Effects of Fuel Type on the Performance of Aero Gas Turbine Combustion Chambers, and the Influence of Design Features

1954 ◽  
Vol 58 (528) ◽  
pp. 813-825
Author(s):  
J. G. Sharp
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Combustion Efficiency ◽  
Combustion Stability ◽  
Fuel Type ◽  
Combustion Chambers ◽  
Exhaust Temperature ◽  
Design Changes ◽  
Fuel Characteristics ◽  
Gas Turbine Combustion

SummaryThe performance of aero gas turbine combustion chambers is discussed under the following headings : Combustion efficiency, combustion stability, ease of ignition, deposits, exhaust temperature variation, and smooth combustion. It is shown that, as assessed by these criteria, combustion chamber performance can be significantly affected by fuel characteristics; also that the effects of fuel type can be greatly modified by equipment design changes. The conclusion is that most of the problems- aggravated by fuel characteristics are better solved by modifications to equipment, if fuel availability and cost are not to be adversely affected.

Numerical and Experimental Investigation of a Semi-Technical Scale Burner Employing Model Synthetic Fuels

2009 ◽  
Author(s):  
Massimiliano Di Domenico ◽  
Peter Kutne ◽  
Clemens Naumann ◽  
Juergen Herzler ◽  
Rajesh Sadanandan ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Numerical Data ◽  
Diagnostic Techniques ◽  
Combustion Efficiency ◽  
Transport Equations ◽  
Numerical Code ◽  
Combustion Chambers ◽  
Flow Equations ◽  
Gas Turbine Combustion ◽  
Shift Reaction

In this paper the development and the application of a numerical code suited for the simulation of gas-turbine combustion chambers is presented. In order to obtain an accurate and flexible framework, a finite-rate chemistry model is implemented, and transport equations for all species and enthalpy are solved. An assumed PDF approach takes effects of temperature and species turbulent fluctuations on the chemistry source term into account. In order to increase code stability and to overcome numerical stiffness due to the large-varying chemical kinetics timescales, an implicit and fully-coupled treatment of the species transport equations is chosen. Low-Mach number flow equations and k-ε turbulence model complete the framework, and make the code able to describe the most important physical phenomena which take place in gas-turbine combustion chambers. In order to validate the numerical simulations, experimental measurements are carried out on a generic non-premixed swirl-flame combustor, fuelled with syngas-air mixtures and studied using optical diagnostic techniques. The combustor is operated at atmospheric and high-pressure conditions with simulated syngas mixtures consisting of H2, N2, CH4, CO. The combustor is housed in an optically-accessible combustion chamber to facilitate the application of chemiluminescence imaging of OH* and planar laser-induced fluorescence (PLIF) of the OH-radical. To investigate the velocity field, particle image velocimetry (PIV) is used. The OH* chemiluminescence imaging is used to visualise the shape of the flame zone and the region of heat release. The OH-PLIF is used to identify reaction zones and regions of burnt gas. The fuel composition is modelled after a hydrogen-rich synthesis gas, which can result after gasification of lignite followed by a CO shift reaction and a sequestration of CO2. Actual gas compositions and boundary conditions are chosen so that it is possible to outline differences and similarities among fuels, and at the same time conclusions about flame stability and combustion efficiency can be drawn. A comparison between experimental and numerical data is presented, and main strengths and deficiencies of the numerical modelling are discussed.

scholarly journals Numerical study of the parameters of a gas turbine combustion chamber with steam injection operating on distillate fuel

2020 ◽  
Vol 0 (0) ◽  
Author(s):  
Serhiy Serbin ◽  
Kateryna Burunsuz
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Mass Flow ◽  
Liquid Fuel ◽  
Numerical Study ◽  
Steam Injection ◽  
Liquid Fuels ◽  
Combustion Chambers ◽  
Mass Flow Rates ◽  
Gas Turbine Combustion

AbstractInvestigations of the working process in a gas turbine combustion chamber with ecological and energy steam injection operating on liquid fuel are conducted. The mathematical model of the aerodynamic processes and liquid fuel combustion in similar burning devices based on the numerical solution of the system of conservation and transport equations for a multi-component chemically reactive turbulent system is developed. The influence of the relative steam mass flow rate (the ratio of the sum of the mass flow rates of ecological and energy steam to the fuel consumption) on the combustion chamber’s emission characteristics is determined. The obtained results can be used for parameter selection and optimization of promising high-temperature gas turbine combustion chambers with steam injection operating on liquid fuels.

scholarly journals On the dynamic nature of azimuthal thermoacoustic modes in annular gas turbine combustion chambers

