Evaluation of Lean Axially Staged Combustion by Multi-Sector Combustor Tests Under LTO Cycle Conditions of a Small Aircraft Engine

2013 ◽  
Author(s):  
Takeshi Yamamoto ◽  
Kazuo Shimodaira ◽  
Yoji Kurosawa ◽  
Seiji Yoshida
Keyword(s):  
Technology Development ◽  
Pressure Ratio ◽  
Nox Reduction ◽  
Aircraft Engine ◽  
Development Project ◽  
Civil Aviation ◽  
Nox Emissions ◽  
Fuel Nozzle ◽  
Conducting Research ◽  
Combustion Tests

JAXA is conducting research and development on aircraft engine technologies to reduce environmental impact in the Technology Development Project for Clean Engines (TechCLEAN). As a part of the project, combustion technologies have been developed with an aggressive target that is an 80% reduction over the NOx threshold of the fourth Committee on Aviation Environmental Protection (CAEP/4) of the International Civil Aviation Organization (ICAO). Lean staged fuel nozzles have been developed and tested using a single-sector combustor under Landing and Take-off (LTO) cycle conditions of the target engine with a rated output of 40 kN and an overall pressure ratio of 25.8. A reduction of 82.2% in LTO NOx emissions relative to the ICAO CAEP/4 standard and drastic reductions in smoke and carbon monoxide (CO) emissions were resulted by single-sector combustor tests of a lean staged combustor with an additional premixed fuel nozzle (ECF: Emission Control Fuel nozzle). After the test, the pilot mixer of the single-sector combustor was improved and an additional 2.5% NOx reduction was achieved by combustion tests. As a next step, a multi-sector combustor with ECF was developed and tested. The test results show that the combustor enables a reduction of 82.2% in LTO NOx emissions relative to the ICAO CAEP/4 standard, though unburnt hydrocarbons (HC) and CO emissions are increased. Temperature distributions in the combustor exit plane were also evaluated.

scholarly journals Emission Reduction of Fuel-Staged Aircraft Engine Combustor Using an Additional Premixed Fuel Nozzle

2013 ◽  
Vol 135 (3) ◽  
Author(s):  
Takeshi Yamamoto ◽  
Kazuo Shimodaira ◽  
Seiji Yoshida ◽  
Yoji Kurosawa
Keyword(s):  
Technology Development ◽  
Pressure Ratio ◽  
Aircraft Engine ◽  
Development Project ◽  
Civil Aviation ◽  
Test Results ◽  
Technology Development Project ◽  
Fuel Nozzle ◽  
Conducting Research ◽  
Japan Aerospace Exploration Agency

The Japan Aerospace Exploration Agency (JAXA) is conducting research and development on aircraft engine technologies to reduce environmental impact for the Technology Development Project for Clean Engines (TechCLEAN). As a part of the project, combustion technologies have been developed with an aggressive target that is an 80% reduction over the NOx threshold of the International Civil Aviation Organization (ICAO) Committee on Aviation Environmental Protection (CAEP)/4 standard. A staged fuel nozzle with a pilot mixer and a main mixer was developed and tested using a single-sector combustor under the target engine's landing and takeoff (LTO) cycle conditions with a rated output of 40 kN and an overall pressure ratio of 25.8. The test results showed a 77% reduction over the CAEP/4 NOx standard. However, the reduction in smoke at thrust conditions higher than the 30% MTO condition and of CO emission at thrust conditions lower than the 85% MTO condition are necessary. In the present study, an additional fuel burner was designed and tested with the staged fuel nozzle in a single-sector combustor to control emissions. The test results show that the combustor enables an 82% reduction in NOx emissions relative to the ICAO CAEP/4 standard and a drastic reduction in smoke and CO emissions.

