Experimental research of the small gas turbine with variable area nozzle

2019 ◽  
Vol 233 (15) ◽  
pp. 5650-5659 ◽  
Author(s):  
Szymon Fulara ◽  
Maciej Chmielewski ◽  
Marian Gieras
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Experimental Research ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Engine Model ◽  
Turbine Efficiency ◽  
Specific Thrust ◽  
Working Parameters ◽  
No Emissions

The main aim of this article is to present the experimental data of the operating parameters and emissions obtained in a small gas turbine equipped with a variable area nozzle system. The variable area nozzle is proposed as a means of improving turbine efficiency, which has been a popular trend in recent development of gas turbine engines. Based on turbine vane twisting, the proposed variable area nozzle system was developed and implemented in GTM-120 small gas turbine. The concept was experimentally investigated on the engine test bench and engine working parameters were accurately measured. Experimental research shows that significant improvement of engine specific fuel consumption (up to 4%) and specific thrust (up to 5%) has been achieved. Additionally, reduction in CO emissions (up to 64%), NO emissions (up to 7%) and NO2 emissions (up to 53%) has been noted. Experimental research results were compared with analytical engine model showing moderate, qualitative agreement between the experimental data and model outputs. Main advantages of variable area nozzle system and design challenges of the proposed concept are discussed in the article summary.

Algorithm of Numerical Checking Calculation of Turbine Cooled Blades of Gas Turbine Engines Using Experimental Data on Heat Transfer and Resistance

2019 ◽  
Vol 62 (2) ◽  
pp. 298-303
Author(s):  
A. V. Il’inkov ◽  
A. M. Ermakov ◽  
V. V. Takmovtsev ◽  
A. V. Shchukin ◽  
A. M. Erzikov
Keyword(s):  
Heat Transfer ◽  
Experimental Data ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines

A Mean Line Prediction Method for Axial Flow Turbine Efficiency

1982 ◽  
Vol 104 (1) ◽  
pp. 111-119 ◽  
Author(s):  
S. C. Kacker ◽  
U. Okapuu
Keyword(s):  
Gas Turbine ◽  
Axial Flow ◽  
Prediction Method ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Loss System ◽  
Turbine Efficiency ◽  
Wide Range ◽  
Line Loss ◽  
Axial Turbines

A mean line loss system is described, capable of predicting the design point efficiencies of current axial turbines of gas turbine engines. This loss system is a development of the Ainley/Mathieson technique of 1951. The prediction method is tested against the “Smith’s chart” and against the known efficiencies of 33 turbines of recent design. It is shown to be able to predict the efficiencies of a wide range of axial turbines of conventional stage loadings to within ± 1 1/2 percent.

scholarly journals Integration of On-Line and Off-Line Diagnostic Algorithms for Aircraft Engine Health Management

2007 ◽  
Author(s):  
Takahisa Kobayashi ◽  
Donald L. Simon
Keyword(s):  
Gas Turbine ◽  
Health Management ◽  
Diagnostic Algorithm ◽  
Aircraft Engine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Simulation Environment ◽  
Diagnostic Algorithms ◽  
Engine Model ◽  
On Line

This paper investigates the integration of on-line and off-line diagnostic algorithms for aircraft gas turbine engines. The on-line diagnostic algorithm is designed for in-flight fault detection. It continuously monitors engine outputs for anomalous signatures induced by faults. The off-line diagnostic algorithm is designed to track engine health degradation over the lifetime of an engine. It estimates engine health degradation periodically over the course of the engine’s life. The estimate generated by the off-line algorithm is used to “update” the on-line algorithm. Through this integration, the on-line algorithm becomes aware of engine health degradation, and its effectiveness to detect faults can be maintained while the engine continues to degrade. The benefit of this integration is investigated in a simulation environment using a nonlinear engine model.

