvard, Vancouver, ISO, and other styles

3

Lin, Chao-An. "Three-dimensional computations of injection into swirling cross-flow using second-moment closure." Thesis, University of Manchester, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.280543.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

McClain, Stephen Taylor. "A discrete-element model for turbulent flow over randomly-rough surfaces." Diss., Mississippi State : Mississippi State University, 2002. http://library.msstate.edu/etd/show.asp?etd=etd-04032002-140007.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

Cardwell, Nicholas Don. "Investigation of Particle Trajectories for Wall Bounded Turbulent Two-Phase Flows." Diss., Virginia Tech, 2010. http://hdl.handle.net/10919/29642.

Full text

Abstract:

The analysis of turbulent flows provides a unique scientific challenge whose solution remains central to unraveling the fundamental nature of all fluid dynamics. Measuring and predicting turbulent flows becomes even more difficult when considering a two-phase flow, which is a commonly encountered engineering problem across many disciplines. One such example, the ingestion of foreign debris into a gas turbine engine, provided the impetus for this study. Despite more than 40 years of research, operation with a particle-laden inlet flow remains a significant problem for modern turbomachines. The purpose, therefore, is to develop experimental methods for investigating multi-phase flows relevant to the cooling of gas turbine components. Initially, several generic components representing turbine cooling designs were evaluated with a particle-laden flow using a special high temperature test facility. The results of this investigation revealed that blockage was highly sensitive to the carrier flowfield as defined by the cooling geometry. A second group of experiments were conducted in one commonly used cooling design using a Time Resolved Digital Particle Image Velocimetry (TRDPIV) system that directly investigated both the carrier flowfield and particle trajectories. Traditional PIV processing algorithms, however, were unable to resolve the particle motions of the two-phase flow with sufficient fidelity. To address this issue, a new Particle Tracking Velocimetry (PTV) algorithm was developed and validated for both single-phase and two-phase flows. The newly developed PTV algorithm was shown to outperform other published algorithms as well as possessing a unique ability to handle particle laden two-phase flows. Overall, this work demonstrates several experimental methods that are well suited for the investigation of wall-bounded turbulent two-phase flows, with a special emphasis on a turbine cooling method. The studies contained herein provide valuable information regarding the previously unknown fluid and particle dynamics within the turbine cooling system.<br>Ph. D.

APA, Harvard, Vancouver, ISO, and other styles

6

Al-Aabidy, Qahtan. "Modelling of turbulent flow and heat transfer in porous media for gas turbine blade cooling." Thesis, University of Manchester, 2018. https://www.research.manchester.ac.uk/portal/en/theses/modelling-of-turbulent-flow-and-heat-transfer-in-porous-media-for-gas-turbine-blade-cooling(f7781d8e-bb1e-4bb7-a57e-4e77875ad6d6).html.

Full text

Abstract:

This thesis focuses on the study of flow and heat transfer in porous media in both laminar and turbulent flow regimes, by using Volume Averaged Reynolds Navier Stokes (VARNS) approach. The main concern is to investigate the possibility of using porous media for the gas turbine blade cooling. Very recently, using this technique in blade cooling, particularly with internal cooling, has motivated many researchers due to an effective enhancement in the blade cooling. In this study turbulence is represented by using the Launder-Sharma low-Reynolds-number k-Îμ turbulence model, which is modified via proposals by Nakayama and Kuwahara (2008) and Pedras and de Lemos (2001) for extra source terms in the turbulent transport equations to account for the porous structure, which is treated as rigid and isotropic. Due to the changing of the effective porosity as the clear fluid region is approached, the porosity and additional source term in the macroscopic Reynolds averaged Navier-Stokes equations are relaxed across a thin transitional layer at the edges of the porous media. This is achieved by utilizing exponential damping relations to consider these changes. The Local Thermal Equilibrium (LTE) (one-energy equation) model is used for the thermal analysis in porous media. In order to investigate the validity of the extended model, laminar and turbulent flow in different cases, fully developed and developing flows, have been considered. For laminar flows, fully developed plane channel flows with one and two porous layers, a channel with a single porous block and partially filled porous channel flows have been examined for the purpose of validating the extra drag terms in the momentum equations. For the validation purpose for turbulent flows in porous media, the extended model has been tested in homogeneous porous media, turbulent porous channel flows, turbulent solid/porous rib channel flows, and repeated turbulent porous baffled channel flows. Results of all laminar cases show excellent qualitative agreements with the available numerical calculations and experimental data. Results of all turbulent cases show that the extended model returns generally satisfactory accuracy through the comparisons with the available data, except for some predictive weaknesses in regions of either impingement or adverse pressure gradients, both of which are largely due the underlying eddy-viscosity model formulation employed. Thus, from all results, it can be confirmed that the extended model is promising for engineering applications.

