Journal articles: 'Annular gas turbine combustor'

1

Khandelwal, B., A. Karakurt, V. Sethi, R. Singh, and Z. Quan. "Preliminary design and performance analysis of a low emission aero-derived gas turbine combustor." Aeronautical Journal 117, no. 1198 (2013): 1249–71. http://dx.doi.org/10.1017/s0001924000008848.

Full text

Abstract:

Abstract Modern gas turbine combustor design is a complex task which includes both experimental and empirical knowledge. Numerous parameters have to be considered for combustor designs which include combustor size, combustion efficiency, emissions and so on. Several empirical correlations and experienced approaches have been developed and summarised in literature for designing conventional combustors. A large number of advanced technologies have been successfully employed to reduce emissions significantly in the last few decades. There is no literature in the public domain for providing detailed design methodologies of triple annular combustors. The objective of this study is to provide a detailed method designing a triple annular dry low emission industrial combustor and evaluate its performance, based on the operating conditions of an industrial engine. The design methodology employs semi-empirical and empirical models for designing different components of gas turbine combustors. Meanwhile, advanced DLE methods such as lean fuel combustion, premixed methods, staged combustion, triple annular, multi-passage diffusers, machined cooling rings, DACRS and heat shields are employed to cut down emissions. The design process is shown step by step for design and performance evaluation of the combustor. The performance of this combustor is predicted, it shows that NO x emissions could be reduced by 60%-90% as compared with conventional single annular combustors.

APA, Harvard, Vancouver, ISO, and other styles

2

Sokolov, K. Y., A. G. Tumanovskiy, M. N. Gutnik, A. V. Sudarev, Y. I. Zakharov, and E. D. Winogradov. "Mathematical Modeling of an Annular Gas Turbine Combustor." Journal of Engineering for Gas Turbines and Power 117, no. 1 (1995): 94–99. http://dx.doi.org/10.1115/1.2812787.

Full text

Abstract:

A mathematical model for the description of axisymmetric swirled flow with diffusion combustion is based on numerical solution of the Reynolds equation with a k–W model of turbulence. The results of numerical and experimental investigations of local and general characteristics of flow, heat and mass transfer, combustion, and NOx formation in an annular combustor with opposite swirled air jets are presented. Satisfactory agreement between calculations and experiments is obtained. The dependences of combustor characteristics versus geometric and operational parameters are generalized.

APA, Harvard, Vancouver, ISO, and other styles

3

Kru¨ger, U., J. Hu¨ren, S. Hoffmann, W. Krebs, P. Flohr, and D. Bohn. "Prediction and Measurement of Thermoacoustic Improvements in Gas Turbines With Annular Combustion Systems." Journal of Engineering for Gas Turbines and Power 123, no. 3 (2000): 557–66. http://dx.doi.org/10.1115/1.1374437.

Full text

Abstract:

Environmental compatibility requires low emission burners for gas turbine power plants. In the past, significant progress has been made developing low NOx and CO burners by introducing lean premixed techniques in combination with annular combustion chambers. Unfortunately, these burners often have a more pronounced tendency to produce combustion-driven oscillations than conventional burner designs. The oscillations may be excited to such an extent that the risk of engine failure occurs. For this reason, the prediction of these thermoacoustic instabilities in the design phase of an engine becomes more and more important. A method based on linear acoustic four-pole elements has been developed to predict instabilities of the ring combustor of the 3A-series gas turbines. The complex network includes the whole combustion system starting from both compressor outlet and fuel supply system and ending at the turbine inlet. The flame frequency response was determined by a transient numerical simulation (step-function approach). Based on this method, possible improvements for the gas turbine are evaluated in this paper. First, the burner impedance is predicted theoretically and compared with results from measurements on a test rig for validation of the prediction approach. Next, the burner impedance in a gas turbine combustion system is analyzed and improved thermoacoustically. Stability analyses for the gas turbine combustion system show the positive impact of this improvement. Second, the interaction of the acoustic parts of the gas turbine system has been detuned systematically in circumferential direction of the annular combustion chamber in order to find a more stable configuration. Stability analyses show the positive effect of this measure as well. The results predicted are compared with measurements from engine operation. The comparisons of prediction and measurements show the applicability of the prediction method in order to evaluate the thermoacoustic stability of the combustor as well as to define possible countermeasures.

APA, Harvard, Vancouver, ISO, and other styles

4

Feitelberg, Alan S., Michael D. Starkey, Richard B. Schiefer, et al. "Performance of a Reduced NOx Diffusion Flame Combustor for the MS5002 Gas Turbine." Journal of Engineering for Gas Turbines and Power 122, no. 2 (2000): 301–6. http://dx.doi.org/10.1115/1.483217.

Full text

Abstract:

This paper describes a reduced NOx diffusion flame combustor that has been developed for the MS5002 gas turbine. Laboratory tests have shown that when firing with natural gas, without water or steam injection, NOx emissions from the new combustor are about 40 percent lower than NOx emissions from the standard MS5002 combustor. CO emissions are virtually unchanged at base load, but increase at part load conditions. The laboratory results were confirmed in 1997 by a commercial demonstration test at a British Petroleum site in Prudhoe Bay, Alaska. The standard MS5002 gas turbine is equipped with a conventional, swirl stabilized diffusion flame combustion system. The twelve standard combustors in an MS5002 turbine are cylindrical cans, approximately 27 cm (10.5 in.) in diameter and 112 cm (44 in.) long. A small, annular, vortex generator surrounds the single fuel nozzle that is centered at the inlet to each can. The walls of the cans are louvered for cooling, and contain an array of mixing and dilution holes that provide the air needed to complete combustion and dilute the burned gas to the desired turbine inlet temperature. The new, reduced NOx emissions combustor (referred to as a “lean head end,” or LHE, combustor) retains all of the key features of the conventional combustor; the only significant difference is the arrangement of the mixing and dilution holes in the cylindrical combustor can. By optimizing the number, diameter, and location of these holes, NOx emissions were substantially reduced. The materials of construction, fuel nozzle, and total combustor air flow were unchanged. The differences in NOx emissions between the standard and LHE combustors, as well as the variations in NOx emissions with firing temperature, were well correlated using turbulent flame length arguments. Details of this correlation are also presented. [S0742-4795(00)01602-1]

APA, Harvard, Vancouver, ISO, and other styles

5

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

6

Kelsall, G. J., M. A. Smith, and M. F. Cannon. "Low Emissions Combustor Development for an Industrial Gas Turbine to Utilize LCV Fuel Gas." Journal of Engineering for Gas Turbines and Power 116, no. 3 (1994): 559–66. http://dx.doi.org/10.1115/1.2906856.

