Academic literature on the topic 'Reverse flow annular combustor'
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Journal articles on the topic "Reverse flow annular combustor"
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Suzuki, Y., T. Satoh, M. Kawano, N. Akikawa, and Y. Matsuda. "Combustion Test Results of an Uncooled Combustor With Ceramic Matrix Composite Liner." Journal of Engineering for Gas Turbines and Power 125, no. 1 (2002): 28–33. http://dx.doi.org/10.1115/1.1501916.
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A reverse-flow annular combustor with its casing diameter of 400 mm was developed using an uncooled liner made of a three-dimensional woven ceramic matrix composite. The combustor was tested using the TRDI high-pressure combustor test facility at the combustor maximum inlet and exit temperature of 723 K and 1623 K, respectively. Although both the material and combustion characteristics were evaluated in the test, this report focused on the combustion performance. As the results of the test, the high combustion efficiency and high heat release ratio of 99.9% and 1032 W/m3/Pa were obtained at the design point. The latter figure is approximately twice as high as that of existing reverse-flow annular combustors. Pattern factor was sufficiently low and was less than 0.1. Surface temperatures of the liner wall were confirmed to be higher than the limit of the combustor made of existing heat-resistant metallic materials.
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Stuttaford, P. J., and P. A. Rubini. "Preliminary Gas Turbine Combustor Design Using a Network Approach." Journal of Engineering for Gas Turbines and Power 119, no. 3 (1997): 546–52. http://dx.doi.org/10.1115/1.2817019.
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The preliminary design process of a gas turbine combustor often involves the use of cumbersome, geometry restrictive semi-empirical models. The objective of this analysis is the development of a versatile design tool for gas turbine combustors, able to model all conceivable combustor types. A network approach is developed that divides the flow into a number of independent semi-empirical subflows. A pressure-correction methodology solves the continuity equation and a pressure-drop/flow rate relationship. The development of a full conjugate heat transfer model allows the calculation of flame tube heat loss in the presence of cooling films, annulus heat addition, and flame tube feature heat pick-up. A constrained equilibrium calculation, incorporating mixing and recirculation models, simulates combustion processes. Comparison of airflow results to a well-validated combustor design code showed close agreement. The versatility of the network solver is illustrated with comparisons to experimental data from a reverse flow combustor.
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Syarifudin, Anwar, and Muhammad Agung Bramantya. "Simulasi Numerik Pengaruh Jumlah Fuel Injector dan Dimensi Lubang Liner Ruang Bakar Turbojet 200 N." Journal of Mechanical Design and Testing 4, no. 1 (2022): 32. http://dx.doi.org/10.22146/jmdt.63201.
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Ruang bakar merupakan salah satu komponen terpenting dalam turbojet karena menentukan gaya dorong turbojet. Tantangan pada turbojet kecil adalah menghasilkan pembakaran sempurna pada ruang yang terbatas. Penelitian ini bertujuan mempelajari pengaruh jumlah fuel injector dan lubang liner terhadap temperatur gas dan sisa CO pada outlet ruang bakar turbojet 200 N. Desain ruang bakar yang digunakan adalah reverse flow annular combustion chamber. Metode penelitian ini menggunakan permodelan pembakaran non premixed dan model turbulensi k-ε dengan solver ANSYS Fluent yang memvariasikan jumlah fuel injector dan diameter lubang liner. Model yang akan disimulasikan memiliki 4 buah boundary condition . Batas Inlet-Fuel dengan masukan laju alir kerosin (C12H23) 0.0076 kg/s dan temperatur 293 K. Inlet udara dengan input laju alir udara masuk 0,53kg/s, temperatur udara masuk 407K, batas combustor-wall diasumsikan adiabatik. Batas outlet dengan inputan tekanan 1 atmosfer. Dalam studi ini didapatkan hasil jumlah fuel injector yang optimal berjumlah 8 buah dan penambahan diameter lubang dilution liner akan meningkatkan temperatur dan sisa CO yang tidak terbakar pada outlet. Dapat disimpulkan jumlah fuel injector dan dimensi lubang liner berpengaruh pada kinerja ruang bakar yang selanjutnya pada gaya dorong turbojet.
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Bharani, Sanjeev, S. N. Singh, and D. P. Agrawal. "Effect of swirl on the flow characteristics in the outer annulus of a prototype reverse-flow gas turbine combustor." Experimental Thermal and Fluid Science 25, no. 6 (2001): 337–47. http://dx.doi.org/10.1016/s0894-1777(01)00089-9.
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Canepa, Edward, Pasquale Di Martino, Piergiorgio Formosa, Marina Ubaldi, and Pietro Zunino. "Unsteady Aerodynamics of an Aeroengine Double Swirler Lean Premixing Prevaporizing Burner." Journal of Engineering for Gas Turbines and Power 128, no. 1 (2004): 29–39. http://dx.doi.org/10.1115/1.1924720.