APA, Harvard, Vancouver, ISO, and other styles

7

Gnanaselvam, Pritheesh. "Modeling Turbulent Dispersion and Deposition of Airborne Particles in High Temperature Pipe Flows." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1598016744932462.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Han, Zhiyi. "The response of turbulent stratified flames to acoustic velocity fluctuations." Thesis, University of Cambridge, 2015. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.708612.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Strömgren, Tobias. "Modelling of turbulent gas-particle flow." Licentiate thesis, KTH, Mechanics, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-4639.

Full text

Abstract:

<p>An Eulerian-Eulerian model for dilute gas-particle turbulent flows is</p><p>developed for engineering applications. The aim is to understand the effect of particles on turbulent flows. The model is implemented in a finite element code which is used to perform numerical simulations. The feedback from the particles on the turbulence and the mean flow of the gas in a vertical channel flow is studied. In particular, the influence of the particle response time and particle volume fraction on the preferential concentration of the particles near the walls, caused by the turbophoretic effect is explored. The study shows that the particle feedback decreases the accumulation of particles on the walls. It is also found that even a low particle volume fraction can have a significant impact on the turbulence and the mean flow of the gas. A model for the particle fluctuating velocity in turbulent gas-particle flow is derived using a set of stochastic differential</p><p>equations. Particle-particle collisions were taken into account. The model shows that the particle fluctuating velocity increases with increasing particle-particle collisions and that increasing particle response times decrease the fluctuating velocity.</p>

APA, Harvard, Vancouver, ISO, and other styles

10

Strömgren, Tobias. "Modelling of turbulent gas-particle flow /." Stockholm : Mekanik, Kungliga Tekniska högskolan, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-4639.

Full text

APA, Harvard, Vancouver, ISO, and other styles

More sources

Books on the topic "Turbulent flow in gas turbines"

1

Lin, Chin-Shun. Numerical calculations of turbulent reacting flow in a gas-turbine combustor. National Aeronautics and Space Administration, 1987.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

2

Nikjooy, Mohammad. On the modelling of non-reactive and reactive turbulent combustor flows. Lewis Research Center, 1987.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

3

Schmidt, Rodney C. Two-equation low-Reynolds-number turbulence modeling of transitional boundary layer flows characteristic of gas turbine blades. Lewis Research Center, 1988.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

4

Astrup, Poul. Turbulent gas-particle flow. Risø National Laboratory, 1992.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

5

Burnett, Mark. Optical instrumentation for fluid flow in gas turbines. typescript, 2000.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

6

P, Astrup. Development of a computer model for stationary turbulent 3-D gas-particle flow: Numerical prediction of a turbulent gas-particle duct flow. Riso Library, 1989.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

7

Arts, T. Three dimensional rotational inviscid flow calculation in axial turbine blade rows. Von Karman Institute, 1985.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

8

Pitts, William M. Mixing in variable density, isothermal turbulent flows and implications for chemically reacting turbulent flows. U.S. Dept. of Commerce, National Bureau of Standards, 1987.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