Full text

Abstract:

Advanced coal-based power generation systems such as the British Coal Topping Cycle offer the potential for high-efficiency electricity generation with minimum environmental impact. An important component of the Topping Cycle program is the gas turbine, for which development of a combustion system to burn low calorific value coal derived fuel gas, at a turbine inlet temperature of 1260°C (2300°F), with minimum pollutant emissions, is a key R&D issue. A phased combustor development program is underway burning low calorific value fuel gas (3.6-4.1 MJ/m3) with low emissions, particularly NOx derived from fuel-bound nitrogen. The first phase of the combustor development program has now been completed using a generic tubo-annular, prototype combustor design. Tests were carried out at combustor loading and Mach numbers considerably greater than the initial design values. Combustor performance at these conditions was encouraging. The second phase of the program is currently in progress. This will assess, initially, an improved variant of the prototype combustor operating at conditions selected to represent a particular medium sized industrial gas turbine. This combustor will also be capable of operating using natural gas as an auxiliary fuel, to suit the start-up procedure for the Topping Cycle. The paper presents the Phase 1 test program results for the prototype combustor. Design of the modified combustor for Phase 2 of the development program is discussed, together with preliminary combustion performance results.

APA, Harvard, Vancouver, ISO, and other styles

7

Kim, J., M. G. Dunn, A. J. Baran, D. P. Wade, and E. L. Tremba. "Deposition of Volcanic Materials in the Hot Sections of Two Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 115, no. 3 (1993): 641–51. http://dx.doi.org/10.1115/1.2906754.

Full text

Abstract:

This paper reports the results of a series of tests designed to determine the melting and subsequent deposition behavior of volcanic ash cloud materials in modern gas turbine engine combustors and high-pressure turbine vanes. The specific materials tested were Mt. St. Helens ash and a soil blend containing volcanic ash (black scoria) from Twin Mountain, NM. Hot section test systems were built using actual engine combustors, fuel nozzles, ignitors, and high-pressure turbine vanes from an Allison T56 engine can-type combustor and a more modern Pratt and Whitney F-100 engine annular-type combustor. A rather large turbine inlet temperature range can be achieved using these two combustors. The deposition behavior of volcanic materials as well as some of the parameters that govern whether or not these volcanic ash materials melt and are subsequently deposited are discussed.

APA, Harvard, Vancouver, ISO, and other styles

8

YAHATA, Kazunori, Koji MATSUBARA, Hiroyuki KOSHIKIZAWA, and Kazuyuki ABE. "Numerical Analysis of Annular Combustor for Micro Gas Turbine." Proceedings of Conference of Hokuriku-Shinetsu Branch 2018.55 (2018): D031. http://dx.doi.org/10.1299/jsmehs.2018.55.d031.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Fureby, Christer. "LES of a Multi-burner Annular Gas Turbine Combustor." Flow, Turbulence and Combustion 84, no. 3 (2009): 543–64. http://dx.doi.org/10.1007/s10494-009-9236-9.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

Garland, R. V., and P. W. Pillsbury. "Status of Topping Combustor Development for Second-Generation Fluidized Bed Combined Cycles." Journal of Engineering for Gas Turbines and Power 114, no. 1 (1992): 126–31. http://dx.doi.org/10.1115/1.2906294.

Full text

Abstract:

Addition of a fluidized bed combustor to a high-efficiency combined cycle plant enables direct firing of inexpensive run-of-the-mine coal in an environmentally acceptable manner. To attain high thermal efficiencies, coal pyrolysis is included. The low heating value fuel gas from the pyrolyzer is burned in a topping combustion system that boosts gas turbine inlet temperature to state of the art while the pyrolyzer-produced char is burned in the bed. The candidate topping combustor, the multi-annular swirl burner, based on a design by J. M. Bee´r, is presented and discussed. Design requirements differ from conventional gas turbine combustors. The use of hot, vitiated air for cooling and combustion, and the use of low heating value fuel containing ammonia, are two factors that make the design requirements unique. The multi-annular swirl burner contains rich-burn, quick-quench, and lean-burn zones formed aerodynamically rather than the physically separate volumes found in other rich-lean combustors. Although fuel is injected through a centrally located nozzle, the combustion air enters axially through a series of swirlers. Wall temperatures are controlled by relatively thick layers of air entering through the various swirler sections, which allows the combustor to be of all-metal construction rather than the ceramic often used in rich-lean concepts. This 12-in.-dia design utilizes some of the features of the previous 5-in. and 10-in. versions of the multi-annular swirl burner; test results from the previous projects were utilized in the formulation of the test for the present program. In the upcoming tests, vitiated air will be provided to simulate a pressurized fluidized bed effluent. Hot syngas seeded with ammonia will be used to simulate the low-Btu gas produced in the pyrolyzer.

APA, Harvard, Vancouver, ISO, and other styles

11

McGuirk, J. J. "The aerodynamic challenges of aeroengine gas-turbine combustion systems." Aeronautical Journal 118, no. 1204 (2014): 557–99. http://dx.doi.org/10.1017/s0001924000009386.

Full text

Abstract:

Abstract The components of an aeroengine gas-turbine combustor have to perform multiple tasks – control of external and internal air distribution, fuel injector feed, fuel/air atomisation, evaporation, and mixing, flame stabilisation, wall cooling, etc. The ‘rich-burn’ concept has achieved great success in optimising combustion efficiency, combustor life, and operational stability over the whole engine cycle. This paper first illustrates the crucial role of aerodynamic processes in achieving these performance goals. Next, the extra aerodynamic challenges of the ‘lean-burn’ injectors required to meet the ever more stringent NO x emissions regulations are introduced, demonstrating that a new multi-disciplinary and ‘whole system’ approach is required. For example, high swirl causes complex unsteady injector aerodynamics; the threat of thermo-acoustic instabilities means both aerodynamic and aeroacoustic characteristics of injectors and other air admission features must be considered; and high injector mass flow means potentially strong compressor/combustor and combustor/turbine coupling. The paper illustrates how research at Loughborough University, based on complementary use of advanced experimental and computational methods, and applied to both isolated sub-components and fully annular combustion systems, has improved understanding and identified novel ideas for combustion system design.

APA, Harvard, Vancouver, ISO, and other styles

12

Sokolov, K. Y., A. G. Tumanovsky, M. N. Gutnik, A. I. Mechanikov, V. P. Reshitko, and M. I. Grinshtein. "Experimental Investigation of GTE-115 Combustor With Premixed Burner Unit." Journal of Engineering for Gas Turbines and Power 116, no. 3 (1994): 547–53. http://dx.doi.org/10.1115/1.2906854.