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Lean premixing prevaporizing (LPP) burners represent a promising solution for low-emission combustion in aeroengines. Since lean premixed combustion suffers from pressure and heat release fluctuations that can be triggered by unsteady large-scale flow structures, a deep knowledge of flow structures formation mechanisms in complex swirling flows is a necessary step in suppressing combustion instabilities. The present paper describes a detailed investigation of the unsteady aerodynamics of a large-scale model of a double swirler aeroengine LPP burner at isothermal conditions. A three-dimensional (3D) laser Doppler velocimeter and an ensemble-averaging technique have been employed to obtain a detailed time-resolved description of the periodically perturbed flow field at the mixing duct exit and associated Reynolds stress and vorticity distributions. Results show a swirling annular jet with an extended region of reverse flow near to the axis. The flow is dominated by a strong periodic perturbation, which occurs in all the three components of velocity. Radial velocity fluctuations cause important periodic displacement of the jet and the inner separated region in the meridional plane. The flow, as expected, is highly turbulent. The periodic stress components have the same order of magnitude of the Reynolds stress components. As a consequence the flow-mixing process is highly enhanced. Turbulence acts on a large spectrum of fluctuation frequencies, whereas the large-scale motion influences the whole flow field in an ordered way that can be dangerous for stability in reactive conditions.
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Kadhim, Wael, Dhirgham Alkhafagiy, and Andrew Shires. "Simulation of the flow inside an annular can combustor." International Journal of Engineering & Technology 3, no. 3 (2014): 357. http://dx.doi.org/10.14419/ijet.v3i3.2499.
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In the gas turbine combustion system, the external flows in annuli play one of the key roles in controlling pressure loss, air flow distribution around the combustor liner, and the attendant effects on performance, durability, and stability. This paper describes a computational fluid dynamics (CFD) simulation of the flow in the outer annulus of a can combustor. Validating this simulation was done with experimental results obtained from analyzing the flow inside a can combustor annulus that was used in a Babylon/Iraq gas turbine power station. Pitot static tubes were used to measure the velocity in ten stations in the annular region. By using the velocity profile for comparison, a good agreement between the CFD simulation and experimental work was observed. Nomenclature: R: radius of combustor (mm) r: local radius (mm) Pt: total pressure (Pascal) Ps: static pressure (Pascal) DG: damp gap (mm) X/Dc: axial distance is normalized with the diameter of the casing as the origin. A, B and L: station of measurement and investigated locations. u: local axial velocity U: mass average axial velocity at inlet Keywords: Annulus Flow, Can Combustor, CFD Simulation, Pitot Static Tube, Velocity Profile.
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Joy, J., PC Wang, and SCM Yu. "Effect of geometric modification on flow behaviour and performance of reverse flow combustor." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 4 (2018): 1457–71. http://dx.doi.org/10.1177/0954410017752717.
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Numerical investigation had been performed on the reverse flow combustor of a mini gas turbine engine so as to investigate the performance characteristics of the combustor by means of geometry modifications. In order to enhance the thrust performance of the reverse flow combustor, the baseline combustor (Model A) was previously modified by increasing its chamber volume by 15%, the fuel-air ratio (FAR) by 40% and by raising the injection point density to two (Model B). However, the thrust optimization of the baseline combustor resulted in high combustor exit temperature that could potentially damage the combustor liners. To rectify the adversity of high exit temperature, the combustor cooling effects were achieved by subsequently adding additional passage holes at the dilution zone of the Model B combustor so as to direct the incoming cold flow from the compressor exit towards the outgoing hot flow in the reverse flow combustor (Model C). The commercial software ANSYS Fluent 17.0 was adopted in this study and to solve the turbulence model, Reynolds Averaged Navier–Stokes methodology was adopted by employing standard k-ɛ turbulence model with standard wall function. A probability density function model was generated to introduce the combustion species and a discrete phase Model was employed to specify the kerosene fuel-based injector properties. The numerical results of Model A combustor were validated against the previous experimental results using grid convergence test. The numerical results were observed to be in good agreement with the experimental results. However, ineffective mixing was found to be a setback for the baseline combustor (Model A) indicating the need for combustor performance improvement. The comparative results of the revised combustor model (Model C) showed that better cooling effects at the combustor exit could be achieved by adding supplementary passage holes at the downstream of the combustor outer liner, respectively. The addition of dilution holes also resolved the issue of high pressure loss that was observed in Model A combustor with no significant change in the specific fuel consumption. The present paper confirms that the performance of the reverse flow combustor model could be affected by slight geometric modification. The performance characteristics of the combustor models are presented in terms of thrust, thrust-to-weight ratio, specific fuel consumption, pressure loss and pattern factor.
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Bicen, A. F., D. Tse, and J. H. Whitelaw. "Flow and combustion characteristics of an annular combustor." Combustion and Flame 72, no. 2 (1988): 175–92. http://dx.doi.org/10.1016/0010-2180(88)90117-4.
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Wang, Hongcai, Hongru Fang, Bingqian Lou, Shitu Abubakar, Yuqiang Li, and Lei Meng. "Exploring the Benefits of Annular Rectangular Rib for Enhancing Thermal Efficiency of Nonpremixed Micro-Combustor." Journal of Chemistry 2020 (February 13, 2020): 1–13. http://dx.doi.org/10.1155/2020/9410389.