9

Pitts, William M. Mixing in variable density, isothermal turbulent flows and implications for chemically reacting turbulent flows. U.S. Dept. of Commerce, National Bureau of Standards, 1987.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

10

Gorbis, Z. R. Momentum and heat transfer in turbulent gas-solid flows. Begell House Publishers, 1995.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

More sources

Book chapters on the topic "Turbulent flow in gas turbines"

1

Pope, Kevin, and Greg F. Naterer. "Power Curves and Turbulent Flow Characteristics of Vertical Axis Wind Turbines." In Alternative Energy and Shale Gas Encyclopedia. John Wiley & Sons, Inc., 2016. http://dx.doi.org/10.1002/9781119066354.ch9.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Coupland, J., and C. H. Priddin. "Modelling the Flow and Combustion in a Production Gas Turbine Combustor." In Turbulent Shear Flows 5. Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-71435-1_26.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Böhm, B., D. Geyer, M. A. Gregor, et al. "Advanced Laser Diagnostics for Understanding Turbulent Combustion and Model Validation." In Flow and Combustion in Advanced Gas Turbine Combustors. Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5320-4_4.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

Siegmann, J., G. Becker, J. Michaelis, and M. Schäfer. "Efficient Numerical Schemes for Simulation and Optimization of Turbulent Reactive Flows." In Flow and Combustion in Advanced Gas Turbine Combustors. Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5320-4_10.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

Shimada, Y., B. Thornber, and D. Drikakis. "Large Eddy Simulation of Turbulent Jet Flow in Gas Turbine Combustors." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14139-3_41.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Guessab, Ahmed, and Abdelkader Aris. "Numerical Calculation of Turbulent Reacting Flow in a Gas Turbine Combustion Chamber." In ICREEC 2019. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5444-5_24.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Sultanian, Bijay K. "Axial-Flow Gas Turbines." In Fluid Mechanics and Turbomachinery. CRC Press, 2021. http://dx.doi.org/10.1201/9781003053996-12.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Sultanian, Bijay K. "Radial-Flow Gas Turbines." In Fluid Mechanics and Turbomachinery. CRC Press, 2021. http://dx.doi.org/10.1201/9781003053996-11.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Jakirlić, S., R. Jester-Zürker, G. John-Puthenveettil, B. Kniesner, and C. Tropea. "Computational Modelling of Flow and Scalar Transport Accounting for Near-Wall Turbulence with Relevance to Gas Turbine Combustors." In Flow and Combustion in Advanced Gas Turbine Combustors. Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-5320-4_9.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

Poinsot, Thierry, Jörg Schlüter, Ghislain Lartigue, Laurent Selle, Werner Krebs, and Stefan Hoffmann. "Using Large Eddy Simulations to Understand Combustion Instabilities in Gas Turbines." In IUTAM Symposium on Turbulent Mixing and Combustion. Springer Netherlands, 2002. http://dx.doi.org/10.1007/978-94-017-1998-8_35.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Turbulent flow in gas turbines"

1

Izenson, Michael G., Mark R. Kennedy, and Janaki R. Sirukudi. "Turbulent Flow Computations for Turbine Disk Cavity Flows." In ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1995. http://dx.doi.org/10.1115/95-gt-192.

Full text

Abstract:

Computational Fluid Dynamics (CFD) plays a key role in the design of rim seals for gas turbines because of the detailed information it can provide about the complex flow in the seal region. However, the fidelity of the computed flow depends strongly on the techniques used to model turbulence. We have performed CFD calculations using several different turbulence models and compared the calculations with data from tests in a water rig at rotational Reynolds numbers of up to 6×105. Calculations were performed using the commercial CFD code, FLUENT™ 4.23 (Fluent, 1990). The turbulence models we used were a full Reynolds Stress Model (RSM) and a k-ε model. The calculated flows were compared to test data using two gross flow measurements: (1) differential pressures measured on the stator face, and (2) directions of the flow measured by dye injection on the stator face. The best agreement with test data was achieved using the RSM. We hypothesize that the RSM is superior to the k-ε turbulence model because of its ability to accurately model the highly anisotropic nature of the turbulence near the rotating turbine disk.