Full text

Abstract:

The results of experimental investigation of the basic parameters of one-burner, 1/18 sector of a full-scale annular combustor of the “Turboatom” GTE-115 gas turbine unit are presented. Specifics of fuel burnup and formation of toxic pollutants in premixed combustion using a pilot diffusion burner are presented. Generalized dependences of combustor characteristics versus flow parameters and an optimized algorithm of combustor loading are illustrated.

APA, Harvard, Vancouver, ISO, and other styles

13

Pyo, Yeongmin, Myunggon Yoon, and Daesik Kim. "Combustion Instability Analysis Using Network Model in an Annular Gas Turbine Combustor." Journal of the Korean Society of Propulsion Engineers 22, no. 3 (2018): 72–80. http://dx.doi.org/10.6108/kspe.2018.22.3.072.

Full text

APA, Harvard, Vancouver, ISO, and other styles

14

Leonard, G., and J. Stegmaier. "Development of an Aeroderivative Gas Turbine Dry Low Emissions Combustion System." Journal of Engineering for Gas Turbines and Power 116, no. 3 (1994): 542–46. http://dx.doi.org/10.1115/1.2906853.

Full text

Abstract:

This paper gives the development status of GE’s new aeroderivative premixed combustion system. This system consists of a new fuel staged annular combustor, compressor rear frame, first-stage turbine nozzle, electronic staging controller, and fuel delivery system. Component test results along with a description of the combustion system are presented. This new system will reduce NOx emissions by 90 percent relative to the original aircraft engine combustion system while maintaining low emissions of CO and UHCs. Tests of a LM6000 gas turbine equipped with the new system are planned for early 1994.

APA, Harvard, Vancouver, ISO, and other styles

15

Fox, T. G., and B. C. Schlein. "Full Annular Rig Development of the FT8 Gas Turbine Combustor." Journal of Engineering for Gas Turbines and Power 114, no. 1 (1992): 27–32. http://dx.doi.org/10.1115/1.2906303.

Full text

Abstract:

The results of developmental testing in a high-pressure, full annular combustion section of the FT8 industrial gas turbine are presented. Base power conditions were simulated at approximately 60 percent of burner pressure. All aspects of combustion performance with liquid fuel were investigated, including starting, blowout, exit temperature signature, emissions, smoke, and liner wall temperature. Configurational change were made to improve liner cooling, reduce emissions, adjust pressure loss, and modify exit temperature profile. The effects of water injection on emissions and performance were evaluated in the final test run. Satisfactory performance in all areas was demonstrated with further refinements to be carried out during developmental engine testing.

APA, Harvard, Vancouver, ISO, and other styles

16

Agrawal, A. K., J. S. Kapat, and T. T. Yang. "An Experimental/Computational Study of Airflow in the Combustor–Diffuser System of a Gas Turbine for Power Generation." Journal of Engineering for Gas Turbines and Power 120, no. 1 (1998): 24–33. http://dx.doi.org/10.1115/1.2818084.

Full text

Abstract:

This paper presents an experimental/computational study of cold flow in the combustor–diffuser system of industrial gas turbines employing can-annular combustors and impingement-cooled transition pieces. The primary objectives were to determine flow interactions between the prediffuser and dump chamber, to evaluate circumferential flow nonuniformities around transition pieces and combustors, and to identify the pressure loss mechanisms. Flow experiments were conducted in an approximately one-third geometric scale, 360-deg annular test model simulating practical details of the prototype including the support struts, transition pieces, impingement sleeves, and can-annular combustors. Wall static pressures and velocity profiles were measured at selected locations in the test model. A three-dimensional computational fluid dynamic analysis employing a multidomain procedure was performed to supplement the flow measurements. The complex geometric features of the test model were included in the analysis. The measured data correlated well with the computations. The results revealed strong interactions between the prediffuser and dump chamber flows. The prediffuser exit flow was distorted, indicating that the uniform exit conditions typically assumed in the diffuser design were violated. The pressure varied circumferentially around the combustor casing and impingement sleeve. The circumferential flow nonuniformities increased toward the inlet of the turbine expander. A venturi effect causing flow to accelerate and decelerate in the dump chamber was also identified. This venturi effect could adversely affect impingement cooling of the transition piece in the prototype. The dump chamber contained several recirculation regions contributing to the losses. Approximately 1.2 dynamic head at the prediffuser inlet was lost in the combustor–diffuser, much of it in the dump chamber where the fluid passed though narrow pathways. A realistic test model and three-dimensional analysis used in this study provided new insight into the flow characteristics of practical combustor–diffuser systems.

APA, Harvard, Vancouver, ISO, and other styles

17

Crocker, D. S., D. Nickolaus, and C. E. Smith. "CFD Modeling of a Gas Turbine Combustor From Compressor Exit to Turbine Inlet." Journal of Engineering for Gas Turbines and Power 121, no. 1 (1999): 89–95. http://dx.doi.org/10.1115/1.2816318.

Full text

Abstract:

Gas turbine combustor CFD modeling has become an important combustor design tool in the past few years, but CFD models are generally limited to the flow field inside the combustor liner or the diffuser/combustor annulus region. Although strongly coupled in reality, the two regions have rarely been coupled in CFD modeling. A CFD calculation for a full model combustor from compressor diffuser exit to turbine inlet is described. The coupled model accomplishes the following two main objectives: (1) implicit description of flow splits and flow conditions for openings into the combustor liner, and (2) prediction of liner wall temperatures. Conjugate heat transfer with nonluminous gas radiation (appropriate for lean, low emission combustors) is utilized to predict wall temperatures compared to the conventional approach of predicting only near wall gas temperatures. Remaining difficult issues such as generating the grid, modeling Swirled vane passages, and modeling effusion cooling are also discussed.

APA, Harvard, Vancouver, ISO, and other styles

18

Vermes, G., L. E. Barta, and J. M. Bee´r. "Low NOx Emission From an Ambient Pressure Diffusion Flame Fired Gas Turbine Cycle (APGC)." Journal of Engineering for Gas Turbines and Power 125, no. 1 (2002): 46–50. http://dx.doi.org/10.1115/1.1520160.