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Micro-combustor can provide the required thermal energy of micro-thermal photovoltaic (MTPV) systems. The performance of MTPV is greatly affected by the effectiveness of a micro-combustor. In this study, a numerical simulation was conducted to explore the benefits of annular rectangular rib for enhancing the thermal performance of a nonpremixed micro-combustor. Based on the investigations under various rib heights, rib positions, and inlet mass flow rates, it is found that the addition of annular rectangular ribs in the micro-combustor creates a turbulent zone in the combustion chamber, thereby enhancing the heat transfer efficiency between the inner wall of the combustion chamber and the burned gas. The micro-combustor with annular rectangular rib shows a higher and more uniform wall temperature. When the H2 mass flow is 7.438 × 10−8 kg/s and the air mass flow is 2.576 × 10−6 kg/s, the optimum dimensionless rib position is at l = 6/9 and r = 0.4. At this condition, the micro-combustor has the most effective and uniform heat transfer performance and shows significant decreases in entropy generation and exergy destruction. However, the optimum l and r significantly depend on the inlet mass flow of H2/air mixture.
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Bharani, S., S. N. Singh, and D. P. Agrawal. "Flow characteristics in the liner of a reverse-flow gas turbine combustor." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 215, no. 4 (2001): 443–51. http://dx.doi.org/10.1243/0957650011538703.
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Investigation carried out in a plane model of a reverse-flow gas turbine combustor under isothermal flow conditions has shown that the bulk of the flow remains close to the outer liner wall between the rows of primary and dilution holes, while it shifts towards the liner mid-plane after the row of dilution holes. At the combustor outlet, the bulk of the flow remains towards the inner wall of the outlet duct, with a uniform flow distribution. At the outlet of the combustor model, turbulence intensity was approximately three times higher than that at the inlet plane.
Dissertations / Theses on the topic "Reverse flow annular combustor"
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PAPPALARDO, JULIANO. "Reverse Flow Combustor Design for a Flexible Fuel Micro Gas Turbine." Doctoral thesis, Università degli studi di Genova, 2021. http://hdl.handle.net/11567/1047033.
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After the analysis of three tendencies in the energy field: substitution of liquid and
solid fuels by gaseous fuels for electricity production; advent of distributed electricity
generation; and the possibility of integration in fuel-cell hybrid systems for electricity
production, the micro gas turbine comes as the most promising solution. Aiming at
sustainable solutions, the micro gas turbine is intended for flexible fuel utilization,
thus biogas is considered as well as natural gas.
Biogas is produced via anaerobic digestion, the main types of reactors and feedstock are discussed. The resulting biogas composition is presented and besides a
composition of 60% methane, 40% carbon dioxide, the purification for utilization in
gas turbines is also featured.
With the objective of designing a compact reverse flow annular combustor operating with lean pre-mixed flames (for reduced nitrogen oxides emissions), initially
for a 100 kW micro gas turbine, a preliminary design phase has been carried out
where the combustor main dimensions (diameters, lenghts and passage widths) were
determined. Lately it was suggested by the research team the design of a similar
combustor for a 1500 kW MGT, the preliminary design has been adapted and the
refinement phase proceeded.
The design refinement perfomance targets are: low pattern factor (obtained with
proper dilution jets positioning and flow rate); contained liner temperatures (obtained with proper positioning of the splash rings that provide cooling air films) and
low total pressure losses (obtained with a constant optimization of flow passages,
avoiding recirculation and stagnation zones). The combustor should also be able to
burn biogas or natural gas with a flame that does not touch the combustor liner or
interferes with liner cooling. CH4 and CO emissions should also result low.
The design methodology of the refinement phase included four main subjects, the
improvement of a feature in one of them usually has brought a beneficial aspect in
another, these main subjects are: injector improvement (for proper fuel pre-mixing);
primary zone flow adequacy (for proper flame positioning and reduced recirculation
zones in the combustion chamber); cooling adequacy (for the liner temperatures lying
below the safety value of 1150 K) and dilution adequacy (for the pattern factor shall
lie below 0.21).
Tangential injectors were adopted since they allow for a compact combustor and a
reduced number of injectors. The disposition adopted is three injector in an upstream
plane (β1) and three injectors in a downstream plane (β2).
CFD simualations models used are: energy equation; Reynolds-Averaged NavierStokes (RANS) with k − realizable model (since it deals with the presence of
flows with complex secondary features), turbulent kinetic energy production limiter (avoid buildup in stagnation zones) and use of standard wall function (which
limits total number of cells in the domain); Species transport with volumetric reactions with the turbulence-chemistry interaction modeled using Finite-rate/Eddydissipation, the mechanism chosen was methane-air 2-step.
Simulations workflow consisted in non-reactive simulations where fuel-premixing
in the injector could be studied and optimized followed by reactive simulations and
reactive simulation with conjugate heat transfer analysis across the liner walls.
A detailed analysis of results (total pressure, velocity, equivalence ratio, rate
of reaction and temperature fields) for natural gas and biogas utilization has been
produced. The total number of different combustors geometries is sixty-one.