APA, Harvard, Vancouver, ISO, and other styles

2

Patel, Kashyap, Chaina Ram, and Vishal Rasaniya. "Numerical Analysis of Turbulent Mixing in Cross Flow Configurations." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2506.

Full text

Abstract:

Abstract The gas turbine combustion chamber is a vital part of a gas turbine engine. Proper mixing of air in the combustor plays an important role in combustion. Increasing mixing rate is an important factor for better combustion efficiency. The injection of air in crossflow is widely studied over the years. The air injected at an angle in upstream direction gives better mixing by colliding with the crossflow. The computational analysis of the injected jet in cross flow is performed with different angles in the upstream direction. The k-omega SST turbulence model was used to investigate the mixing behavior. The air is injected at different angles and observed that with an increase in angle from 60° to 135°, the rate of mixing and turbulent intensity increased. The jet inclination in the upstream direction greatly influenced the mixing behavior. The jet penetration in perpendicular direction was almost the same for 120° and 135°. But there is added penalty in the form of the pressure loss at the angle 135°. So considering the pressure loss and ease of manufacturing the 120° jet inclination is preferable for better mixing among the four cases studied here. The idea of inclining jet in upstream direction can be implemented on the combustor for increased performance and shorter size.

APA, Harvard, Vancouver, ISO, and other styles

3

Sellan, Dhanalakshmi, Raju Murugan, and Saravanan Balusamy. "Experimental and Numerical Analysis of Turbulent Swirl Flow Structure in Double Swirler Burner." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2739.

Full text

Abstract:

Abstract Dynamic and kinematic characteristics of non-reactive turbulent swirl flow studies are significant for optimizing burner design, stability, and validating numerical simulations. The experiments were conducted on unconfined double swirler burner to understand the structure of non-reactive turbulent swirl flow for various inner and outer swirl Reynold’s numbers (Re). The burner is designed with double swirlers, inner and outer; both are medium swirlers with geometric swirl number of 0.8. The instantaneous 3C-2D velocity field in a plane is obtained by using Stereo Particle Image Velocimetry (SPIV) in backward-backward scattering position. In each case, 1000 image pairs are acquired with appropriate calibration and post-processed using cross-correlation and particle tracking technique. Turbulence parameters such as Reynolds stress and turbulence intensity as well as the velocity field of all three components are analyzed for various Re that are useful to understand the effect of turbulent mixing. Numerical study for the same cases are carried out, and experimental results are compared with numerical results. A computational domain contains 1146217 cells are generated for the 3D numerical simulation, and Large Eddy Simulation (LES) approach is used to predict the unsteady behavior of the flow fields. The increase in inner swirl Re increases both axial and azimuthal velocity component, which facilitate mixing in gas turbine application. The inner recirculation zone moves downstream with the rise in inner swirl Re and subsequently increasing the outer swirl Re leads to the operating condition where the blowout may occur.

APA, Harvard, Vancouver, ISO, and other styles

4

Wittig, S., W. Klausmann, B. Noll, and J. Himmelsbach. "Evaporation of Fuel Droplets in Turbulent Combustor Flow." In ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1988. http://dx.doi.org/10.1115/88-gt-107.

Full text

Abstract:

Detailed measurements of a recirculating, droplet charged air flow within a model combustor are compared with predictions based on three different evaporation models. Similar results are obtained with the simplified d2-law, the uniform temperature model and thin skin model for relatively short droplet-heatup phases. Discrepancies, however, are observed under conditions where the droplet heating phase is relatively long, i.e. at low temperature conditions. Extended evaporation models, therefore, are necessary when the ignition performance is to be analysed.

APA, Harvard, Vancouver, ISO, and other styles

5

Gan, Xiaopeng, Muhsin Kilic, and J. Michael Owen. "Flow Between Contra-Rotating Discs." In ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1993. http://dx.doi.org/10.1115/93-gt-286.