Full text

Abstract:

The prospects of reduced NOx emission, improved efficiency, stable, and oscillation-free combustion, and reduced construction costs achieved by an “Inverted Brayton Cycle” applied to midsize (0.5 to 5.0 MWe) power plants are discussed. In this cycle, the combustion products of an atmospheric pressure combustor are expanded in the gas turbine to subatmospheric pressure and following heat extraction are compressed back to slightly above the atmospheric, sufficient to enable a controlled fraction of the exhaust gas to be recirculated to the combustor. Due to the larger volume flow rate of the gas, the polytropic efficiency of both the turbine and compressor of this small machine is increased. Because of the low operating pressure and flue gas recirculation, both of which are instrumental to low NOx formation, the combustor can be operated in the diffusion flame mode; this, on the other hand, assures good flame stability and oscillation-free combustion over wide ranges of the operating variables. For the task of obtaining very low NOx formation, the well-tested multi annular swirl burner (MASB) is chosen. Recent computational and experimental development of the MASB by Siemens-Westinghouse as a topping combustor is discussed. It is shown that the MASB operated in rich-quench-lean mode is capable of single-digit NOx emission. The emissions are further lowered in the APGC by ambient pressure combustion, and by the injection of the recirculated gas in the quench zone of the combustor. Results of a computational optimization study of the ambient pressure gas turbine cycle (APGC) are presented.

APA, Harvard, Vancouver, ISO, and other styles

19

Gordon, R., and Y. Levy. "Optimization of Wall Cooling in Gas Turbine Combustor Through Three-Dimensional Numerical Simulation." Journal of Engineering for Gas Turbines and Power 127, no. 4 (2005): 704–23. http://dx.doi.org/10.1115/1.1808432.

Full text

Abstract:

This paper is concerned with improving the prediction reliability of CFD modeling of gas turbine combustors. CFD modeling of gas turbine combustors has recently become an important tool in the combustor design process, which till now routinely used the old “cut and try” design practice. Improving the prediction capabilities and reliability of CFD methods will reduce the cycle time between idea and a working product. The paper presents a 3D numerical simulation of the BSE Ltd. YT-175 engine combustor, a small, annular, reversal flow type combustor. The entire flow field is modeled, from the compressor diffuser to turbine inlet. The model includes the fuel nozzle, the vaporizer solid walls, and liner solid walls with the dilution holes and cooling louvers. A periodic 36 deg sector of the combustor is modeled using a hybrid structured/unstructured multiblock grid. The time averaged Navier-Stokes (N-S) equations are solved, using the k-ε turbulence model and the combined time scale (COMTIME)/PPDF models for modeling the turbulent kinetic energy reaction rate. The vaporizer and liner walls’ temperature is predicted by the “conjugate heat transfer” methodology, based on simultaneous solution of the heat transfer equations for the vaporizer and liner walls, coupled with the N-S equations for the fluids. The calculated results for the mass flux passing through the vaporizer and various holes and slots of the liner walls, as well as the jet angle emerging from the liner dilution holes, are in very good agreement with experimental measurements. The predicted location of the liner wall hot spots agrees well with the position of deformations and cracks that occurred in the liner walls during test runs of the combustor. The CFD was used to modify the YT-175 combustion chamber to eliminate structural problems, caused by the liner walls overheating, that were observed during its development.

APA, Harvard, Vancouver, ISO, and other styles

20

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

21

Farisco, Federica, Lukasz Panek, and Jim BW Kok. "Thermo-acoustic cross-talk between cans in a can-annular combustor." International Journal of Spray and Combustion Dynamics 9, no. 4 (2017): 452–69. http://dx.doi.org/10.1177/1756827717716373.

Full text

Abstract:

Thermo-acoustic instabilities in gas turbine engines are studied to avoid engine failure. Compared to the engines with annular combustors, the can-annular combustor design should be less vulnerable to acoustic burner-to-burner interaction, since the burners are acoustically coupled only by the turbine stator stage and the plenum. However, non-negligible cross-talk between neighboring cans has been observed in measurements in such machines. This study is focused on the analysis of the acoustic interaction between the cans. Simplified two-dimensional (2D) and three-dimensional (3D) equivalent systems representing the corresponding engine alike turbine design are investigated. Thermo-acoustic instabilities are reproduced using a forced response approach. Compressible large eddy simulation based on the open source computational fluid dynamics OpenFOAM framework is used applying accurate boundary conditions for the flow and the acoustics. A study of the reflection coefficient and of the transfer function between the cans has been performed. Comparisons between 2D and 3D equivalent configurations have been evaluated.

APA, Harvard, Vancouver, ISO, and other styles

22

Tolpadi, A. K. "Calculation of Two-Phase Flow in Gas Turbine Combustors." Journal of Engineering for Gas Turbines and Power 117, no. 4 (1995): 695–703. http://dx.doi.org/10.1115/1.2815455.

Full text

Abstract:

A method is presented for computing steady two-phase turbulent combusting flow in a gas turbine combustor. The gas phase equations are solved in an Eulerian frame of reference. The two-phase calculations are performed by using a liquid droplet spray combustion model and treating the motion of the evaporating fuel droplets in a Lagrangian frame of reference. The numerical algorithm employs nonorthogonal curvilinear coordinates, a multigrid iterative solution procedure, the standard k-ε turbulence model, and a combustion model comprising an assumed shape probability density function and the conserved scalar formulation. The trajectory computation of the fuel provides the source terms for all the gas phase equations. This two-phase model was applied to a real piece of combustion hardware in the form of a modern GE/SNECMA single annular CFM56 turbofan engine combustor. For the purposes of comparison, calculations were also performed by treating the fuel as a single gaseous phase. The effect on the solution of two extreme situations of the fuel as a gas and initially as a liquid was examined. The distribution of the velocity field and the conserved scalar within the combustor, as well as the distribution of the temperature field in the reaction zone and in the exhaust, were all predicted with the combustor operating both at high-power and low-power (ground idle) conditions. The calculated exit gas temperature was compared with test rig measurements. Under both low and high-power conditions, the temperature appeared to show an improved agreement with the measured data when the calculations were performed with the spray model as compared to a single-phase calculation.

APA, Harvard, Vancouver, ISO, and other styles

23

Cook, C. S., J. C. Corman, and D. M. Todd. "System Evaluation and LBTU Fuel Combustion Studies for IGCC Power Generation." Journal of Engineering for Gas Turbines and Power 117, no. 4 (1995): 673–77. http://dx.doi.org/10.1115/1.2815452.

