Integrated Experimental and Numerical Approach for Fuel-Air Mixing Prediction in a Heavy-Duty Gas Turbine LP Burner

2000 ◽  
Vol 123 (4) ◽  
pp. 803-809 ◽  
Author(s):  
G. Mori ◽  
S. Razore ◽  
M. Ubaldi ◽  
P. Zunino
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Numerical Procedure ◽  
Turbulence Models ◽  
Mie Scattering ◽  
Optical Measurements ◽  
Heavy Duty ◽  
Experimental Apparatus ◽  
Air Mixing ◽  
Heavy Duty Gas Turbine

An integrated experimental-numerical procedure has been developed for fuel-air mixing prediction in a heavy-duty gas turbine burner. Optical measurements of the degree of mixing have been performed in a full-scale test rig operating with cold flow. Experimental data have been utilized to validate a CFD RANS numerical model. In fact, it is recognized that the turbulence behavior of jets in swirling air-flow stream is not accurately described by standard k-ε turbulence models; therefore advanced turbulence models have been assessed by means of experimental data. The degree of mixing between simulated fuel and air streams has been evaluated at the burner exit section by means of a planar Mie scattering technique. The experimental apparatus consists of a pulsed Nd:YAG laser and a high resolution CCD video camera connected to a frame grabber. The acquired instantaneous images have been processed through specific procedures that also take into account the laser beam spatial nonuniformity. A second-order discretization scheme with a RSM turbulence model gives the best accordance with the experimental data. Such CFD model will be part of a more general method addressed to numerical prediction of turbulent combustion flames in LP technology.

Integrated Experimental and Numerical Approach for Fuel-Air Mixing Prediction in a Heavy-Duty Gas Turbine LP Burner

2000 ◽  
Author(s):  
Giulio Mori ◽  
Sandro Razore ◽  
Marina Ubaldi ◽  
Pietro Zunino
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Numerical Procedure ◽  
Turbulence Models ◽  
Mie Scattering ◽  
Optical Measurements ◽  
Heavy Duty ◽  
Experimental Apparatus ◽  
Air Mixing ◽  
Heavy Duty Gas Turbine

An integrated experimental-numerical procedure has been developed for fuel-air mixing prediction in a heavy-duty gas turbine burner. Optical measurements of the degree of mixing have been performed in a full-scale test rig operating with cold flow. Experimental data have been utilized to validate a CFD RANS numerical model. In fact, it is recognized that the turbulence behavior of jets in swirling air-flow stream is not accurately described by standard k-ε turbulence models; therefore advanced turbulence models have been assessed by means of experimental data. The degree of mixing between simulated fuel and air streams has been evaluated at the burner exit section by means of a planar Mie scattering technique. The experimental apparatus consists of a pulsed Nd:YAG laser and a high resolution CCD video camera connected to a frame grabber. The acquired instantaneous images have been processed through specific procedures that also take into account the laser beam spatial non-uniformity. A second order discretization scheme with a RSM turbulence model gives the best accordance with the experimental data. Such CFD model will be part of a more general method addressed to numerical prediction of turbulent combustion flames in LP technology.

Numerical Re-Design of a Heavy Duty Gas Turbine Hydrogen-Fired Combustion Chamber

2010 ◽  
Author(s):  
Alessandro Marini ◽  
Giovanni Riccio ◽  
Francesco Martelli ◽  
Stefano Sigali ◽  
Stefano Cocchi
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Fuel Injection ◽  
Nox Reduction ◽  
Airflow Rate ◽  
Heavy Duty ◽  
Air Mixing ◽  
Dry Conditions ◽  
Heavy Duty Gas Turbine ◽  
Full Scale Tests

The present work describes the numerical methodology followed to characterize and study modifications to a silo-type diffusive combustion chamber installed on a GE10, a 10 MW class heavy-duty gas turbine manufactured by GE Oil & Gas. The goal of the work was to investigate modifications to the combustion chamber to allow operation with 100% hydrogen fuel at reduced NOx production in dry conditions. The investigation focused mainly on the burner; the liner was not substantially changed. The swirler and the fuel injection holes were redesigned to achieve better fuel-air mixing and a higher airflow rate in the primary zone of the combustor, maintaining a diffusion flame scheme. The proposed modifications were analyzed using a 3D CFD RANS reactive procedure based on commercial codes. The method was previously validated by comparison with the experimental data from the full scale tests performed at the Enel Facility at Sesta, Italy. In-house codes were developed for the post-processing of the results. The numerical analysis has shown that the modified version can provide a NOx reduction up to 40%. The results are discussed focusing on the effect of fuel injection scheme on mixing quality and NOx emission containment.