Full text

Abstract:

The paper describes a combined experimental and computational study of laminar and turbulent flow between contra-rotating discs. Laminar computations produce Batchelor-type flow: radial outflow occurs in boundary layers on the discs and inflow is confined to a thin shear layer in the mid-plane; between the boundary layers and the shear layer, two contra-rotating cores of fluid are formed. Turbulent computations (using a low-Reynolds-number k-ε turbulence model) and LDA measurements provide no evidence for Batchelor-type flow, even for rotational Reynolds numbers as low as 2.2 × 104. Whilst separate boundary layers are formed on the discs, radial inflow occurs in a single interior core that extends between the two boundary layers; in the core, rotational effects are weak. Although the flow in the core was always found to be turbulent, the flow in the boundary layers could remain laminar for rotational Reynolds numbers up to 1.2 × 105. For the case of a superposed outflow, there is a source region in which the radial component of velocity is everywhere positive; radially outward of this region, the flow is similar to that described above. Although the turbulence model exhibited premature transition from laminar to turbulent flow in the boundary layers, agreement between the computed and measured radial and tangential components of velocity was mainly good over a wide range of nondimensional flow rates and rotational Reynolds numbers.

APA, Harvard, Vancouver, ISO, and other styles

6

Amano, R. S., B. Song, S. Sitarama, and B. Lin. "Predictions of Turbulent Flow in a Turbine Stator/Rotor Passage." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-524.

Full text

Abstract:

Numerical study on a three-dimensional turbulent flow in a turbine stator/rotor passage is presented in this paper. The standard k-ε model was used for the first phase of the turbulence computations. The computations were further extended by employing the full Reynolds-stress closure model (RSM). The computational results obtained using these models were compared in order to investigate the turbulence effect in the near-wall region. The governing equations in a generalized curvilinear coordinate system are discretized by using the SIMPLEC method with non-staggered grids. The oscillations in pressure and velocity due to non-staggered grids are eliminated by using a special interpolation method. The predicted midspan pressure coefficients using the k-ε model and the RSM are compared with the experimental data. It was shown that the present results obtained by using either model are fairly reasonable. Computations were then extended to cover the entire blade-to-blade flow passage, and the three-dimensional effects on pressure and turbulence kinetic energy were evaluated. It was observed that the two turbulence models predict different results for the turbulence kinetic energy. This variation was identified as being related to some non-isotropic turbulence occurring near the blade surface due to the severe acceleration of the flow. It was thus proven that the models based on the RSM give more realistic predictions for highly turbulent cascade flow computations than a Boussinesq viscosity model.

APA, Harvard, Vancouver, ISO, and other styles

7

Langella, Ivan, Johannes Heinze, Thomas Behrendt, Lena Voigt, Nedunchezhian Swaminathan, and Marco Zedda. "Turbulent Flame Shape Switching at Conditions Relevant for Gas Turbines." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-91879.

Full text

Abstract:

Abstract A numerical investigation is conducted in this work to shed light on the reasons leading to different flame configurations in gas turbine combustion chambers of aeronautical interest. Large eddy simulations (LES) with a flamelet-based combustion closure are employed for this purpose to simulate the DLR-AT Big Optical Single Sector (BOSS) rig fitted with a Rolls-Royce developmental lean burn injector. The reacting flow field downstream this injector is sensitive to the intricate turbulent-combustion interaction and exhibits two different configurations: (i) a penetrating central jet leading to an M-shape lifted flame; or (ii) a diverging jet leading to a V-shaped flame. First, the LES results are validated using available BOSS rig measurements, and comparisons show that the numerical approach used is consistent and works well. The turbulent-combustion interaction model terms and parameters are then varied systematically to assess the flame behavior. The influences observed are discussed in the paper from physical and modelling perspectives to develop physical understanding on the flame behavior in practical combustors for both scientific and design purposes.

