scholarly journals Effect of Inlet Conditions on Lean Premixed Gas Turbine Combustor Performance

1998 ◽  
Author(s):  
Suresh R. Vilayanur ◽  
Nell T. Davis ◽  
Scott Samuelsen
Keyword(s):  
Equivalence Ratio ◽  
Statistical Approach ◽  
Recirculation Zone ◽  
Cfd Modeling ◽  
Gas Turbine Combustor ◽  
Fuel Distribution ◽  
Multiple Parameters ◽  
Significant Parameter ◽  
Concentration Peak ◽  
Inlet Conditions

To address the complex effect of inlet parameters on combustor performance, a statistically based technique is applied to a model, premixed natural gas fired combustor. In this way, multiple parameters are simultaneously investigated for their contribution to combustion performance. Atmospheric tests are performed at conditions otherwise representative of industrial combustors: 670 K. inlet preheat and an equivalence ratio of 0.47. Experimental results, in combination with CFD modeling, reveal that (1) the statistical approach is an effective tool by which parameters that dominate performance can be identified, (2) the principal statistically significant parameter linked to NOx production is the inlet fuel distribution, (3) the principal statistically significant parameter linked to CO production is swirl solidity, and (4) an inlet fuel distribution that features a concentration peak in line with the shear layer of the recirculation zone yields NOx levels comparable to a well premixed case.

Performance of a Dry Low-NOx Gas Turbine Combustor Designed With a New Fuel Supply Concept

2002 ◽  
Vol 124 (4) ◽  
pp. 771-775 ◽  
Author(s):  
T. Wakabayashi ◽  
S. Ito ◽  
S. Koga ◽  
M. Ippommatsu ◽  
K. Moriya ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Equivalence Ratio ◽  
Gas Turbine Combustor ◽  
Lean Premixed Combustion ◽  
Fuel Distribution ◽  
Fuel Supply ◽  
Stable Combustion ◽  
Fuel Jet ◽  
Combustion Region ◽  
Pressurized Combustion

This paper describes the performance of a dry low-NOx gas turbine combustor designed with a new fuel supply concept. This concept uses automatic fuel distribution achieved by an interaction between the fuel jet and the airflow. At high loads, most of the fuel is supplied to the lean premixed combustion region for low-NOx, while at low loads, it is supplied to the pilot combustion region for stable combustion. A numerical simulation was carried out to estimate the equivalence ratio in the fuel supply unit. Next, through the pressurized combustion experiments on the combustor with this fuel supply unit using natural gas as fuel, it was confirmed that NOx emissions were reduced and stable combustion was achieved over a wide equivalence ratio range.

Performance of a Dry Low-NOx Gas Turbine Combustor Designed With a New Fuel Supply Concept

2001 ◽  
Author(s):  
Tsutomu Wakabayashi ◽  
Seiichi Ito ◽  
Shonosuke Koga ◽  
Masamichi Ippommatsu ◽  
Koji Moriya ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Equivalence Ratio ◽  
Gas Turbine Combustor ◽  
Lean Premixed Combustion ◽  
Fuel Distribution ◽  
Fuel Supply ◽  
Stable Combustion ◽  
Fuel Jet ◽  
Combustion Region ◽  
Pressurized Combustion

This paper describes the performance of a dry low-NOx gas turbine combustor designed with a new fuel supply concept. This concept uses automatic fuel distribution achieved by an interaction between the fuel jet and the airflow. At high loads, most of the fuel is supplied to the lean premixed combustion region for low-NOx, while at low loads, it is supplied to the pilot combustion region for stable combustion. A numerical simulation was carried out to estimate the equivalence ratio in the fuel supply unit. Next, through the pressurized combustion experiments on the combustor with this fuel supply unit using natural gas as fuel, it was confirmed that NOx emissions were reduced and stable combustion was achieved over a wide equivalence ratio range.

scholarly journals Development of Micro Gas Turbine Combustor with a Recirculation Zone Induced by an Upward Swirl

2008 ◽  
Vol 3 (1) ◽  
pp. 204-215
Author(s):  
Kousaku YOTORIYAMA ◽  
Shunsuke AMANO ◽  
Hidetomo FUJIWARA ◽  
Tomohiko FURUHATA ◽  
Masataka ARAI
Keyword(s):  
Gas Turbine ◽  
Recirculation Zone ◽  
Gas Turbine Combustor ◽  
Micro Gas Turbine

Simulation of HCCI Combustion Characteristics for Low RON Gasoline Surrogate Fuels

2014 ◽  
Vol 694 ◽  
pp. 54-58
Author(s):  
Ling Zhe Zhang ◽  
Ya Kun Sun ◽  
Su Li ◽  
Qing Ping Zheng
Keyword(s):  
Equivalence Ratio ◽  
Chemical Kinetic ◽  
Combustion Characteristics ◽  
Material Strength ◽  
Inlet Temperature ◽  
Compression Ignition Engine ◽  
Chemical Kinetic Model ◽  
Hcci Engine ◽  
Surrogate Fuels ◽  
Inlet Conditions

A reduced chemical kinetic model (103species and 468 reactions) for new low-RON(research octane number) gasoline surrogate fuels has been proposed. Simulations explored for ignition delay time have been compared with experimental data in shock tubes at pressure of 10atm-55 atm and temperatue of 600-1400 K (fuel/air equivalence ratio=0.5,1.0,2.0 and EGR rate=0, 20%). The simulation data presented 15% enlargement compared with experiments showed applicability of the new kinetic mode in this work. A combustion simulation model has been build for HCCI(homogeneous charge compression ignition) engine with Chemkin-pro. The effects of different air inlet temperature, inlet pressure, engine speed and the fuel air equivalence ratio on the combustion characteristics of the fuel were researched. The results indicated the combustion in an HCCI engine worked sufficiently with lean mixtures and low speed. Meanwhile the material strength could be influenced when the inlet conditions changed. This helps to promote the low-RON gasoline surrogate fuel application in the HCCI engine.