The final combustor model satisfies the project requirements in terms of performance and emissions while respecting the given geometric constrains (based on
turbine dimensions) and boundary conditions.
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Parisi, Valerio. "Large Eddy Simulation of a Stagnation Point Reverse Flow Combustor." Thesis, Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/13995.
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In this study, numerical simulations of a low emission lab-scale non-premixed combustor are conducted and analyzed. The objectives are to provide new insight into the physical phenomena in the SPRF (Stagnation Point Reverse Flow) combustor built in the Georgia Tech Combustion Lab, and to compare three Large Eddy Simulation (LES) combustion models (Eddy Break-Up [EBU], Steady Flamelet [SF] and Linear Eddy Model [LEM]) for non-premixed combustion. The nominal operating condition of the SPRF combustor achieves very low NOx and CO emissions by combining turbulent mixing of exhaust gases with preheated reactants and chemical kinetics. The SPRF numerical simulation focuses on capturing the complex interaction between turbulent mixing and heat release. LES simulations have been carried out for a non-reactive case in order to analyze the turbulent mixing inside the combustor. The LES results have been compared to PIV experimental data and the code has been validated. The dominating features of the operational mode of the SPRF combustor (dilution of hot products into reactants, pre-heating and pre-mixing) have been analyzed, and results from the EBU-LES, SF-LES and LEM-LES simulations have been compared. Analysis shows that the LEM-LES simulation achieves the best agreement with the observed flame structure and is the only model that captures the stabilization processes observed in the experiments. EBU-LES and SF-LES do not predict the correct flow pattern because of the inaccurate modeling of sub-grid scale mixing and turbulence-combustion interaction. Limitations of these two models for this type of combustor are discussed.
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Sedalor, Teddy. "Heat Transfer and Flow Characteristic Study in a Low Emission Annular Combustor." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/32036.
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Modern Dry Low Emissions (DLE) combustors are characterized by highly swirling and
expanding flows that makes the convective heat load on the combustor liner gas side difficult to
predict and estimate. A coupled experimental-numerical study of swirling flow and its effects on
combustor liner heat transfer inside a DLE annular combustor model is presented. A simulated
scaled up annular combustor shell was designed with a generic fuel nozzle provided by Solar
Turbines to create the swirl in the flow. The experiment was simulated with a cold flow and
heated walls. An infrared camera was used to obtain the temperature distribution along the liner
wall. Experimentally measured pressure distributions were compared with the heat transfer
results. The experiment was conducted at various Reynolds Numbers to investigate the effect on
the heat transfer peak locations and pressure distributions. A CFD study was performed using
Fluent and turbulence models and used to corroborate and verify the experimental results.
Results show that the heat transfer enhancement in the annulus has slightly different
characteristics for the concave and convex walls. Results also show a much slower drop in heat
transfer coefficient enhancement with increasing Reynolds number compared to can combustors
from a previous study. An introductory study of the effect of a soft wall on the heat transfer on
the combustor liner is also presented.<br>Master of Science
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Abd, El-Nabi Bassam. "Single Annular Combustor: Experimental investigations of Aerodynamics, Dynamics and Emissions." University of Cincinnati / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1268082767.
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Wang, Liang. "Experimental and Computational Investigation of Thermal-Flow Characteristics of Gas Turbine Reverse-Flow Combustor." ScholarWorks@UNO, 2010. http://scholarworks.uno.edu/td/1212.
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Reverse-flow combustors have been used in heavy land-based gas turbines for many decades. A sheath is typically installed to provide cooling at an expense of large pressure losses, through small jet impingement cooling and strong forced convention channel flow. With the modern advancement in metallurgy and thermal-barrier coating technologies, it may become possible to remove this sheath to recover the pressure losses without melting the combustor chamber. However, without the sheath, the flow inside the dump diffuser may exert nonuniform cooling on the combustion chamber. Therefore, the objective of this project is to investigate the flow pattern, pressure drop, and heat transfer in the dump-diffuser reverse-flow combustor with and without sheath to determine if the sheath could be removed. The investigation was conducted through both experimental and computational simulation. The results show that 3.3% pressure losses could be recovered and the highest wall temperature will increase 18% without the sheath.
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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.
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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.
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Carmack, Andrew Cardin. "Heat Transfer and Flow Measurements in Gas Turbine Engine Can and Annular Combustors." Thesis, Virginia Tech, 2012. http://hdl.handle.net/10919/32466.
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A comparison study between axial and radial swirler performance in a gas turbine can combustor was conducted by investigating the correlation between combustor flow field geometry and convective heat transfer at cold flow conditions for Reynolds numbers of 50,000 and 80,000. Flow velocities were measured using Particle Image Velocimetry (PIV) along the center axial plane and radial cross sections of the flow. It was observed that both swirlers produced a strong rotating flow with a reverse flow core. The axial swirler induced larger recirculation zones at both the backside wall and the central area as the flow exits the swirler, and created a much more uniform rotational velocity distribution. The radial swirler however, produced greater rotational velocity as well as a thicker and higher velocity reverse flow core. Wall heat transfer and temperature measurements were also taken. Peak heat transfer regions directly correspond to the location of the flow as it exits each swirler and impinges on the combustor liner wall.