2013 ◽  
Vol 469 (2151) ◽  
pp. 20120535 ◽  
Author(s):  
Nicolas Noiray ◽  
Bruno Schuermans
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Travelling Waves ◽  
Acoustic Measurements ◽  
Combustion Chambers ◽  
Dynamic Nature ◽  
Detailed Statistical Analysis ◽  
Gas Turbine Combustion ◽  
Modal Dynamics ◽  
Good Agreement

This paper deals with the dynamics of standing and rotating azimuthal thermoacoustic modes in annular combustion chambers. Simultaneous acoustic measurements have been made at multiple circumferential positions in an annular gas turbine combustion chamber. A detailed statistical analysis of the spatial Fourier amplitudes extracted from these data reveals that the acoustic modes are continuously switching between standing, clockwise and counter-clockwise travelling waves. A theoretical framework from which the modal dynamics can be explained is proposed and supported by real gas turbine data. The stochastic differential equations that govern these systems have been derived and used as a basis for system identification of the measured engine data. The model describes the probabilities of the two azimuthal wave components as a function of the random source intensity, the asymmetry in the system and the strength of the thermoacoustic interaction. The solution of the simplified system is in good agreement with experimental observations on a gas turbine combustion chamber.

Combination of 1D Code and CFD for Performance Analysis of a Silo Type Gas Turbine Combustor

2010 ◽  
Author(s):  
N. Rasooli ◽  
S. Besharat Shafiei ◽  
H. Khaledi
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Mass Distribution ◽  
Gas Turbines ◽  
Pressure Loss ◽  
Combustion Efficiency ◽  
Operating Conditions ◽  
Empirical Correlations ◽  
Combustion Chambers ◽  
Cfd Simulations

Whereas Gas Turbines are the most important producers of Propulsion and Power in the world and with attention to the importance of combustion chamber as one of the three basic components of Gas Turbine, various activities in different levels have been done on this component. Because of the environmental limitations and laws related to the pollutants such as NOx and CO, Lean Premixed Combustion Chambers are specially considered in gas turbine industries. This study is part of a Multi-Layer simulation of the whole gas turbine cycle in MPG Company. In this work, the combination of a general 1D code and CFD is used for deriving appropriate performance curves for a 1D and 0D gas turbine design, off-design and dynamic cycle code. This 1D code is a general code which has been developed for different combustion chambers; annular, can-annular, can type and silo type combustion chambers. The purpose of generating this 1D code is the possibility of fast analysis of combustors in different operating conditions and reaching required outputs. This 1D code is a part of a general simulation 1D code for gas turbine and was used for a silo type combustor performance prediction. This code generates required quantities such as pressure loss, exit temperature, liner temperature and mass distribution through the combustion chamber. Mass distribution and pressure loss are analyzed and determined with an electrical analogy. Results derived from 1D code are validated with empirical data available for different combustors. There is appropriate agreement between these experimental and analytical results. Drag coefficients for liner holes are available from experimental data and for burner are calculated as a curve with CFD simulations. What differs this code from other 1D codes for gas turbine combustors is the advantage of using combustion efficiencies evolved from numerical simulation results in different loads. These efficiencies are determined with CFD simulations and are available as maps and inserted into the gas temperature calculation algorithm of 1D code. In other 1D codes in this field, empirical correlations are used for combustion efficiency determination. Combustion efficiency curves for design and off-design conditions in this study are achieved by 2D and 3D simulation of combustion chamber with application of EBU/Finite Rate model and 8 step reactions of CH4 burning. Diffusion flame in low loads and premixed flame in high loads are considered. Flame stability and Lean Blow Out charts are evolved from CFD simulation and Heat transfer is applied with empirical correlations.

scholarly journals Experience With Large Gas Turbine Combustion Chambers

1982 ◽  
Author(s):  
A. Lienert ◽  
O. Schmoch
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Peak Load ◽  
Combustion Chambers ◽  
Initial Stage ◽  
Gas Turbine Combustion ◽  
Maintenance And Inspection ◽  
Positive Effect ◽  
Base Load

Large gas turbine combustion chambers, being arranged outside of the unit, exhibit quite a lot of advantages with respect to combustion. Moreover, they are characterized by a long life of all components. Thus, in case of such gas turbine units the maintenance and inspection intervals are relatively large being not determined by the combustion chamber or combustion chamber components. There are not many failures. They may easily be recognized at their initial stage and can be eliminated quickly as the inside is accessible via a manhole. This in turn has a positive effect on overall maintenance and service cost. Besides, this easy accessibility allows for a direct examination of the turbine inner casing and the first turbine stages in case of maintenanced works. Experiences are based on the operation of more than 100 gas turbines of such a kind, whereby several have been run at peak load with more than 5000 starts, others at base load with more than 100,000 operating hours.