Full text

Abstract:

The integration of gas turbines and combined cycle systems with advances in coal gasification and gas stream cleanup systems will result in economically viable IGCC systems. Optimization of IGCC systems for both emission levels and cost of electricity is critical to achieving this goal. A technical issue is the ability to use a wide range of coal and petroleum-based fuel gases in conventional gas turbine combustor hardware. In order to characterize the acceptability of these syngases for gas turbines, combustion studies were conducted with simulated coal gases using full-scale advanced gas turbine (7F) combustor components. It was found that NOx emissions could be correlated as a simple function of stoichiometric flame temperature for a wide range of heating values while CO emissions were shown to depend primarily on the H2 content of the fuel below heating values of 130 Btu/scf (5125 kJ/NM3) and for H2/CO ratios less than unity. The test program further demonstrated the capability of advanced can-annular combustion systems to burn fuels from air-blown gasifiers with fuel lower heating values as low as 90 Btu/scf (3548 kJ/NM3) at 2300°F (1260°C) firing temperature. In support of ongoing economic studies, numerous IGCC system evaluations have been conducted incorporating a majority of the commercial or near-commercial coal gasification systems coupled with “F” series gas turbine combined cycles. Both oxygen and air-blown configurations have been studied, in some cases with high and low-temperature gas cleaning systems. It has been shown that system studies must start with the characteristics and limitations of the gas turbine if output and operating economics are to be optimized throughout the range of ambient operating temperature and load variation.

APA, Harvard, Vancouver, ISO, and other styles

24

Marudhappan, Raja, Chandrasekhar Udayagiri, and Koni Hemachandra Reddy. "Combustion chamber design and reaction modeling for aero turbo-shaft engine." Aircraft Engineering and Aerospace Technology 91, no. 1 (2018): 94–111. http://dx.doi.org/10.1108/aeat-10-2017-0217.

Full text

Abstract:

Purpose The purpose of this paper is to formulate a structured approach to design an annular diffusion flame combustion chamber for use in the development of a 1,400 kW range aero turbo shaft engine. The purpose is extended to perform numerical combustion modeling by solving transient Favre Averaged Navier Stokes equations using realizable two equation k-e turbulence model and Discrete Ordinate radiation model. The presumed shape β-Probability Density Function (β-PDF) is used for turbulence chemistry interaction. The experiments are conducted on the real engine to validate the combustion chamber performance. Design/methodology/approach The combustor geometry is designed using the reference area method and semi-empirical correlations. The three dimensional combustor model is made using a commercial software. The numerical modeling of the combustion process is performed by following Eulerian approach. The functional testing of combustor was conducted to evaluate the performance. Findings The results obtained by the numerical modeling provide a detailed understanding of the combustor internal flow dynamics. The transient flame structures and streamline plots are presented. The velocity profiles obtained at different locations along the combustor by numerical modeling mostly go in-line with the previously published research works. The combustor exit temperature obtained by numerical modeling and experiment are found to be within the acceptable limit. These results form the basis of understanding the design procedure and opens-up avenues for further developments. Research limitations/implications Internal flow and combustion dynamics obtained from numerical simulation are not experimented owing to non-availability of adequate research facilities. Practical implications This study contributes toward the understanding of basic procedures and firsthand experience in the design aspects of combustors for aero-engine applications. This work also highlights one of the efficient, faster and economical aero gas turbine annular diffusion flame combustion chamber design and development. Originality/value The main novelty in this work is the incorporation of scoops in the dilution zone of the numerical model of combustion chamber to augment the effectiveness of cooling of combustion products to obtain the desired combustor exit temperature. The use of polyhedral cells for computational domain discretization in combustion modeling for aero engine application helps in achieving faster convergence and reliable predictions. The methodology and procedures presented in this work provide a basic understanding of the design aspects to the beginners working in the gas turbine combustors particularly meant for turbo shaft engines applications.

APA, Harvard, Vancouver, ISO, and other styles

25

Bicen, A. F., M. Senda, and J. H. Whitelaw. "Scalar Characteristics of Combusting Flow in a Model Annular Combustor." Journal of Engineering for Gas Turbines and Power 111, no. 1 (1989): 90–96. http://dx.doi.org/10.1115/1.3240233.

Full text

Abstract:

Temperature and species concentration measurements have been obtained in a model combustor operating at an inlet temperature of 515 K and atmospheric pressure and are reported and discussed. The model comprises two rectangular sectors representing the primary and upper dilution zones of an annular combustor used in small gas-turbine engines. Natural gas (94 percent CH4) was used as fuel and was delivered through a T-vaporizer at rates that led to air-fuel ratios of 29 and 50, similar to those of take-off and ground-idle conditions, respectively. Temperatures were obtained at the exit of the combustor using fine-wire thermocouples and mean concentrations of major species were obtained in the primary zone and at the exit on a dry basis by gas sampling and analysis. The results show that the 200 K increase in inlet air temperature reduces the pattern factor from 0.55 to 0.3 and increases the combustion efficiency from 69 to 94 percent with the air-fuel ratio of 29. The higher air-fuel ratio improves the combustion efficiency to 97.6 percent but results in a worse pattern factor of 0.48. The results confirm the need for consideration of the rate-controlled CO → CO2 reaction in the dilution zone if CO emission is to be calculated correctly and temperatures are to be within 150 K. Examination of temperatures obtained from a local enthalpy balance shows that they are higher than measurements obtained with preheat, in contrast to a similar comparison without preheat.

APA, Harvard, Vancouver, ISO, and other styles

26

McGuirk, J., and J. M. L. M. Palma. "Calculations of the dilution system in an annular gas turbine combustor." AIAA Journal 30, no. 4 (1992): 963–72. http://dx.doi.org/10.2514/3.11015.

Full text

APA, Harvard, Vancouver, ISO, and other styles

27

Zhao, J. X., and Y. B. Lai. "Numerical study of an annular gas turbine combustor with dump diffuser." Journal of Thermal Science 8, no. 1 (1999): 59–64. http://dx.doi.org/10.1007/s11630-999-0025-5.

Full text

APA, Harvard, Vancouver, ISO, and other styles

28

Solanki, H. K., D. B. Kulshreshtha, and N. R. Chaudhari. "Low NOx Annular Type Combustor for 20 kW Gas Turbine Engine." Journal of The Institution of Engineers (India): Series C 101, no. 6 (2020): 1035–42. http://dx.doi.org/10.1007/s40032-020-00610-6.

Full text

APA, Harvard, Vancouver, ISO, and other styles

29

Cowell, L. H., and K. O. Smith. "Development of a Liquid-Fueled, Lean-Premixed Gas Turbine Combustor." Journal of Engineering for Gas Turbines and Power 115, no. 3 (1993): 554–62. http://dx.doi.org/10.1115/1.2906743.