Convective heat transfer was also measured along the liner wall of a gas turbine annular combustor fitted with radial swirlers for Reynolds numbers 210000, 420000, and 840000. The impingement location of the flow exiting from the radial swirler resulted in peak heat transfer regions along the concave wall of the annular combustor. The convex side showed peak heat transfer regions above and below the impingement area. This behavior is due to the recirculation zones caused by the interaction between the swirlers inside the annulus.<br>Master of Science
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Dunn, Jason. "ON THE NATURE OF THE FLOW IN A SEPARATED ANNULAR DIFFUSER." Master's thesis, University of Central Florida, 2009. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/4101.
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The combustor-diffuser system remains one of the most studied sections of the turbomachine. Most of these investigations are due to the fact that quite a bit of flow diffusion is required in this section as the high speed flow exits the compressor and must be slowed down to enter the combustor. Like any diffusion process there is the chance for the development of an unfavorable adverse pressure gradient that can lead to flow separation; a cause of drastic losses within a turbine. There are two diffusion processes in the combustor-diffuser system: The flow first exits the compressor into a pre-diffuser, or compressor discharge diffuser. This diffuser is responsible for a majority of the pressure recovery. The flow then exits the pre-diffuser by a sudden expansion into the dump diffuser. The dump diffuser comprises the majority of the losses, but is necessary to reduce the fluid velocity within acceptable limits for combustion. The topic of active flow control is gaining interest in the industry because such a technique may be able to alleviate some of the requirements of the dump diffuser. If a wider angle pre-diffuser with separation control were used the fluid velocity would be slowed more within that region without significant losses. Experiments were performed on two annular diffusers to characterize the flow separation to create a foundation for future active flow control techniques. Both diffusers had the same fully developed inlet flow condition, however, the expansion of the two diffusers differed such that one diffuser replicated a typical compressor discharge diffuser found in a real machine while the other would create a naturally separated flow along the outer wall. Both diffusers were tested at two Reynolds numbers, 5x104 and 1x105, with and without a vertical wall downstream of the exit to replicate the dump diffuser that re-directs the flow from the pre-diffuser outlet to the combustor. Static pressure measurements were obtained along the OD and ID wall of the diffusers to determine the recovered pressure throughout the diffuser. In addition to these measurements, tufts were used to visualize the flow. A turbulent CFD model was also created to compare against experimental results. In the end, the results were validated against empirical data as well as the CFD model. It was shown that the location of the vertical wall was directly related to the amount of separation as well as the separation characteristics. These findings support previous work and help guide future work for active flow control in a separated annular diffuser both computationally and experimentally.<br>M.S.A.E.<br>Department of Mechanical, Materials and Aerospace Engineering;<br>Engineering and Computer Science<br>Aerospace Engineering MSAE
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Radhakrishnan, Arun. "Self-sustained combustion of low grade solid fuels in a stagnation-point reverse-flow combustor." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/50275.
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This thesis investigates the use of the Stagnation-Point Reverse-Flow (SPRF) combustor geometry for burning low-grade solid fuels that are attractive for specific industrial applications because of their low cost and on-site availability. These fuels are in general, hard to burn, either because of high moisture and impurity-content, e.g. biomass, or their low-volatiles content, e.g., petroleum-coke. This results in various challenges to the combustor designer, for example reduced flame stability and poor combustion efficiency. Conventional solutions include preheating the incoming flow as well as co-firing with high-grade fuels. The SPRF combustor geometry has been chosen because it was demonstrated to operate stably on standard gaseous and liquid-fuels corresponding to ultra fuel-lean conditions and power densities at atmospheric-pressure around 20-25 MW/m3. Previous studies on the SPRF combustor have proven that the unique, reverse flow-geometry allows entrainment of near-adiabatic products into the incoming reactants, thereby enhancing the reactivity of the mixture. Further, the presence of the stagnation-end created a region of low mean velocities and high levels of unsteadiness and mixing-rates that supported the reaction-zones. In this study, we examine the performance of the SPRF geometry on a specific low grade solid fuel, petroleum coke.
There are three main goals of this thesis. The first goal is the design of a SPRF combustor to operate on solid-fuels based on a design-scaling methodology, as well as demonstration of successful operation corresponding to a baseline condition. The second goal involves understanding the mode of operation of the SPRF combustor on solid-fuels based on visualization studies. The third goal of this thesis is developing and using reduced-order models to better understand and predict the ignition and quasi-steady burning behavior of dispersed-phase particles in the SPRF combustor.