Design Parameters for an Aircraft Engine Exit Plane Particle Sampling System

2010 ◽  
Vol 133 (2) ◽  
Author(s):  
Hsi-Wu Wong ◽  
Zhenhong Yu ◽  
Michael T. Timko ◽  
Scott C. Herndon ◽  
Elena de la Rosa Blanco ◽  
...  
Keyword(s):  
Experimental Data ◽  
System Design ◽  
Gas Turbine ◽  
Black Carbon ◽  
Particle Formation ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Exit Plane ◽  
Sampling System ◽  
Sampling Line

The experimental data and numerical modeling were utilized to investigate the effects of exhaust sampling parameters on the measurements of particulate matter (PM) emitted at the exit plane of gas-turbine engines. The results provide guidance for sampling system design and operation. Engine power level is the most critical factor that influences the size and quantity of black carbon soot particles emitted from gas-turbine engines and must be considered in sampling system design. The results of this investigation indicate that the available soot surface area significantly affects the amount of volatile gases that can condense onto soot particles. During exhaust particle measurements, a dilution gas is typically added to the sampled exhaust stream to suppress volatile particle formation in the sampling line. Modeling results indicate that the dilution gas should be introduced upstream before a critical location in the sampling line that corresponds to the onset of particle formation microphysics. Also, the dilution gas should be dry for maximum nucleation suppression. In most aircraft PM emissions measurements, the probe-rake systems are water cooled and the sampling line may be heated. Modeling results suggest that the water cooling of the probe tip should be limited to avoid overcooling the sampling line wall temperature and, thus, minimize additional particle formation in the sampling line. The experimental data show that heating the sampling lines will decrease black carbon and sulfate PM mass and increase organic PM mass reaching the instruments. Sampling line transmission losses may prevent some of the particles emitted at the engine exit plane from reaching the instruments, especially particles that are smaller in size. Modeling results suggest that homogeneous nucleation can occur in the engine exit plane sampling line. If newly nucleated particles, typically smaller than 10 nm, are indeed formed in the sampling line, sampling line particle losses provide a possible explanation, in addition to the application of dry diluent, that they are generally not observed in the PM emissions measurements.

Lean Blowout Research in a Generic Gas Turbine Combustor With High Optical Access

1993 ◽  
Author(s):  
G. J. Sturgess ◽  
D. Shouse
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Air Force ◽  
Operating Conditions ◽  
Test Facility ◽  
Turbine Engines ◽  
Flame Stability ◽  
Gas Turbine Engines ◽  
Gas Turbine Combustor ◽  
Lean Blowout

The U.S. Air Force is conducting a comprehensive research program aimed at improving the design and analysis capabilities for flame stability and lean blowout in the combustors of aircraft gas turbine engines. As part of this program, a simplified version of a generic gas turbine combustor is used. The intent is to provide an experimental data base against which lean blowout modeling might be evaluated and calibrated. The design features of the combustor and its instrumentation are highlighted, and the test facility is described. Lean blowout results for gaseous propane fuel are presented over a range of operating conditions at three different dome flow splits. Comparison of results with those of a simplified research combustor is also made. Lean blowout behavior is complex, so that simple phenomenological correlations of experimental data will not be general enough for use as design tools.

scholarly journals TO DETERMINATION OF THE QUANTITY OF DANGEROUS GASES IN A GAS TURBINE HEAT-VENTILATION TUNNEL INSTALLATION

2019 ◽  
Vol 2 (4) ◽  
pp. 45-52
Author(s):  
Lavrenty Kiyanitsa ◽  
Olga Kulikova
Keyword(s):  
Nitrogen Oxides ◽  
Gas Turbine ◽  
Far East ◽  
Carbon Oxide ◽  
Hazardous Substances ◽  
Turbine Engines ◽  
Hazardous Substance ◽  
Gas Turbine Engines ◽  
Working Parameters

There is the emission problem of hazardous substances such as nitrogen oxides, carbon oxide and soot into inner space of tunnel with heated air while using of gas-turbine engines as heat ventilating equipment for long railway tunnels in conditions of harsh continental climate of Siberian and Far East. In the investigation working parameters of gas-turbine equipment based on jet engine D-36 is determined. The analysis of hazardous substance emissions for two specific working modes is carried out. It is educed that the concentration of nitrogen oxides located at ventilating flow from the equipment, working at nominal mode, do not exceed standards of maximal permissible concentrations for railway tunnels. Parameters of the surrounding air, discharged into the tunnel, for dilution of ventilating flow with high content of nitrogen oxides to standard of MPC is determined.