Full text

Abstract:

Development of a lean-premixed, liquid-fueled combustor is in progress to achieve ultra-low NOx emissions at typical gas turbine operating conditions. A filming fuel injector design was tested on a bench scale can combustor to evaluate critical design and operating parameters for low-emissions performance. Testing was completed using No. 2 diesel. Key design variables tested include premixing length, swirler angle, injector centerbody diameter, and reduced liner cooling. NOx emissions below 12 ppmv at 9 bar pressure were measured. Corresponding CO levels were 50 ppmv. An optimized injector design was fabricated for testing in a three injector sector of an annular combustor. Operating parameters and test results are discussed in the paper.

APA, Harvard, Vancouver, ISO, and other styles

30

Boies, Adam M., Marc E. J. Stettler, Jacob J. Swanson, et al. "Particle Emission Characteristics of a Gas Turbine with a Double Annular Combustor." Aerosol Science and Technology 49, no. 9 (2015): 842–55. http://dx.doi.org/10.1080/02786826.2015.1078452.

Full text

APA, Harvard, Vancouver, ISO, and other styles

31

Hataysal, Seyfettin, and Ahmet Yozgatligil. "A coupled flow and chemical reactor network model for predicting gas turbine combustor performance." Thermal Science 24, no. 3 Part B (2020): 1977–89. http://dx.doi.org/10.2298/tsci180602246h.

Full text

Abstract:

Gas turbine combustor performance was explored by utilizing a 1-D flow network model. To obtain the preliminary performance of combustion chamber, three different flow network solvers were coupled with a chemical reactor network scheme. These flow solvers were developed via simplified, segregated and direct solutions of the nodal equations. Flow models were utilized to predict the flow field, pressure, density and temperature distribution inside the chamber network. The network model followed a segregated flow and chemical network scheme, and could supply information about the pressure drop, nodal pressure, average temperature, species distribution, and flow split. For the verification of the model?s results, analyses were performed using CFD on a seven-stage annular test combustor from TUSAS Engine Industries, and the results were then compared with actual performance tests of the combustor. The results showed that the preliminary performance predictor code accurately estimated the flow distribution. Pressure distribution was also consistent with the CFD results, but with varying levels of conformity. The same was true for the average temperature predictions of the inner combustor at the dilution and exit zones. However, the reactor network predicted higher elemental temperatures at the entry zones.

APA, Harvard, Vancouver, ISO, and other styles

32

Döbbeling, Klaus, Jaan Hellat, and Hans Koch. "25 Years of BBC/ABB/Alstom Lean Premix Combustion Technologies." Journal of Engineering for Gas Turbines and Power 129, no. 1 (2005): 2–12. http://dx.doi.org/10.1115/1.2181183.

Full text

Abstract:

The paper will show the development of lean premix combustion technologies in BBC, ABB, and Alstom gas turbines. Different technologies have been developed and applied in Brown Boveri Company (BBC) before 1990. Considerable improvements with respect to NOx emissions as compared to gas turbines with a single combustor and a single diffusion burner for liquid and gaseous fuel have been achieved with burners with extended premixing sections and with multi-injection burners for annular combustors. Between 1990 and 2005, burners with short but effective premixing zones (EV burners: environmentally friendly V-shaped burners) have been implemented in all new gas turbines of the ABB (and later Alstom) fleet with NOx levels well below 25 vppmd (@15% O2). In addition to this, three variants of premix technologies have been successfully developed and deployed into Alstom GT engines: the sequential EV burners—a technology that allows premixing of natural gas and oil into a hot exhaust stream to reheat the exhaust gases of a first high-pressure turbine; the MBtu EV burners that are used to burn syngas in a premix flame with low NOx emissions; and the advanced EV burners (AEV) that are capable to prevaporize and premix liquid fuel prior to combustion and burn it with very low NOx emissions without water injection. The paper will give an overview of these technologies and their usage in Alstom gas turbines over the last 25years.

APA, Harvard, Vancouver, ISO, and other styles

33

Brophy, Chris, and Gabriel Roy. "Benefits and Challenges of Pressure-Gain Combustion Systems for Gas Turbines." Mechanical Engineering 131, no. 03 (2009): 54–55. http://dx.doi.org/10.1115/1.2009-mar-8.

Full text

Abstract:

This article discusses benefits and challenges of Pressure-Gain Combustion Systems for Gas Turbines. The article also highlights that one approach to substantially improve gas turbine thermal efficiency is to replace the nearly constant pressure combustion process with some form of pressure-gain heat release such as either a constant volume or detonative mode of combustion. These systems commonly possess some form of rotating inlet valve design to control the filling process for an annular array of combustors and maintain the appropriate amount of inlet isolation. Although evaluation of turbine life and performance needs to continue, turbine efficiencies approaching values comparable to those of steady-state operation have been reported. The article concludes that the collaborative efforts, such as listed in the article, are ultimately required in times of reduced funding for continued technology development. Even with the risks and challenges associated with this technology, a high payoff potential exists with hybrid gas turbine architectures.

APA, Harvard, Vancouver, ISO, and other styles

34

Fureby, C. "Large eddy simulation modelling of combustion for propulsion applications." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 367, no. 1899 (2009): 2957–69. http://dx.doi.org/10.1098/rsta.2008.0271.

Full text

Abstract:

Predictive modelling of turbulent combustion is important for the development of air-breathing engines, internal combustion engines, furnaces and for power generation. Significant advances in modelling non-reactive turbulent flows are now possible with the development of large eddy simulation (LES), in which the large energetic scales of the flow are resolved on the grid while modelling the effects of the small scales. Here, we discuss the use of combustion LES in predictive modelling of propulsion applications such as gas turbine, ramjet and scramjet engines. The LES models used are described in some detail and are validated against laboratory data—of which results from two cases are presented. These validated LES models are then applied to an annular multi-burner gas turbine combustor and a simplified scramjet combustor, for which some additional experimental data are available. For these cases, good agreement with the available reference data is obtained, and the LES predictions are used to elucidate the flow physics in such devices to further enhance our knowledge of these propulsion systems. Particular attention is focused on the influence of the combustion chemistry, turbulence–chemistry interaction, self-ignition, flame holding burner-to-burner interactions and combustion oscillations.

APA, Harvard, Vancouver, ISO, and other styles

35

Ghirardo, G., M. P. Juniper, and J. P. Moeck. "Weakly nonlinear analysis of thermoacoustic instabilities in annular combustors." Journal of Fluid Mechanics 805 (September 16, 2016): 52–87. http://dx.doi.org/10.1017/jfm.2016.494.