scholarly journals Applications of CFD Method to Gas Mixing Analysis in a Large-Scaled Tank

2007 ◽  
Author(s):  
Si Y. Lee ◽  
Richard A. Dimenna
Keyword(s):  
Liquid Surface ◽  
Operating Conditions ◽  
Evolution Rate ◽  
Cfd Modeling ◽  
Local Concentration ◽  
Gas Mixing ◽  
Recirculation Flow ◽  
Air Inlet ◽  
Inlet Conditions ◽  
Vapor Space

The computational fluid dynamics (CFD) modeling technique was applied to the estimation of maximum benzene concentration for the vapor space inside a large-scaled and high-level radioactive waste tank at Savannah River site (SRS). The objective of the work was to perform the calculations for the benzene mixing behavior in the vapor space of Tank 48 and its impact on the local concentration of benzene. The calculations were used to evaluate the degree to which purge air mixes with benzene evolving from the liquid surface and its ability to prevent an unacceptable concentration of benzene from forming. The analysis was focused on changing the tank operating conditions to establish internal recirculation and changing the benzene evolution rate from the liquid surface. The model used a three-dimensional momentum coupled with multi-species transport. The calculations included potential operating conditions for air inlet and exhaust flows, recirculation flow rate, and benzene evolution rate with prototypic tank geometry. The flow conditions are assumed to be fully turbulent since Reynolds numbers for typical operating conditions are in the range of 20,000 to 70,000 based on the inlet conditions of the air purge system. A standard two-equation turbulence model was used. The modeling results for the typical gas mixing problems available in the literature were compared and verified through comparisons with the test results. The benchmarking results showed that the predictions are in good agreement with the analytical solutions and literature data. Additional sensitivity calculations included a reduced benzene evolution rate, reduced air inlet and exhaust flow, and forced internal recirculation. The modeling results showed that the vapor space was fairly well mixed and that benzene concentrations were relatively low when forced recirculation and 72 cfm ventilation air through the tank boundary were imposed. For the same 72 cfm air inlet flow but without forced recirculation, the heavier benzene gas was stratified. The results demonstrated that benzene concentrations were relatively low for typical operating configurations and conditions. Detailed results and the cases considered in the calculations will be discussed here.

Gas Turbine Combustor Design Parameter Analysis for Soot Reduction Using CFD

1999 ◽  
Author(s):  
D. Scott Crocker ◽  
Rahul Puri
Keyword(s):  
Software Package ◽  
Negative Impact ◽  
Experimental Testing ◽  
Stability Margin ◽  
Primary Objective ◽  
Parameter Analysis ◽  
Cfd Modeling ◽  
Gas Turbine Combustor ◽  
Primary Zone ◽  
Selection Of

AlliedSignal’s F124 combustor is analyzed using CFD as part of an effort to improve the design of the combustor. A reduction of soot emissions, without negative impact on other performance features such as liner life and lean stability, was the primary objective. The existing F124 combustor (TFE1042) was modeled using the commercial CFD-ACE+ software package to validate the CFD results and provide a basis for comparison for the modified design. Two design of experiment (DOE) matrices of the redesigned combustor were analyzed using CFD modeling. The results of the CFD solutions led to the selection of two configurations for combustor rig experimental testing. The test configurations were selected based on CFD predicted trends for smoke, ignition, lean stability and pattern factor. Engine tests demonstrated a smoke number reduction from more than 40 to less than 10. Lean stability was degraded as a result of a leaner primary zone, but adequate lean stability margin was maintained.

Parametric Study of Emissions From Low Calorific Value Syn-Gas Combustion, With Variation of Fuel Distribution, in a Prototype Three Sector Burner

2011 ◽  
Author(s):  
Ivan R. Sigfrid ◽  
Ronald Whiddon ◽  
Marcus Alde´n ◽  
Jens Klingmann
Keyword(s):  
Equivalence Ratio ◽  
Flame Temperature ◽  
Calorific Value ◽  
Discrete Control ◽  
Test Sequence ◽  
Gas Combustion ◽  
Fuel Distribution ◽  
Gasification Process ◽  
Dilute Gas ◽  
Main Burner

The emission composition is measured for a prototype burner while varying the equivalence ratio in discrete portions of the burner. The burner is a three sector system, consisting of a separate igniter, pilot/stabilizer and main burner. The design allows for discrete control of equivalence ratio in each of the three sectors. The ignition sector, designated RPL (Rich-Pilot-Lean), operates from rich to lean equivalence values, and serves to ignite the pilot sector, which, in turn, stabilizes the main combustion sector. All three burner sections are premixed. The burner is operated at atmospheric pressure with inlet flows heated to 650 K (±8 K). Tests were performed for three gases: methane, a model syngas (10% CH4, 22.5% CO, 67.5% H2), and dilute syngas. The dilute gas includes sufficient nitrogen to lower the heating value to 15 MJ/m3. The model syngas and diluted syngas are representative of fuels produced by gasification process. The burner emissions, specifically, CO, CO2, O2 and NOx, are measured while holding the RPL equivalence value constant and varying the equivalence ratio of the pilot and main sectors. The equivalence ratios for pilot and main sectors are chosen such that the total burner equivalence ratios remain constant during a test sequence. The target total equivalence ratio for each gas is chosen such that all experiments should have the same flame temperature.

Sign in / Sign up

Export Citation Format

Share Document