Download or read book A Parametric Investigation of a Model Gas Turbine Can Combustor written by J. Brouwer and published by . This book was released on 1988 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Parametric Investigation of Soot Behavior and Other Emissions in a Gas Turbine Combustor written by Joseph Dickson Weller and published by . This book was released on 1984 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted to determine the effects of operating characteristics and fuel additives in a gas turbine combustor on particulates (soot) and other gaseous emissions (NOx, NO). The principles of Mie theory and three-wavelength light transmittance have been utilized in this investigation to determine particulate size and mass concentration. Using an Allison T63 turboshaft engine combustor, five experimental fuels of varying chemical composition were analyzed from an emissions standpoint. There was no apparent relationship between particulate size and either fuel composition or combustor exhaust temperature. Nitric oxide levels were indifferent to fuel composition but did show a characteristics upward trend with exhaust temperature. Visible spectrum transmittance did indicate an inverse relation to increasing exhaust temperature. Though only two fuel additives were tested on one fuel, there was no manifestation of improved transmittance with their use.

Download or read book Gas Turbine Combustion Modeling for a Parametric Emissions Monitoring System written by and published by . This book was released on 2007 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Oxides of nitrogen (NO[subscript x]), carbon monoxide (CO) and other combustion by-products of gas turbines have long been identified as harmful atmospheric pollutants to the environment and humans. Various government agencies place restrictions on emissions and often require some sort of emissions monitoring even for new low emission gas turbines. Predicting actual emissions from operating parameters that affect the formation of pollutants, called parametric emissions monitoring system (PEMS), has potential economic advantages compared to a continuous emissions monitoring system (CEMS). The problem is that a simple applicable PEMS does not exist. During this study, a gas turbine combustor model applying first engineering principles was developed to predict the emission formation of NO[subscript x]and CO in a gas turbine. The model is based on a lean-premixed combustor with a main and pilot burner including the function of a bleeding air valve. The model relies on ambient condition and load. The load is expressed as a percentage of the target speed of the gas producer turbine. Air flow and fuel flow for the main and pilot burner are calculated by the model based on the load through a set of measured input data for a specific gas turbine. To find the combustion temperature characteristics, the combustor is divided into several zones. The temperature for each zone is calculated by applying an energy balance. To predict NO[subscript x] and CO, several correlations explored by various researchers are used and compared against each other, using the calculated temperatures, pressures and equivalence ratios. A comparison between collected emissions examples from a turbine test cell data spreadsheet and predicted emissions by the developed model under the same conditions show a highly accurate match for NO[subscript x] emission at any load. Because of the high variation of CO at part load, the model predictions only match the CO data set at full load.

Download or read book Combustion Noise written by Anna Schwarz and published by Springer Science & Business Media. This book was released on 2009-06-17 with total page 304 pages. Available in PDF, EPUB and Kindle. Book excerpt: November, 2008 Anna Schwarz, Johannes Janicka In the last thirty years noise emission has developed into a topic of increasing importance to society and economy. In ?elds such as air, road and rail traf?c, the control of noise emissions and development of associated noise-reduction techno- gies is a central requirement for social acceptance and economical competitiveness. The noise emission of combustion systems is a major part of the task of noise - duction. The following aspects motivate research: • Modern combustion chambers in technical combustion systems with low pol- tion exhausts are 5 - 8 dB louder compared to their predecessors. In the ope- tional state the noise pressure levels achieved can even be 10-15 dB louder. • High capacity torches in the chemical industry are usually placed at ground level because of the reasons of noise emissions instead of being placed at a height suitable for safety and security. • For airplanes the combustion emissions become a more and more important topic. The combustion instability and noise issues are one major obstacle for the introduction of green technologies as lean fuel combustion and premixed burners in aero-engines. The direct and indirect contribution of combustion noise to the overall core noise is still under discussion. However, it is clear that the core noise besides the fan tone will become an important noise source in future aero-engine designs. To further reduce the jet noise, geared ultra high bypass ratio fans are driven by only a few highly loaded turbine stages.