Full text

Abstract:

Rotationally symmetric annular combustors are of practical importance because they generically resemble combustion chambers in gas turbines, in which thermoacoustically driven oscillations are a major concern. We focus on azimuthal thermoacoustic oscillations and model the fluctuating heat release rate as being dependent only on the local pressure in the combustion chamber. We study the dynamics of the annular combustor with a finite number of compact flames equispaced around the annulus, and characterize the flames’ response with a describing function. We discuss the existence, amplitude and the stability of standing and spinning waves, as a function of: (i) the number of the burners; (ii) the acoustic damping in the chamber; (iii) the flame response. We present the implications for industrial applications and the future direction of investigations. We then present as an example the first theoretical study of thermoacoustic triggering in annular combustors, which shows that rotationally symmetric annular chambers that are thermoacoustically unstable do not experience only stable spinning solutions, but can also experience stable standing solutions. We finally test the theory on one experiment with good agreement.

APA, Harvard, Vancouver, ISO, and other styles

36

Sarangi, Niranjan, S. K. Panigrahi, and U. Chandrasekhar. "Fatigue Life Evaluation of an Annular Combustor Casing of a Gas Turbine Engine." Journal of Testing and Evaluation 42, no. 3 (2014): 20130031. http://dx.doi.org/10.1520/jte20130031.

Full text

APA, Harvard, Vancouver, ISO, and other styles

37

Wang, Weihao, Weiguang Huang, Yun Cao, and Chuang Gao. "Atmospheric Test and Numerical Models Assessment of Annular Combustor on ZK2000 Gas Turbine." Journal of Thermal Science 27, no. 6 (2018): 516–26. http://dx.doi.org/10.1007/s11630-018-1018-z.

Full text

APA, Harvard, Vancouver, ISO, and other styles

38

Rizk, N. K., and H. C. Mongia. "Semianalytical Correlations for NOx, CO, and UHC Emissions." Journal of Engineering for Gas Turbines and Power 115, no. 3 (1993): 612–19. http://dx.doi.org/10.1115/1.2906750.

Full text

Abstract:

To meet the future goals of reduced emissions produced by gas turbine combustors, a better understanding of the process of formation of various pollutants is required. Both empirical and analytical approaches are used to provide the exhaust concentrations of pollutants of interest such as NOx, CO, and unburned hydrocarbon with varying degrees of success. In the present investigation, an emission model that simulates the combustor by a number of reactors representing various combustion zones is proposed. A detailed chemical kinetic scheme was used to provide a fundamental basis for the derivation of a number of expressions that simulate the reaction scheme. The model addresses the combined effects of spray evaporation and mixing in the reaction zone. The model validation included the utilization of a large data base obtained for an annular combustor of a modern turbopropulsion engine. In addition to the satisfactory agreement with the measurements, the model provided insight into the regions within the combustor that could be responsible for the excessive formation of emissions. Methods to reduce the emissions may be implemented in light of such information.

APA, Harvard, Vancouver, ISO, and other styles

39

Gao, Huanhuan, Zaiguo Fu, Zhuoxiong Zeng, Jiang Liu, and Peifen Weng. "Effects of Swirling Strength of the Premixed Gas Flow on Pollutant Emission in a Heavy-Duty Gas Turbine." E3S Web of Conferences 118 (2019): 04038. http://dx.doi.org/10.1051/e3sconf/201911804038.

Full text

Abstract:

The combustion process and pollutant emission of an annular combustion chamber for a heavy-duty gas turbine were investigated by numerical method. The realizable k-ε model and finite rate/eddy dissipation model were adopted for calculations of turbulence and combustion. The effects of different swirling numbers of the double-swirler inlet on the temperature distribution and the thermal NOx formation in the combustion chamber were analyzed. The results show that the change of the swirling number of the outer swirling flow has a greater influence on the generation of the thermal NOx when compared with that of the inner swirling flow. The maximum average temperature of the central cross section of the combustor does not exceed 1760K. The average mass fraction of the generated thermal NOx at the exit decreases with the increasing outer swirling number. When the outer swirling number is less than 0.8, the generation of the thermal NOx is severe at the side wall of the combustion chamber.

APA, Harvard, Vancouver, ISO, and other styles

40

Domeracki, W. F., T. E. Dowdy, and D. M. Bachovchin. "Topping Combustor Status for Second-Generation Pressurized Fluidized Bed Cycle Application." Journal of Engineering for Gas Turbines and Power 119, no. 1 (1997): 27–33. http://dx.doi.org/10.1115/1.2815558.

Full text

Abstract:

Second-generation Pressurized Fluidized Bed (PFB) combined cycles employ topping combustion to raise the turbine inlet temperature for enhanced cycle efficiency. This concept creates special combustion system requirements that are very different from requirements of conventional gas turbine systems. The topping combustor provides the means for achieving state-of-the-art turbine inlet temperatures and is the main contributor to enhanced plant performance. The objective of this program is to develop a topping combustor that provides low emissions, and is a durable, efficient device exhibiting stable combustion and manageable wall temperatures. The combustor will be required to burn a low-Btu Syngas under normal “coal-fired” conditions. However, for start-up and/or carbonizer outage, it may be necessary to fire a clean fuel, such as oil or natural gas. Prior testing has shown the Westinghouse Multi-Annular Swirl Burner (MASB) to have excellent potential for this application. Metal wall temperatures can be maintained at acceptable levels, even though most “cooling” is done by 1600°F vitiated air. Good pattern factors and combustion efficiencies have been obtained. Additionally, low conversion rates of fuel bound nitrogen to NOx have been demonstrated. This paper presents an update of the status of an ongoing topping combustor development and test program for application to “Second-Generation Pressurized Fluidized Bed Combined Cycles (PFBCC).” The program is sponsored by the Department of Energy’s Morgantown Energy Technology Center (DOE/METC) and will first be applied commercially into the Clean Coal Technology Round V Four Rivers Energy Modernization Project. Phase 1 of the program involved a conceptual and economic study (Robertson et al., 1988); Phase 2 addresses design and subscale testing of components; and Phase 3 will cover pilot plant testing of components integrated into one system.

APA, Harvard, Vancouver, ISO, and other styles

41

Tinga, T., J. F. van Kampen, B. de Jager, and J. B. W. Kok. "Gas Turbine Combustor Liner Life Assessment Using a Combined Fluid/Structural Approach." Journal of Engineering for Gas Turbines and Power 129, no. 1 (2006): 69–79. http://dx.doi.org/10.1115/1.2360603.