The SPRF combustor has been demonstrated to operate stably on pure-oxygen and a slurry made from water and petroleum-coke, both at the baseline conditions (125 kW, 18 g/s, ~25 µm particles) and higher power-densities and powder sizes. For an overall combustor length less than a meter, combustion is not complete (global combustion efficiency less than 70%). Luminance imaging results indicate the incoming reactant jet ignites and exhibits intense burning at the mid-combustor region, around 15 jet diameters downstream of the inlet, most likely due to enhanced mixing as a result of the highly unsteady velocity field. This roughly corresponds to the location of the reaction zones in the previous SPRF combustors operating on gas and liquid fuels. Planar laser visualization of the reacting flow-field using particle-scattering reveals that ignition of a significant amount of the reactants occurs only after the incoming jet has broken into reactant packets. Post-ignition, these burning packets burn out slowly as they reverse direction and exit the combustor on either side of the central injector. This is unlike the behavior in liquid and gas-fueled operation where the incoming reactants burned across a highly corrugated, thin-flame front. Based on these findings, as well as the results of previous SPRF studies, an idealized model of combustor operation based on a plug flow reactor has been developed. The predictions suggest that fuel-conversion efficiency is enhanced by the combustor operating pressure and lowered by the heat-losses.
Overall, this effort has shown the SPRF geometry is a promising compact-combustor concept for self-sustained operation on low-grade solid-fuels for typical high-pressure applications such as direct steam-generation. Based on these findings, it is recommended that future designs for the specific application previously mentioned have a shorter base-combustor with lower heat-losses and a longer steam-generation section for injection of water.
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Gopalakrishnan, Priya. "Effects of the reacting flowfield on combustion processes in a stagnation point reverse flow combustor." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2008. http://hdl.handle.net/1853/22682.
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Thesis (Ph. D.)--Aerospace Engineering, Georgia Institute of Technology, 2008.<br>Committee Chair: Seitzman, Jerry; Committee Member: Gaeta, Richard; Committee Member: Jagoda, Jeff; Committee Member: Neumeier, Yedidia; Committee Member: Yoda, Minami; Committee Member: Zinn, Ben.
Books on the topic "Reverse flow annular combustor"
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Hu, T. C. J. An experimental and computational investigation of an annular reverse-flow combustor. Institute for Aerospace Studies, University of Toronto, 1990.
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Hu, Tin Cheung John. An experimental and computational investigation of an annular reverse-flow combustor. University of Toronto, 1991.
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United States. National Aeronautics and Space Administration., ed. LDV measurements in an annular combustor model. Purdue University, School of Aeronautics and Astronautics, 1989.
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United States. National Aeronautics and Space Administration., ed. LDV measurements in an annular combustor model. National Aeronautics and Space Administration, 1996.
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United States. National Aeronautics and Space Administration., ed. Laser doppler velocimeter measurements and laser sheet imaging in an annular combustor model. National Aeronautics and Space Administration, 1995.
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United States. National Aeronautics and Space Administration., ed. Concentration measurements in a cold flow model annular combustor using laser induced fluorescence. National Aeronautics and Space Administration, 1996.
Find full textBook chapters on the topic "Reverse flow annular combustor"
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Nema, Pooja, Abhishek Dubey, and Abhijit Kushari. "Investigation of Reverse Flow Slinger Combustor with Methanol." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5996-9_38.
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Di Martino, P., E. Narciso, and G. Cinque. "Numerical Model for Predictions of Reverse Flow Combustor Aerothermal Characteristics." In Aerothermodynamics in Combustors. Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84755-4_24.
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Varol, Gökhan, Gürkan Sarıkaya, Onur Tunçer, and Görkem Öztarlık. "Emissions Prediction of a Reverse Flow Combustor Using Network Models." In Sustainable Aviation. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-34181-1_15.
Full textConference papers on the topic "Reverse flow annular combustor"
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Paskin, M., and W. Acosta. "Compliant metal enhanced convection cooled reverse-flow annular combustor." In 30th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-2710.
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Reddy, K. Sudhakar, D. N. Reddy, and C. M. Vara Prasad. "Experimental Investigations on Isothermal Swirling Flows in a Reverse Flow Annular Gas Turbine Combustor." In ASME Turbo Expo 2005: Power for Land, Sea, and Air. ASMEDC, 2005. http://dx.doi.org/10.1115/gt2005-69111.
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An experimental work was carried out on confined swirling flows under non-combusting conditions in a reverse flow annular gas turbine combustor. Flow measurements with a five hole pitot probe are carried out in a flow apparatus of a geometrical configuration similar to the model of a swirl combustor. Mean flow results are obtained for different flow conditions to determine the effect of swirl on the recirculation zone and the variation of the swirl strength along the axis of the gas turbine combustion chamber. The boundaries of the recirculation region are plotted to compare the size and length of the zone with various swirlers. Minimum flow Reynolds number is required for flow recirculation; the effect of Reynolds number on determining which flow class is present for flow of interest in combustion chamber was investigated. The inlet swirl number is optimized for higher swirl strength and the inlet swirl number for which recirculation completely vanishes is also estimated.
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Suzuki, Yasufumi, Toyoichi Satoh, Manabu Kawano, Naofumi Akikawa, and Yoshihiro Matsuda. "Combustion Test Results of an Uncooled Combustor With Ceramic Matrix Composite Liner." In ASME Turbo Expo 2001: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/2001-gt-0088.