A Comprehensive Fuel Spray Model for High Pressure Fuel Injectors

2008 ◽  
Author(s):  
Gerald J. Micklow ◽  
Krishna Ankem ◽  
Tarek Abdel-Salam
Keyword(s):  
Experimental Data ◽  
High Pressure ◽  
Gas Turbine ◽  
Direct Injection ◽  
Combustion Process ◽  
Injection Pressure ◽  
Pollutant Emission ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Fuel Injectors

Understanding the physics and chemistry involved in spray combustion, with its transient effects and the inhomogeneity of the spray is quite challenging. For efficient operation of both internal combustion and gas turbine engines, great insight into the physics of the problem can be obtained when a computational analysis is used in conjunction with either an experimental program or through published experimental data. The main area to be investigated to obtain good combustion begins with the fuel injection process and an accurate description of the mean diameter of the fuel particle, injection pressure, drag coefficient, rate shaping etc must be defined correctly. This work presents a methodology to perform the task set out in the previous paragraph and uses experimental data obtained from available literature to construct a semi-empirical numerical model for high pressure fuel injectors. A modified version of a multidimensional computer code called KIVA3V was used for the computations, with improved sub-models for mean droplet diameter, injection pressure, injection velocity, and drop distortion and drag. The results achieved show good agreement with the published in-cylinder experimental data for a Volkswagen 1.9 L turbo-charged direct injection internal combustion engine under actual operating conditions. It is crucial to model the spray distribution accurately, as the combustion process and the resulting temperature distribution and pollutant emission formation is intimately tied to the in-cylinder fuel distribution. The present scheme has achieved excellent agreement with published experimental data and will make an important contribution to the numerical simulation of the combustion process and pollutant emission formation in compression ignition direct injection engines and gas turbine engines.

Numerical Investigation of Ignition Sequence in a Multi-Burner Methane-Air Swirl Combustor Using Flamelet Generated Manifold Combustion Model

2019 ◽  
Author(s):  
Pravin Nakod ◽  
Sourabh Shrivastava ◽  
Saurabh Patwardhan ◽  
Stefano Orsino ◽  
Rakesh Yadav
Keyword(s):  
Experimental Data ◽  
Numerical Investigation ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Combustion Model ◽  
Gas Turbine Engines ◽  
Swirl Combustor ◽  
Low Emission ◽  
Flamelet Generated Manifold ◽  
Work Assessment

Abstract Low emission gas turbine engines, operating under fuel lean conditions, are susceptible to light-around issues. Traditionally, gas turbine manufacturers rely on experimentation and testing to understand the relight characteristics of a combustor. However, since the last decade, numerical simulations are gaining popularity in performance evaluation of the light-around characteristics of the gas turbine combustors. In the present work, assessment of the Flamelet Generated Manifold (FGM) combustion model is carried out to understand its performance for capturing the correct ignition sequence in a linear multi-burner methane-air swirl combustor designed by COmplexe de Recherche Interprof essionnel en Aérothermochimie (CORIA) in the context of Knowledge for Ignition, Acoustics, and Instabilities (KIAI) project. The present work uses linear five, four and two swirled injector configurations for the validation of the simulation results. Non-reacting and reacting Large Eddy Simulations (LES) are performed for three injector arrangements to predict the main flow structure, mixing, flame propagation and ignition sequence. Non-reacting time-averaged flow quantities such as mean axial and radial velocities are data-sampled and compared with the experimental results. The predicted results show a good comparison between simulation and experimental data. Ignition sequence and timing predicted from the reacting LES for all the three configurations studied in this work, also compare well with the experimental data. This numerical investigation confirms that the FGM combustion model used in the LES framework can be successfully employed for the prediction of the relight characteristics of the gas turbine engines.

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