Full text

Abstract:

A life assessment was performed on a fighter jet engine annular combustor liner, using a combined fluid/structural approach. Computational fluid dynamics analyses were performed to obtain the thermal loading of the combustor liner and finite element analyses were done to calculate the temperature and stress/strain distribution in the liner during several operating conditions. A method was developed to analyze a complete flight with limited computational effort. Finally, the creep and fatigue life for a measured flight were calculated and the results were compared to field experience data. The absolute number of cycles to crack initiation appeared hard to predict, but the location and direction of cracking could be correlated well with field data.

APA, Harvard, Vancouver, ISO, and other styles

42

Povey, T., K. S. Chana, and T. V. Jones. "Heat transfer measurements on an intermediate-pressure nozzle guide vane tested in a rotating annular turbine facility, and the modifying effects of a non-uniform inlet temperature profile." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 217, no. 4 (2003): 421–31. http://dx.doi.org/10.1243/095765003322315487.

Full text

Abstract:

In modern gas turbine engines there exist significant temperature gradients in the combustor exit flow. These gradients arise because both fuel and dilution air are introduced within the combustor as discrete jets. The effects of this non-uniform temperature field on the aerodynamics and heat transfer rate distributions of nozzle guide vanes and turbine blades is difficult to predict, although an increased understanding of the effects of temperature gradients would enhance the accuracy of estimates of turbine component life and efficiency. Low-frequency measurements of heat transfer rate have been conducted on an annular transonic intermediate-pressure (IP) nozzle guide vane operating downstream of a high-pressure (HP) rotating turbine stage. Measurements were conducted with both uniform and non-uniform inlet temperature profiles. The non-uniform temperature profile included both radial and circumferential gradients of temperature. Experiments were conducted in the isentropic light piston facility at QinetiQ Pyestock, a short-duration engine-size turbine facility with 1.5 turbine stages, in which Mach number, Reynolds number and gas—wall temperature ratios are correctly modelled. Experimental heat transfer results are compared with predictions performed using boundary layer methods.

APA, Harvard, Vancouver, ISO, and other styles

43

Worth, Nicholas A., and James R. Dawson. "Self-excited circumferential instabilities in a model annular gas turbine combustor: Global flame dynamics." Proceedings of the Combustion Institute 34, no. 2 (2013): 3127–34. http://dx.doi.org/10.1016/j.proci.2012.05.061.

Full text

APA, Harvard, Vancouver, ISO, and other styles

44

Zettervall, N., N. A. Worth, M. Mazur, J. R. Dawson, and C. Fureby. "Large eddy simulation of CH4-air and C2H4-air combustion in a model annular gas turbine combustor." Proceedings of the Combustion Institute 37, no. 4 (2019): 5223–31. http://dx.doi.org/10.1016/j.proci.2018.06.021.

Full text

APA, Harvard, Vancouver, ISO, and other styles

45

Cho, Ju Hyeong. "Design Methodology of an Annular Combustor for Micro Gas Turbines." Journal of the Korean Society of Combustion 19, no. 4 (2014): 21–27. http://dx.doi.org/10.15231/jksc.2014.19.4.021.

Full text

APA, Harvard, Vancouver, ISO, and other styles

46

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

47

Bideau, R. J. "The Development of a Computer Code for the Estimation of Combustor Exhaust Temperature Using Simple Gas Analysis Measurements." Journal of Engineering for Gas Turbines and Power 121, no. 1 (1999): 80–88. http://dx.doi.org/10.1115/1.2816317.

Full text

Abstract:

Advances in gas turbine technology have led to levels of turbine inlet temperature that preclude the use of thermocouple and simple gas analysis techniques for gas temperature determination. Simple gas analysis schemes rely on the measurement of a very limited range of species in the gas sample: typically, CO2, CO, and hydrocarbons (UHC). A method of estimating the other important species is required. Simple gas analysis schemes that rely only on elemental mass balance equations to determine the concentration of species are inadequate where high temperature results in significant dissociation. A method has been developed to enable temperature determination at levels that render simple schemes inaccurate. The procedure is based on the measurement of CO2, CO, UHC, and oxides of nitrogen in the exhaust gas. Other species concentrations are calculated using an assumption of partial thermodynamic equilibrium. This allows the calculation of many important combustion parameters. The method has been implemented as a computer code, with an object orientated design approach using the C++ language. The paper details the theory behind the approach and its implementation. The expected errors for practical applications are discussed and quantified. The method is illustrated by an exhaust temperature pattern factor investigation of an annular combustor. Temperatures determined by thermocouples are compared with those calculated from gas samples.

APA, Harvard, Vancouver, ISO, and other styles

48

Panigrahi, S. K., N. Sarangi, and U. Chandrasekhar. "Experimental Evaluation of Overload Capability of an Annular Combustor Casing of a Gas Turbine Engine." Experimental Techniques 40, no. 2 (2016): 841–48. http://dx.doi.org/10.1007/s40799-016-0083-z.

Full text

APA, Harvard, Vancouver, ISO, and other styles

49

Walz, G., W. Krebs, S. Hoffmann, and H. Judith. "Detailed Analysis of the Acoustic Mode Shapes of an Annular Combustion Chamber." Journal of Engineering for Gas Turbines and Power 124, no. 1 (1999): 3–9. http://dx.doi.org/10.1115/1.1396346.

Full text

Abstract:

To get a better understanding of the formation of thermoacoustic oscillations in an annular gas turbine combustor, an analysis of the acoustic eigenmodes has been conducted using the finite element method. The influence of different boundary conditions and a space-dependent velocity of sound has been investigated. The boundary conditions actually define the eigenfrequency spectrum. Hence, it is crucial to know, e.g., the burner impedance. In case of the combustion system without significant mixing air addition considered in this paper, the space-dependence of the velocity of sound is of minor importance for the eigenfrequency spectrum leading to a maximum deviation of only five percent in the eigenvalues. It is demonstrated that the efficiency of the numerical eigenvalue analysis can be improved by making use of symmetry, by splitting the problem into several steps with alternate boundary conditions, and by choosing the shift frequency ωs in the range of frequencies one is interested in.

APA, Harvard, Vancouver, ISO, and other styles

50

Kim, Lina, Ji-Seok Hong, Won Cheol Jeong, Kwang-Hee Yoo, Jong-Chan Kim, and Hong-Gye Sung. "Turbulent Combustion Characteristics of a Swirl Injector in a Gas Turbine Annular Combustor Using LES and Level-set Flamelet." Journal of the Korean Society of Propulsion Engineers 18, no. 2 (2014): 1–9. http://dx.doi.org/10.6108/kspe.2014.18.2.001.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Journal articles on the topic 'Annular gas turbine combustor'

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