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A reverse-flow annular combustor with its casing diameter of 400 mm was developed using an uncooled liner made of three-dimensional-woven ceramic-matrix composite. The combustor was tested using the TRDI high-pressure combustor test facility at the combustor maximum inlet and exit temperature of 723K and 1623K respectively. Although both the material and combustion characteristics were evaluated in the test, this report focused on the combustion performance. As the results of the test, the high combustion efficiency and high heat release ratio of 99.9% and 1032 W/m3/Pa were obtained at the design point. The latter figure is approximately twice as high as that of existing reverse–flow annular combustors. Pattern factor was sufficiently low and was less than 0.1. Surface temperatures of the liner wall were confirmed to be higher than the limit of the combustor made of existing heat-resistant metallic materials.
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Martino, P. Di, S. Colantuoni, L. Cirillo, and G. Cinque. "CFD Modelling of an Advanced 1600 K Reverse-Flow Combustor." In ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1994. http://dx.doi.org/10.1115/94-gt-468.
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A fully-elliptic three dimensional computational fluid dynamic (CFD) code based on pressure-correction techniques has been used in the design of an advanced turbine single annular reverse-flow combustor (AR1600) under development at Alfa Romeo Avio (ARA). Fuel injection was handled using a Lagrangian liquid droplet spray model coupled to the gas phase equations, which are solved in an Eulerian frame of reference. Turbulent transport is described by the standard k-ε model. The combustion model utilizes a conserved scalar formulation and an assumed shape probability density function to account for chemistry-turbulence interaction. The numerical algorithm employs structured nonorthogonal curvilinear grids, node-centered variable arrangement and Cartesian velocity components. The code was validated on a similar combustor (AR318 turboprop engine of 600 SHP). The numerical results agree well with the test measurements available for this chamber. The aerothermal design of AR1600 (1600K exit temperature) has the same gemetrical constraints of AR318 (tip and root diameters for compressor outlet and turbine inlet), but the lenght is shorter to reduce surface area for less cooling and to utilize the excess air for more efficient mixing and combustion.
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Kapat, J. S., T. Wang, W. R. Ryan, I. S. Diakunchak, and R. L. Bannister. "Cold Flow Experiments in a Sub-Scale Model of the Diffuser-Combustor Section of an Industrial Gas Turbine." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-518.
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This paper describes the experimental facility and flow measurements in a sub-scale, 360-degree model of the diffuser-combustor section of an advanced developmental industrial gas turbine. The experiments were performed under cold flow conditions which can be scaled to actual machine operation through the use of a conventional flow parameter. Wall pressure measurements were used to calculate the static pressure recovery in the annular pre-diffuser. A five-hole probe was used to measure the complex three-dimensional flow in the dump diffuser. Mass-weighted average total pressures were calculated to examine the loss characteristics of the annular and the dump diffuser. The “sink” effect caused by the combustors induces a nonuniform velocity profile and pressure distribution at the exit of the annular pre-diffuser, thereby reducing the effectiveness of the annular pre-diffuser. The outer region of the dump diffuser effectively diffuses the flow while recirculation in other areas of the dump diffuser lowers diffuser effectiveness. Partially nonuniform flow distribution was observed at the entrance to the annular passage between the combustors and the combustor housing (top hat). The existence of circumferential flow in this annular passage tends to increase air flow uniformity into the combustor. Although a specific geometry was selected for the present study, the results provide sufficient generality for improving understanding of the complex flow behaviors in the reverse flow diffuser-combustor sections of industrial gas turbines.
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Hegde, Gajanana B., Bhupendra Khandelwal, Vishal Sethi, and Riti Singh. "Design, Evaluation and Performance Analysis of Staged Low Emission Combustors." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-69215.
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The most uncertain and challenging part in the design of a gas turbine has long been the combustion chamber. There has been large number of experimentations in industries and universities alike to better understand the dynamic and complex processes that occur inside a combustion chamber. This study concentrates on gas turbine combustors as a whole, and formulates a theoretical design procedure for staged combustors in particular. Not much of literatures available currently in public domain provide intensive study on designing staged combustors. The work covers an extensive study of design methods applied in conventional combustor designs, which includes the reverse flow combustor and the axial flow annular combustors. The knowledge acquired from this study is then applied to develop a theoretical design methodology for double staged (radial and axial) low emission annular combustors. Additionally a model combustor is designed for each type; radial and axial staging using the developed methodology. A prediction of the performance for the model combustors is executed. The main conclusion is that the dimensions of model combustors obtained from the developed design methodology are within the feasibility limits. The comparison between the radially staged and the axially staged combustor has yielded the predicted results such as lower NOx prediction for the latter and shorter combustor length for the former. The NOx emission result of the new combustor models are found to be in the range of 50–60ppm. However the predicted NOx results are only very crude and need further detailed study.
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Karuppannan, Srinivasan, Vaibhav Murlidhar Sondur, Gullapalli Sivaramakrishna, Raju D. Navindgi, and N. Muthuveerappan. "CFD Analyses of Combustor-Diffuser System of Marine Gas Turbine Engine." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4739.