Download or read book An Experimental and Numerical Investigation of a Gas Turbine Research Combustor written by Reuben Montresor Morris and published by . This book was released on 2013 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Gas turbine engineering faces many challenges in the constant strive to increase not only the efficiency of engines but also the various stages of development and design. Development of combustors have primarily consisted of empirical or semi-empirical modelling combined with experimental investigations. Due to the associated costs and development time a need exists for an alternative method of development. Although experimental investigations can never be substituted completely, mathematical models incorporating numerical methods have shown to be an attractive alternative to conventional combustor design methods. The purpose of this study is twofold: firstly, to experimentally investigate the physical properties associated with a research combustor that is geometrically representative of practical combustors: and secondly, to use the experimental measurements for the validation of a computational fluids dynamic model that was developed to simulate the research combustor using a commercial code. The combustor was tested at atmospheric conditions and is representative of practical combustors that are characterized by a turbulent, three-dimensional flow field. The single can combustor is divided into a primary, secondary and dilution zone, incorporating film cooling air through stacked rings and an axial swirler centred around the fuel atomizer. Measurements at different air/fuel ratios captured the thermal field during operating conditions and consisted of inside gas, liner wall and exit gas temperatures. An investigation of the different combustion models available, led to the implementation of the presumed-PDF model of unpremixed turbulent reaction. The computational grid included the external and internal flow field with velocity boundary conditions prescribed at the various inlets. Two-phase flow was not accounted for with the assumption made that the liquid fuel is introduced into the combustion chamber in a gas phase. Experimental results showed that incomplete combustion occurs in the primary zone, thereby reducing the overall efficiency. Also evident from the results obtained are the incorrect flow splits at the various inlets. Evaluation of the numerical model showed that gas temperatures inside the combustor are overpredicted. However, the numerical model is capable of capturing the correct distributions of temperatures and trends obtained experimentally. This study is successful in capturing detail temperature measurements that will be used for validation purposes to assist the development of a numerical model that can accurately predict combustion properties.

Download or read book An Investigation of Gas Turbine Combustors with High Inlet Air Temperatures Part 3 Experimental Developments written by Richard D. Anderson and published by . This book was released on 1971 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: Current gas turbine combustor design philosophy must reflect consideration of both emission control and high inlet air temperature effects on flame stability, combustor performance, and flame tube life. An experimental facility has been designed for the detailed, systematic study of gas turbine combustion as a function of realistic inlet parameters. In an attempt to provide fundamental gas turbine measurements are described. In addition to a detailed description of the experimental facility, internal gas temperature and gas sampling probing techniques, facility instrumentation, and future engine parameter settings are discussed.

Download or read book Combining a One dimensional Empirical and Network Solver with Computational Fluid Dynamics to Investigate Possible Modifications to a Commercial Gas Turbine Combustor written by Johannes Jacobus Gouws and published by . This book was released on 2005 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Gas turbine combustion chambers were traditionally designed through trial and error which was unfortunately a time-consuming and expensive process. The development of computers, however, contributed a great deal to the development of combustion chambers, enabling one to model such systems more accurately in less time. Traditionally, preliminary combustor designs were conducted with the use of one-dimensional codes to assist in the prediction of flow distributions and pressure losses across the combustion chamber mainly due to their rapid execution times and ease of use. The results are generally used as boundary conditions in three- dimensional models to predict the internal flow field of the combustor. More recent studies solve the entire flow field from prediffuser to combustor exit. This approach is, however, a computationally expensive procedure and can only be used if adequate computer resources are available. The purpose of this study is two-fold: (1) to develop a one-dimensional incompressible code, incorporating an empirical-based combustion model, to assist a one-dimensional network solver in predicting flow- and temperature distributions, as well as pressure losses. This is done due to the lack of a combustion model in the network solver that was used. An incompressible solution of flow splits, pressure losses, and temperature distributions is also obtained and compared with the compressible solution obtained by the network solver: (2) to utilise the data, obtained from the network solver, as boundary conditions to a three-dimensional numerical model to investigate possible modifications to the dome wall of a standard T56 combustion chamber. A numerical base case model is validated against experimental exit temperature data, and based upon that comparison, the remaining numerical models are compared with the numerical base case. The effect of the modification on the dome wall temperature is therefore apparent when the modified numerical model is compared with the numerical base case. A second empirical code was developed to design the geometry of axial straight vane swirlers with different swirl angles. To maintain overall engine efficiency, the pressure loss that was determined from the network analysis, of the base case model, is used during the design of the different swirlers. The pressure loss across the modified combustion chamber will therefore remain similar to that of the original design. Hence, to maintain a constant pressure loss across the modified combustion chambers, the network solver is used to determine how many existing hole features should be closed for the pressure loss to remain similar. The hole features are closed, virtually, in such a manner as not to influence the equivalence ratio in each zone significantly, therefore maintaining combustion performance similar to that of the original design. Although the equivalence ratios in each combustion zone will be more or less unaffected, the addition of a swirler will influence the emission levels obtained from the system due to enhanced air-fuel mixing. A purely numerical parametric analysis was conducted to investigate the influence of different swirler geometries on the dome wall temperature while maintaining an acceptable exit temperature distribution. The data is compared against the data obtained from an experimentally validated base case model. The investigation concerns the replacement of the existing splash-cooling devices on the dome wall with that of a single swirler. A number of swirler parameters such as blade angle, mass flow rate, and number of blades were varied during the study, investigating its influence on the dome wall temperature distribution. Results showed that the swirlers with approximately the same mass flow as the existing splash-cooling devices had almost no impact on the dome wall temperatures but maintained the exit temperature profile. An investigation of swirlers with an increased mass flow rate was also done and results showed that these swirlers had a better impact on the dome wall temperatures. However, due to the increased mass flow rate, stable combustion is not guaranteed since the air/fuel ratio in the primary combustion zone was altered. The conclusion that was drawn from the study, was that by simply adding an axial air swirler might reduce high-temperature gradients on the dome but will not guarantee stable combustion during off-design operating conditions. Therefore, a complete new hole layout design might be necessary to ensure good combustion performance across a wide operating range.

