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.

Experimental Study of Atomization Characteristic of Air Blast Atomizer

2013 ◽  
Vol 300-301 ◽  
pp. 185-188 ◽  
Author(s):  
Kai Liu ◽  
Li Yan Sun
Keyword(s):  
Experimental Data ◽  
Test Methods ◽  
Spray Angle ◽  
Fuel Injector ◽  
Heavy Duty ◽  
Air Blast ◽  
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.

Experimental Study on the Atomization Behavior of Fuel Nozzle of Low Pollution

2011 ◽  
Vol 66-68 ◽  
pp. 307-310
Author(s):  
Xu Li ◽  
Kai Liu
Keyword(s):  
Experimental Data ◽  
Experimental Study ◽  
Combustion Efficiency ◽  
Outlet Temperature ◽  
Design Development ◽  
Heavy Duty ◽  
Group Design ◽  
Fuel Nozzle ◽  
Heavy Duty Gas Turbine ◽  
Reliable Basis

Experimental investigation results of the fuel nozzle group in a heavy-duty gas turbine are presented. Atomization characteristic has great impact about combustion efficiency, ignition performance, and outlet temperature field of combustor. Obtained atomization characteristic about spray particle size and distribution using LDV/PDPA system. These experimental data have provided reliable basis for the nozzle group design, development and operation.

Experimental Study on Pollution Emissions of the DLN Combustor

2011 ◽  
Vol 138-139 ◽  
pp. 958-961
Author(s):  
Xu Li ◽  
Kai Liu
Keyword(s):  
Experimental Study ◽  
Gas Turbine ◽  
Combustion Efficiency ◽  
Test System ◽  
Heavy Duty ◽  
Pressure Test ◽  
Design Requirements ◽  
Heavy Duty Gas Turbine ◽  
Pollution Emissions ◽  
Reliable Basis

Experimental study of combustor of heavy-duty gas turbine (E) which is the first independent intellectual property rights has been finished on high-pressure test system by China Gas Turbine Establishment of AVIVI. The content of CO and UHC are very low, the combustion is stable and efficient, the combustion efficiency is over 99%; pollution emissions (NOx) are 225mg/m3 (15%O2) under rated condition, which is not meet the design requirements. The results indicated: The radio of on-watch-fuel is large, which makes the content of NOx is large; uneven premixed fuel is another important reason that makes the content of NOx is large. The conclusion has provided the reliable basis for gas turbine’s design and development.

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.

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.

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