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Reverse flow can annular combustor configuration becomes the inevitable option for industrial and marine gas turbine engine, due to its advantages over other configurations. The complexity associated with can annular configuration is optimum design of annular diffuser, as its flow field is dominated by downstream blockage created by transition duct geometry. In the present study, flow behavior in the annular diffuser has been analyzed by simulating realistic downstream combustor liner and transition duct geometry. Flow analysis has been carried out using ANSYS Fluent and turbulence has been modeled using Realizable k-ε model. The diffuser is designed based on G* method, for optimum pressure recovery. Six diffuser configurations have been analyzed by varying the inner wall profile. The effect of parameters on flow field within diffuser and dump region has been studied. Also, the static pressure recovery and total pressure loss coefficient of diffuser is calculated and compared. The results show that the profile of the inner wall and the dump region needs to be tailored to get optimum performance from diffuser.
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Stuttaford, Peter J., and Philip A. Rubini. "Preliminary Gas Turbine Combustor Design Using a Network Approach." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-135.
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The preliminary design process of a gas turbine combustor often involves the use of cumbersome, geometry restrictive semi-empirical models. The objective of this analysis is the development of a versatile design tool for gas turbine combustors, able to model all conceivable combustor types. A network approach is developed which divides the flow into a number of independent semi-empirical sub-flows. A pressure-correction methodology solves the continuity equation and a pressure-drop/flow rate relationship. The development of a full conjugate heat transfer model allows the calculation of flametube heat loss in the presence of cooling films, annulus heat addition, and flametube feature heat pick-up. A constrained equilibrium calculation, incorporating mixing and recirculation models, simulates combustion processes. Comparison of airflow results to a well validated combustor design code showed close agreement. The versatility of the network solver is illustrated with comparisons to experimental data from a reverse flow combustor.
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Lai, Mark K., Robert S. Reynolds, and Jeffrey Armstrong. "CFD-Based, Parametric, Design Tool for Gas Turbine Combustors From Compressor Deswirl Exit to Turbine Inlet." In ASME Turbo Expo 2002: Power for Land, Sea, and Air. ASMEDC, 2002. http://dx.doi.org/10.1115/gt2002-30090.
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Since 1998, the Honeywell Engines & Systems, Combustion & Emissions Group has been developing an advanced, CFD-based, parametric, detailed design-by-analysis tool for gas turbine combustors called Advanced Combustion Tools (ACT). ACT solves the entire flow regime from the compressor deswirl exit to the turbine stator inlet, and can be used for combustor diagnostics, design, and development. ACT is applicable to can, through-flow, and reverse-flow combustors, and accommodates features unique to different combustor designs. The main features of ACT are: 1. Reduction of Analysis Cycle Time: Geometry modeling and grid generation are fully parametric and modular, using an inhouse feature-based technology. Each geometrical feature can be deleted, replaced, added, and modified easily, quickly, and efficiently. 2. Elimination of Inter-Feature Boundary Assumptions: All the complex combustor features, such as wall cooling configuration, details of the air swirler assemblies and fuel atomizer systems, dome-shroud/cowl wall, and splash cooling plate, are considered and fully coupled into the CFD calculations. This allows the plenum and annulus aerodynamics to interact directly with the combustor internal flow. 3. Ease of Use: To reduce setup time and errors and to facilitate parametric studies, ACT is highly customized for engineers. 4. Accurate and Efficient CFD Solutions: Advanced physical submodels of combustion and spray have been implemented. This paper provides an overview and development experiences of ACT. Application of ACT to a through-flow combustor system is presented to illustrate the approach as applied to real-world combustors. Validation of the ACT system, by comparison to test cell data, is in-progress and will be the subject of a future paper.
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Chatterjee, Souvick, Samiran Samanta, Achintya Mukhopadhyay, Koushik Ghosh, and Swarnendu Sen. "Effect of a Confined Outer Air Stream on Instability of an Annular Liquid Sheet Exposed to Gas Flow." In ASME 2012 Gas Turbine India Conference. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gtindia2012-9605.
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A gas turbine combustor will act in a desired way only if its components, specially the fuel injector perform satisfactorily producing fine homogeneous droplets. Stability analysis of liquid, a rich classical fluid mechanics problem, when applied to fuel injector studies can enhance our knowledge leading towards the design of an advanced efficient atomizer. In this work, we analyzed the instability of a swirling annular liquid, exposed to co-flowing inner and outer air streams, by a temporal linear stability analysis using perturbation method. This temporal analysis discusses the effect of liquid Weber number, liquid swirl strength, both inner and outer gas-to-liquid velocity ratio and outer air gas swirl strength on the growth rate of interface instability. Another interesting inclusion in this work is the effect of confinement of the outer air stream which leads to a finite thickness of the outer air stream. Our results show a higher optimum growth rate obtained at a higher axial wave number in the presence of confinement compared to that when the outer air stream extends to infinity. This leads to the formation of smaller droplets which increases the efficiency of atomization. A comparative study between different helical modes revealed that the helical modes are dominant compared to the axisymmetric mode in presence of outer air swirl, whereas reverse phenomenon occurs in its absence.