The Measurement of Gas Turbine Combustion Efficiency by Gas Analysis

1949 ◽  
Vol 1 (2) ◽  
pp. 165-186
Author(s):  
L. J. Richards ◽  
J. C. Street
Keyword(s):  
Gas Turbine ◽  
Analytical Techniques ◽  
Combustion Efficiency ◽  
Gas Analysis ◽  
Research Centre ◽  
Combustion Chambers ◽  
Sampling Systems ◽  
Gas Turbine Combustion ◽  
Engine Testing ◽  
Efficiency Determination

SummaryFollowing a brief discussion of various methods of measuring combustion efficiency in gas turbine chambers, the superiority in accuracy of applied gas analysis is stated. Factors leading to inefficiencies in combustion are outlined and the exhaust constituents requiring measurement are deduced. The chief difficulty in the past in the application of gas analysis methods to combustion efficiency determination has been the time consumed in actual analysis of samples; at Thornton Research Centre means of overcoming this difficulty have been investigated and several rapid and accurate analytical techniques have been developed and used successfully. These techniques are described, together with other promising methods at present under development. The broad requirements of obtaining exhaust gas samples for analysis are discussed and typical sampling systems described; precautions necessary in applying these systems are given. Formulse for the calculation of combustion efficiency from analytical results, together with any assumptions made, are given in the text and their derivation explained in an Appendix. The techniques described have been developed primarily for use in conjunction with rig testing of aircraft gas turbine combustion chambers; the broader application—for instance, to engine testing—of the principles involved are considered briefly.

Analysis of Temperature Distribution Over a Gas Turbine Shaft Exposed to a Swirl Combustor Flue

2010 ◽  
Author(s):  
V. Aghakashi ◽  
M. H. Saidi ◽  
A. Ghafourian ◽  
A. A. Mozafari
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Equivalence Ratio ◽  
Vortex Flow ◽  
Combustion Efficiency ◽  
Swirl Flow ◽  
Axial Position ◽  
Combustion Chambers ◽  
Swirl Combustor ◽  
Turbine Shaft

Gas turbine shaft is generally exposed to high temperature gases and may seriously be affected and overheated due to temperature fluctuations in the combustion chamber. Considering vortex flow in the combustion chamber, it may increase the heat release rate and combustion efficiency and also control location of energy release. However, this may result in excess temperature on the combustor equipments and gas turbine shaft. Vortex flow in the vortex engine which is created by the geometry of combustion chamber and conditions of flow field is a bidirectional swirl flow that maintains the chamber wall cool. In this study a new gas turbine combustion chamber implementing a liner around the shaft and liquid fuel feeding system is designed and fabricated. Influence of parameters such as axial position in the combustor direction and equivalence ratio are studied. Experimental results are compared with the numerical simulation by the existing commercial software. Swirl number i.e. ratio of angular flux of angular momentum to angular flux of linear momentum multiplied by nozzle radius, in this study is assumed to be constant. In order to measure the temperature along the liner, K type thermocouples are used. Results show that the heat transfer to the liner at the inlet of combustion chamber is enough high and at the outlet of combustion chamber is relatively low. The effect of parameters such as equivalence ratio and the mass flow rate of oxidizer on the temperature of the liner is investigated and compared with the numerical solution. This type of combustion chambers can be used in gas turbine engines due to their low weight and short length of combustion chamber.

Numerical study of the parameters of a gas turbine combustion chamber with steam injection operating on distillate fuel

2020 ◽  
Vol 0 (0) ◽  
Author(s):  
Serhiy Serbin ◽  
Kateryna Burunsuz
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Mass Flow ◽  
Liquid Fuel ◽  
Numerical Study ◽  
Steam Injection ◽  
Liquid Fuels ◽  
Combustion Chambers ◽  
Mass Flow Rates ◽  
Gas Turbine Combustion

Abstract Investigations of the working process in a gas turbine combustion chamber with ecological and energy steam injection operating on liquid fuel are conducted. The mathematical model of the aerodynamic processes and liquid fuel combustion in similar burning devices based on the numerical solution of the system of conservation and transport equations for a multi-component chemically reactive turbulent system is developed. The influence of the relative steam mass flow rate (the ratio of the sum of the mass flow rates of ecological and energy steam to the fuel consumption) on the combustion chamber’s emission characteristics is determined. The obtained results can be used for parameter selection and optimization of promising high-temperature gas turbine combustion chambers with steam injection operating on liquid fuels.

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