APA, Harvard, Vancouver, ISO, and other styles

8

Gregory-Smith, D. G., and Th Biesinger. "Turbulence Evaluation Within the Secondary Flow Region of a Turbine Cascade." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-060.

Full text

Abstract:

Three-dimensional turbulent and mean velocity fields have been measured within a large-scale axial turbine cascade. The results indicate a complex turbulent flow field especially within the secondary vortex. The turbulence is shown to he significantly non-isotropic, and the production and dissipation terms in the turbulent kinetic energy equation have been evaluated in order to illustrate the unusual turbulence behaviour. Comparisons with a Navier-Stokes computation indicate areas for improvement in turbulence and transition modelling.

APA, Harvard, Vancouver, ISO, and other styles

9

Martelli, Francesco, and Vittorio Michelassi. "Viscous Flow Calculations in Turbomachinery Channels." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-5.

Full text

Abstract:

An implicit procedure based on the artificial compressibility formulation is presented for the numerical solution of the two-dimensional incompressible steady Navier-Stokes equations in the presence of large separated regions. Turbulence effects are accounted for by the Chien low Reynolds number form of the K-ε turbulence model and the Baldwin-Lomax algebraic expression for turbulent viscosity. The governing equations are written in conservative form and implicitly solved in fully coupled form using the approximate factorization technique. Preliminary tests were carried out in a laminar flow regime to check the accuracy and stability of the method in two-dimensional and cylindrical axisymmetric flow configurations. After testing in laminar and turbulent flow regimes and comparing the two turbulence models, the code was successfully applied to an actual gas turbine diffuser at low Mach numbers.

APA, Harvard, Vancouver, ISO, and other styles

10

Volino, Ralph J. "Wavelet Analysis of Transitional Flow Data Under High Free-Stream Turbulence Conditions." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-289.

Full text

Abstract:

Transitional flow data from boundary layers subject to strong acceleration (K as high as 9×10−6) and high free-stream turbulence (∼8%) were analyzed using wavelet transforms. Wavelet analysis provides the energy content of a signal on both a frequency and instantaneous time basis. It differs from traditional Fourier spectral analysis, which can only provide the spectral energy on a time averaged basis. Instantaneous velocity data from intermittent, transitional boundary layers were segregated into turbulent and non-turbulent zones through conditional sampling. Wavelet analysis was used to determine the frequency content of the velocity fluctuations and turbulent shear stress in the two zones separately. The streamwise velocity fluctuations in the turbulent and non-turbulent zones appeared similar. This was attributed to the effect of the free-stream turbulence, which had the same effects on both zones. The wall-normal fluctuations and turbulent shear stress were of significantly higher magnitude and frequency in the turbulent zone. These results suggest that turbulence models should be based on transport quantities rather than turbulent kinetic energy. The regions just upstream and just downstream of turbulent zones were also analyzed, to check for possible important frequencies leading to the initiation of turbulence or characteristic of the “calm” zone trailing a turbulent spot. No distinct behavior was observed in either of these zones. Uncertainty values associated with the wavelet spectra are high due to the short data records available. Results are shown to be valid in spite of these uncertainties, however longer data records should be acquired in future studies.

APA, Harvard, Vancouver, ISO, and other styles

Reports on the topic "Turbulent flow in gas turbines"

1

Clemens, Noel, and Venkat Raman. Predictive LES Modeling and Validation of High-Pressure Turbulent Flames and Flashback in Hydrogen-enriched Gas Turbines. Office of Scientific and Technical Information (OSTI), 2019. http://dx.doi.org/10.2172/1506058.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

TRUJILLO, STEVEN M., KIM ANN SHOLLENBERGER, TIMOTHY J. O'HERN, THOMAS W. GRASSER, and JOHN R. TORCZYNSKI. A Gas-Solid Riser Experiment for Fundamental Studies of Turbulent Multiphase Flow. Office of Scientific and Technical Information (OSTI), 2001. http://dx.doi.org/10.2172/783085.

Full text

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!