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.

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.

Effect of Vortex Flow on Heat Transfer to Combustion Chamber Wall

2006 ◽  
Vol 129 (2) ◽  
pp. 622-624 ◽  
Author(s):  
A. Ghafourian ◽  
M. H. Saidi ◽  
S. Jahangirian ◽  
M. Abarham
Keyword(s):  
Heat Transfer ◽  
Combustion Chamber ◽  
Wall Temperature ◽  
Hot Spots ◽  
Vortex Flow ◽  
Swirl Flow ◽  
Experimental Facility ◽  
Combustion Chambers ◽  
Flow Rates ◽  
Bidirectional Flow

A new experimental facility was designed, fabricated, and tested to model and study the effect of bidirectional swirl flow on the rate of heat transfer to combustion chamber walls. Reduction of this heat transfer can result in time and cost of design and fabrication methods of combustion chambers. The experimental study was performed using propane and air with oxygen as fuel and oxidizer, respectively. For similar flow rates, in cases where bidirectional flow was present, wall temperature reductions of up to 70% were observed. In cases where only some of the oxidizer was injected from the chamber end to generate the bidirectional swirl flow, the lowest wall temperature existed. This can be due to better mixing of fuel and oxidizer and absence of hot spots in the combustion core.

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.

Comparing Different Solutions for the Micro-Gas Turbine Combustor

2004 ◽  
Author(s):  
Maria Cristina Cameretti ◽  
Raffaele Tuccillo
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Equivalence Ratio ◽  
The Self ◽  
Combustion Chambers ◽  
Gas Turbine Combustor ◽  
Lean Mixture ◽  
Micro Gas Turbine ◽  
Different Types ◽  
Annular Combustor

This paper compares different types of combustion chambers for a micro-gas turbine which operates with both different fuels and variations in the inlet air conditions. The combustor types examined cover a wide variety of conditions for the primary combustion, whose fuel/air equivalence ratio ranges from typical lean-premixed levels up to dramatically rich values. The latter is attained in a combustion chamber of the RQL type, while the lean mixture burns in a tubular swirled combustor also equipped with a pilot igniter. The comparison is completed by including an annular combustor with a primary diffusive burner. The CFD based analysis highlights the main differences among the three types of combustors, in terms of temperature and pollutant distributions, and by focusing the attention on the self-ignition occurrence.

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.

Numerical Simulation as Design Optimization Tool for Gas Turbine Combustion Chambers

2010 ◽  
Author(s):  
Digvijay B. Kulshreshtha ◽  
S. A. Channiwala ◽  
Saurabh B. Dikshit
Keyword(s):  
Numerical Simulation ◽  
Temperature Distribution ◽  
Combustion Chamber ◽  
Design Optimization ◽  
Gas Turbine ◽  
Flow Patterns ◽  
Intermediate Zone ◽  
Experimental Investigations ◽  
Combustion Chambers ◽  
Primary Zone

In present study an attempt has been made through CFD approach using CFX 11 to analyze the flow patterns within the combustion liner and through different air admission holes, namely, primary zone, intermediate zone, dilution zone and wall cooling, and from these the temperature distribution in the liner and at walls as well as the temperature quality at the exit of the combustion chamber are predicted. The design optimization is carried out using the CFD results with validation using experimental investigations.

scholarly journals Analysis of Efficiency upon Enhancing the Fuel Combustion Completeness in the GTU Burners Using Fuel Gas Heating up

2021 ◽  
pp. 88-98
Author(s):  
Ahiley Pekov ◽  
◽  
Nikolai Bachev ◽  
Alena Shilova ◽  
Oleg Matyunin ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Combustion Efficiency ◽  
Fuel Combustion ◽  
Fuel Gas ◽  
Temperature Changes ◽  
Gas Heating ◽  
Different Temperatures ◽  
Design Characteristics ◽  
Heating Up

One main characteristic of the gas turbine unit (GTU) burner is its fuel combustion completeness, which affects directly the efficiency of the power plant along with CO and unburnt hydrocarbons CnHm emissions. The aim of this work was the research on the application of the fuel heating-up as an alternative method for increasing the fuel combustion completeness and controlling the emission of harmful agents. This goal is achieved by obtaining experimental data on the emissions of CO and NOx at different temperatures of the fuel gas supply to the combustion chamber. The most significant result of the work is the experimentally confirmed possibility of increasing the combustion efficiency (decreasing CO) by heating the fuel gas while maintaining constant gas-dynamic characteristics of the chamber. The significance of the results obtained consists in the experimental confirmation of the combustion quality control only by heating the fuel gas without changing the operating and design characteristics of the combustion chamber. The fuel combustion low completeness can cause the burner unstable operation in the form of the unsteady pre-blowout burning combined with the pressure oscillations in the burner. At present, methods for ensuring the increase in stability and completeness of the fuel combustion are related to the air rate and temperature changes at the inlet. However, the use of these methods can be unwanted because of their causing the decrease in the coefficient of efficiency and in the resource of the ‘hot part’ of the gas-turbine facility.