Download or read book Gas Turbine Combustor Design Problems written by Arthur Henry Lefebvre and published by Hemisphere Pub. This book was released on 1980 with total page 458 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Gas turbine combustor design parameter analysis for soot reduction using CFD ASME 99 GT 240 written by D. Scott Crocker and published by . This book was released on 1999 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, Indiana, June 7-June 10, 1999.

Download or read book Combustor Modelling written by and published by . This book was released on 1980 with total page 406 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Role of Primary Jets in the Dome Region Aerodynamics of a Model Can Combustor written by Cecilia Dianne Richards and published by . This book was released on 1990 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The role of the primary jets in the aerothermal behavior and overall performance of a gas turbine combustor is explored through an experimental study. The study is performed in a model laboratory combustor that possesses the essential features of practical combustors. The test bed is designed to accommodate optical access for laser diagnostics and overall flow visualization, and is capable of incorporating variable inlet geometries. In the present case, the combustor is operated on JP-4 at atmospheric pressure. A parametric variation in the number of jets per row and axial location of the jet row is performed. The aerodynamic and thermal fields are characterized using laser anemometry and a thermocouple probe, respectively. Species concentrations are acquired via extractive probe sampling. The results demonstrate the importance of primary jet location with respect to the dome swirler. The percent mass recirculated into the dome region, as well as the overall uniformity of mixing and combustion efficiency, are substantially influenced by jet row location. The momentum ratio of the incoming primary jet stream to that of the approaching crossflow of reacting dome gases has a direct impact on the mixing patterns as well. An increase in the number of primary jets leads, in the present case, to more uniform mixing.

Download or read book AIAA ASME SAE ASEE 24th Joint Propulsion Conference written by and published by . This book was released on 1988 with total page 400 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 956 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book ASME Technical Papers written by and published by . This book was released on 2001 with total page 472 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book TECHNICAL REPORT AN EXPERIMENTAL INVESTIGATION OF A COMBUSTOR FOR AN EXPLOSION CYCLE GAS TURBINE written by D.E. ROGERS, P.O. HATS, and published by . This book was released on with total page 63 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Investigation of Gas Turbine Combustors with High Inlet Air Temperatures Part I Combustor Modelling written by Dean C Hammond (Jr) and published by . This book was released on 1971 with total page 119 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical model has been developed which will predict the performance and pollutant emissions of gas turbine combustors. The entire gas turbine combustor is approximated as a collection of perfectly stirred zones. Within each zone a general hydrocarbon combustion mechanism is used to predict the gas composition and temperature. The zone volumes and sizes are assigned from consideration of the theoretically predicted gas flows thereby approximating the mixing behavior of the system. Selected predictions of the overall model for a 'typical' aircraft combustor are presented. These results are seen to be qualitatively accurate and fall in the range of values typically observed in practical systems.

Download or read book Parametric Studies of Gas Turbine Engine Design written by Azrin Ariffin and published by . This book was released on 1999 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: