Effects of Inlet Parameters on Combustion Performance in Gas Turbine Combustor
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Yingwen Yan
Abstract
The effects of different inlet parameters such as inlet temperature and pressure on combustion performance in a single-head combustor were experimentally investigated in this study. The combustion efficiency, total pressure loss, and CO and NO emissions at the outlet of a single-head rectangular combustor with different types of swirlers were separately measured. The experimental results showed that the inlet parameters had obvious effects on the combustion performance, with critical values of 600 K for the inlet temperature and 3.5 bar for the inlet pressure. The combustion efficiency noticeably increased with an increase in the inlet pressure or temperature below these values; however, when either of the inlet parameters was above the critical value, the combustion efficiency was approximately 100 %; that is, the combustion efficiency changed little with an increase in inlet temperate or pressure. When the inlet temperature or pressure increased, NO emission increased but CO emission decreased. By fitting curves to analyze the experimental data, the empirical relationships between the emissions and the inlet temperature were observed to be
Funding statement: This work was supported by the Fundamental Research Funds for the Central Universities (No. NS2015029).
References
1. Wei S. Advanced gas turbine combustor design and development. Shanghai: Profile of Shanghai Jiao Tong University Press, 2014.Search in Google Scholar
2. Huang Y. Combustion and combustor. Beijing: Beihang University Press, 2009.Search in Google Scholar
3. Martelli F, Riccio G, Benelli G, Cecchini D, Carrai L. Scaling from atmospheric pressure rig to full-scale pressure for the emission measurement from a gas turbine combustor. Proceedings of ASME Turbo Expo 2001, June 4–7, 2001, New Orleans, Louisiana, 2001-GT–0070.10.1115/2001-GT-0070Search in Google Scholar
4. Cui Y, Xu G, Yu B, Nie C, Huang W. The effects of pressure on gas turbine combustor performance: an investigation via numerical simulation. Proceedings of GT2006 ASME Turbo Expo 2006. May 8–11, 2006, Barcelona, Spain. GT2006–90635.Search in Google Scholar
5. Bhargava A, Kendrick D, Colket M, Sowa W, Casleton K, Maloney D. Pressure effect on NOx and CO emissions in industrial gas turbines. Proceeding of ASME Turbo Expo, May 8–11, 2000, Munich Germany, 2000-GT–97.10.1115/2000-GT-0097Search in Google Scholar
6. Mishra RK, Singh K. Effect of operating conditions on the emission characteristics of an annular combustor. J Aerospace Sci Technol 2009;61(2):305–11.Search in Google Scholar
7. Mishra RK, Ramanujam PS, Badrinath C, Bhat MN. Influence of operating pressure on the performance of an aero gas turbine combustor, XVII ISABE, Munich, Germany, 4–9 September, 2005.Search in Google Scholar
8. Wang F, Kong W, Wang B, Lao S, Zhang P. Effects of inlet temperature on combustion characteristics within a micro gas turbine combustor. J Eng Thermophys 2007;28(2):331–4.Search in Google Scholar
9. Wang F, Kong W, Wang B, Lao S, Zhang P. Fuel effects on gas turbine combustion-liner temperature, pattern factor, and pollutant emissions. J Aircraft 1984;21(11):887–98.10.2514/3.45059Search in Google Scholar
10. Mellor AM. Semi-empirical correlations for gas turbine emissions, ignition, and flame stabilization. Prog Energy Combust Sci 1980;6(4):347–58.10.1016/0360-1285(80)90010-6Search in Google Scholar
11. Mongia HC. On Initiating 3rd generation of correlations for gaseous emissions of aero-propulsion engines. 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 4–7 January 2010, Orlando, Florida, AIAA 2010–1529.10.2514/6.2010-1529Search in Google Scholar
12. Rizk NK, Mongia HC. Semianalytical correlations for NOx, CO and UHC emissions. Allison Gas Turbine Division General Motors Corporation Indianapolis, Indiana, 92-GT–130.Search in Google Scholar
13. Mongia HC. N+3 and N+4 generation aeropropulsion engine combustors: Part 5: NOx, CO, HC and Smoke Emissions. 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, July 14–17, 2013, San Jose, CA, AIAA 2013–3653.10.2514/6.2013-3653Search in Google Scholar
14. Mongia HC. N + 3 and N + 4 generation aeropropulsion engine combustors: Part 6: operating conditions, target goals and lifted jets. 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, July 14–17, 2013, San Jose, CA. AIAA 2013–3654.10.2514/6.2013-3654Search in Google Scholar
15. Jin R. Aero gas turbine combustor. Beijing: China Astronautic Publishing House, 1988.Search in Google Scholar
16. Zhao J, Wang S, Liu Y. Exhaust pollution and noise of thermal power plant, 2nd ed. Beijing: Science Publishing Company, 2009.Search in Google Scholar
17. Held TJ, Mueller MA, Li SC, Mongia HC. A data-driven model For NOx, CO and UHC emissions for a dry low emissions gas turbine combustor. 37th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 8–11 July 2001 Salt Lake City, AIAA–2001–3425.10.2514/6.2001-3425Search in Google Scholar
18. Mongia HC. On continuous NOx reduction of aero-propulsion engines. 48th AIAA Aerospace Sciences Meeting, 4–7 January 2010, Orlando, Florida, AIAA 2010–1329.10.2514/6.2010-1329Search in Google Scholar
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Articles in the same Issue
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- Effects of Inlet Parameters on Combustion Performance in Gas Turbine Combustor
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Articles in the same Issue
- Frontmatter
- Editorials
- Reasons for Triple-Funding of the Jet-Engine-Industry to Meet 2020–2040 6th-Gen-Challenge: Counter-Air Penetration, CAP
- Reasons for triple-funding of the jet-engine-industry to meet 2020-2040 6TH-Gen-Challenge: Counter-Air Penetration, CAP
- Original Research Articles
- Experimental Investigation of Reacting Flow Characteristics in a Dual-Mode Scramjet Combustor
- Experimental Investigation of Shape Transition Effects on Isolator Performance
- Effects of Inlet Parameters on Combustion Performance in Gas Turbine Combustor
- Gas Turbine Engine Gas-path Fault Diagnosis Based on Improved SBELM Architecture
- The Effects of Turbulent Burning Velocity Models in a Swirl-Stabilized Lean Premixed Combustor
- Inverse Simulation for Gas Turbine Engine Control through Differential Algebraic Inequality Formulation
- Aerodynamic Optimization of Turbine Based Combined Cycle Nozzle
- Nonlinear System Modeling based on System Equilibrium Manifold
- Numerical Study on Heat Transfer Enhancement of Swirl Chamber on Gas Turbine Blade