Experimental Study on Atomization Characteristic of Fuel Injector of Heavy-Duty Gas Turbine

2011 ◽  
Vol 354-355 ◽  
pp. 488-491
Author(s):  
Kai Liu ◽  
Bao Cheng Zhang ◽  
Hong An Ma
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Test Methods ◽  
Spray Angle ◽  
Fuel Injector ◽  
Heavy Duty ◽  
Group Design ◽  
Design Requirements ◽  
Heavy Duty Gas Turbine ◽  
Reliable Basis

Experimental investigation results of the fuel injector group in a heavy-duty gas turbine are presented. Atomization characteristic has great impact about combustion, inflame, temperature field of outlet. Obtained atomization characteristic about spray particle size and spray angle using LDV/PDPA system, determined dimension of injector group. On the basis of these tests, the combustion testing of the injector group in the flame tube is made, its every targets are arrived in the design requirements. This has demonstrated: the test systems and test methods are practical, feasible and reliable. These experimental data have provided the reliable basis for the injector group design and development.

Fretting Fatigue Cracking of an Arresting Feature in a Turbine Disk of a Heavy-Duty Gas Turbine Engine

2018 ◽  
Vol 55 (1) ◽  
pp. 37-46
Author(s):  
A. Neidel ◽  
M. Giller ◽  
S. Riesenbeck
Keyword(s):  
Gas Turbine ◽  
Fatigue Cracking ◽  
Fretting Fatigue ◽  
Gas Turbine Engine ◽  
Turbine Disk ◽  
Heavy Duty ◽  
Turbine Engine ◽  
Heavy Duty Gas Turbine

A New Superalloy Enabling Heavy Duty Gas Turbine Wheels for Improved Combined Cycle Efficiency

2017 ◽  
Author(s):  
Andrew Detor ◽  
◽  
Richard DiDomizio ◽  
Don McAllister ◽  
Erica Sampson ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Combined Cycle ◽  
Heavy Duty ◽  
Heavy Duty Gas Turbine ◽  
Cycle Efficiency

Impact of Different Film-Cooling Modes at Trailing Edge on the Aerodynamic Performance of Heavy Duty Gas Turbine Cascade

2011 ◽  
Vol 84-85 ◽  
pp. 259-263
Author(s):  
Xun Liu ◽  
Song Tao Wang ◽  
Xun Zhou ◽  
Guo Tai Feng
Keyword(s):  
Gas Turbine ◽  
Film Cooling ◽  
Large Mass ◽  
Turbine Cascade ◽  
Heavy Duty ◽  
Trailing Edge ◽  
Central Difference ◽  
Adiabatic Effectiveness ◽  
Heavy Duty Gas Turbine ◽  
The Impact

In this paper, the trailing edge film cooling flow field of a heavy duty gas turbine cascade has been studied by central difference scheme and multi-block grid technique. The research is based on the three-dimensional N-S equation solver. By way of analysis of the temperature field, the distribution of profile pressure, and the distribution of film-cooling adiabatic effectiveness in the region of trailing edge with different cool air injection mass and different angles, it is found that the impact on the film-cooling adiabatic effectiveness is slightly by changing the injection mass. The distribution of profile pressure dropped intensely at the pressure side near the injection holes line with the large mass cooling air. The cooling effect is good in the region of trailing edge while the injection air is along the direction of stream.

Thermoacoustic Stability Analysis of a Full-Annular Lean Combustor for Heavy-Duty Applications

2021 ◽  
Author(s):  
Daniele Pampaloni ◽  
Antonio Andreini ◽  
Alessandro Marini ◽  
Giovanni Riccio ◽  
Gianni Ceccherini
Keyword(s):  
Stability Analysis ◽  
Gas Turbine ◽  
Flame Temperature ◽  
Numerical Procedure ◽  
Pollutant Emissions ◽  
Computational Time ◽  
Heavy Duty ◽  
Operational Parameters ◽  
3D Fem ◽  
Wide Range

Abstract Thermoacoustic characterization of gas turbine combustion systems is of primary importance for successful development of gas turbine technology, to meet the stringent targets on pollutant emissions. In this context, it becomes more and more necessary to develop reliable tools to be used in the industrial design process. The dynamics of a lean-premixed full-annular combustor for heavy-duty applications has been numerically studied in this work. The well-established CFD-SI method has been used to investigate the flame response varying operational parameters such as the flame temperature (global equivalence ratio) and the fuel split between premixed and pilot fuel injections: such a wide range experimental characterization represents an opportunity to validate the employed numerical methods and to give a deeper insight into the flame dynamics. URANS simulations have been performed, due to their affordable computational costs from the industrial perspective, after validating their accuracy through the comparison against LES results. Furthermore, an approach where the pilot and the premixed flame responses are analyzed separately is proposed, exploiting the independence of their evolution. The calculated FTFs have been implemented in a 3D FEM model of the chamber, in order to perform linear stability analysis and to validate the numerical approach. A boundary condition for rotational periodicity based on Bloch-Wave theory has been implemented into the Helmholtz solver and validated against full-annular chamber simulations, allowing a significant reduction in computational time. The reliability of the numerical procedure has been assessed through the comparison against full-annular experimental results.

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