THERMO ACOUSTIC PROCESSES IN LOW EMISSION COMBUSTION CHAMBER OF GAS TURBINE ENGINE CAPACITY 25 MW

2019 ◽  
pp. 86-90
Author(s):  
Sergey Serbin
Keyword(s):  
Mathematical Models ◽  
Combustion Chamber ◽  
Gas Turbine ◽  
Three Dimensional ◽  
Fuel Mixture ◽  
Gas Turbine Engine ◽  
Operational Parameters ◽  
Combustion Chambers ◽  
Turbine Engine ◽  
Low Emission

The appliance of modern tools of the computational fluid dynamics for the investigation of the pulsation processes in the combustion chamber caused by the design features of flame tubes and aerodynamic interaction compressor, combustor and turbine is discussed. The aim of the research is to investigate and forecast the non-stationary processes in the gas turbine combustion chambers. The results of the numerical experiments which were carried out using three-dimensional mathematical models in gaseous fuels combustion chambers reflect sufficiently the physical and chemical processes of the unsteady combustion and can be recommended to optimize the geometrical and operational parameters of the low-emission combustion chamber. The appliance of such mathematical models are reasonable for the development of new samples of combustors which operate at the lean air-fuel mixture as well as for the modernization of the existing chambers with the aim to develop the constructive measures aimed at reducing the probability of the occurrence of the pulsation combustion modes. Keywords: gas turbine engine, combustor, turbulent combustion, pulsation combustion, numerical methods, mathematical simulation.

Characteristics of Deposits in Gas Turbine Combustion Chambers Using Synthetic and Conventional Jet Fuels

2013 ◽  
Vol 135 (7) ◽  
Author(s):  
Greg Pucher ◽  
William Allan ◽  
Pierre Poitras
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Alternative Fuels ◽  
Large Scale ◽  
Aviation Fuel ◽  
Jet Fuels ◽  
Combustion Chambers ◽  
Fuel Blend ◽  
Synthetic Fuel ◽  
Camelina Oil

The synthetic fuel industry is poised to experience large-scale growth and profoundly affect current aviation fuel infrastructure. New candidate technologies, such as Camelina oil-derived synthetic fuel have been demonstrated to not only provide satisfactory quasi drop-in characteristics for conventional fuels, but in life cycle analysis studies have also been shown to potentially offer positive improvements relative to conventional feedstocks with respect to economic, environmental, and land use considerations. As part of a multiyear study at the Royal Military College of Canada to evaluate combustion related parameters of fuel additives and alternative fuels for gas turbine applications, a Camelina-derived synthetic fuel blend was assessed to determine potential combustion related benefits as compared to conventional and other synthetic blends. The Combustion Chamber Sector Rig (CCSR) which houses a Rolls Royce T-56-A-15 combustion section was utilized for the evaluation of emissions and deposits. Following combustion testing, several combustion system components, including the combustion chamber, fuel nozzle, and igniter plug were analyzed for relative levels of deposit build-up. As with other Fischer Tropsch derived synthetic fuels, there were positive benefits found with Camelina blends in terms of emissions performance and deposit production tendencies.

Effect of Vortex Flow on Heat Transfer to Combustion Chamber Wall

2004 ◽  
Author(s):  
S. Jahangirian ◽  
M. Abarham ◽  
A. Ghafourian ◽  
M. H. Saidi
Keyword(s):  
Heat Transfer ◽  
Combustion Chamber ◽  
Wall Temperature ◽  
Wide Spectrum ◽  
Swirl Flow ◽  
Combustion Chambers ◽  
Flow Rates ◽  
Mass Flow Rates ◽  
Bidirectional Flow ◽  
Further Development

A new experimental facility was designed, fabricated and tested to model and study the effect of bidirectional swirl flow on the rate of heat transfer to combustion chamber walls in many applications. Heat transfer to combustion chamber walls is an unwanted phenomenon. Reduction of this heat transfer can result in time and cost saving methods in design and fabrication of combustion chambers. The experimental study was performed by using propane and air with oxygen as fuel and oxidizer respectively. The location of injection ports and geometry of combustion chamber are flexible and could be varied. Tests were performed with different mass flow rates of fuel and oxidizer. For the same flow rates and with the presence of bidirectional flow, a wall temperature reduction of up to 50% was observed. In cases where only some of the oxidizer was injected from the chamber end to generate the bidirectional swirl flow, highest efficiency and lowest wall temperature existed. This can be due to better mixing of fuel and oxidizer and absence of hot spots in the combusting core. Further development of this technique enables combustion chamber manufacturers in a wide spectrum of industries such as gas turbine manufacturers to use less expensive and more available material in their production of combustors.

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