Optimization of a Small Aircraft Combustor to Reduce NOx Emissions Under Practical Conditions

2007 ◽  
Author(s):  
Mitsumasa Makida ◽  
Hideshi Yamada ◽  
Kazuo Shimodaira ◽  
Takeshi Yamamoto ◽  
Shigeru Hayashi
Keyword(s):  
Pressure Ratio ◽  
Load Condition ◽  
Atmospheric Condition ◽  
Aircraft Engine ◽  
Civil Aviation ◽  
Nox Emissions ◽  
Lean Burn ◽  
Lean Blowout ◽  
Fuel Nozzle ◽  
The Rich

A series of research experiments under practical conditions has been conducted to develop a combustor for a small-class aircraft engine (with the pressure ratio of about 20). In the previous research experiments, including ignition and emission tests under atmospheric pressure, we applied a single airblast fuel nozzle and utilized the rich-burn quick-quench lean-burn (RQL) combustion approach. The combustor was tuned to show the behavior of the RQL under the atmospheric condition. In this paper, the results of single-sector combustor experiments under the practical temperature and pressure conditions are presented, in which RQL behavior is observed and NOx emissions in the ICAO (International Civil Aviation Organization) LTO (Landing and Take-Off) cycle are reduced to 45% of the ICAO CAEP4 (Committee on Aviation Environmental Protection 4) standard. Also the results of successive multi-sector combustor tests to optimize combustion performances with a more practical combustor configuration under the practical conditions are presented. The emission characteristics which are obtained are compared with those of the single-sector tests, and combustor size and configuration, air mass flow ratio and air hole positions are tuned through a series of multi-sector experiments. After the optimization, the combustor achieved the following performances; NOx emissions are reduced to less than 42% of the ICAO CAEP4 standard, CO and THC (Total Hydrocarbon) are reduced to those of 2% and 50% respectively, the lean blowout limit is kept over 220 AFR (Air to Fuel Ratio) at the idle condition and the exit temperature profile at the full load condition is sufficiently uniform (P.T.F.<0.15). The process of optimization will be discussed in this report.

Emission Reduction of Fuel Staged Aircraft Engine Combustor Using an Additional Premixed Fuel Nozzle

2012 ◽  
Author(s):  
Takeshi Yamamoto ◽  
Kazuo Shimodaira ◽  
Seiji Yoshida ◽  
Yoji Kurosawa
Keyword(s):  
Pressure Ratio ◽  
Aircraft Engine ◽  
Test Results ◽  
Drastic Reduction ◽  
Fuel Nozzle ◽  
Conducting Research ◽  
Japan Aerospace Exploration Agency ◽  
Co Emission ◽  
Fuel Burner ◽  
Additional Fuel

The Japan Aerospace Exploration Agency (JAXA) is conducting research and development on aircraft engine technologies to reduce environmental impact for the TechCLEAN project. As a part of the project, combustion technologies have been developed with an aggressive target that is an 80% reduction over the NOx threshold of the ICAO CAEP/4 standard. A staged fuel nozzle with a pilot mixer and a main mixer was developed and tested using a single-sector combustor under the target engine’s LTO cycle conditions with a rated output of 40 kN and an overall pressure ratio of 25.8. The test results showed a 77% reduction over the CAEP/4 NOx standard. A reduction in smoke was found under a higher thrust condition than the 30% MTO condition, and a reduction in CO emission was found under a lower thrust condition than the 85% MTO condition. In the present study, an additional fuel burner was designed and tested with the staged fuel nozzle in a single-sector combustor to control emissions. The test results show that the combustor enables an 82% reduction in NOx emissions relative to the ICAO CAEP/4 standard and a drastic reduction in smoke and CO emissions.

Effects of Air Jets Through Combustor Liner Holes on Emissions of Lean Staged Combustor

2014 ◽  
Author(s):  
Takeshi Yamamoto ◽  
Kazuo Shimodaira ◽  
Yoji Kurosawa ◽  
Naoki Nakamura
Keyword(s):  
Pressure Ratio ◽  
Nox Reduction ◽  
Combustion Efficiency ◽  
Long Distance ◽  
Simulation Code ◽  
Eddy Simulation ◽  
Air Jets ◽  
Fuel Nozzle ◽  
Combustion Tests ◽  
Combustor Liner

In JAXA, combustion technologies have been developed with a target that is an 80% NOx reduction of the CAEP/4 standard. A lean staged fuel nozzle with a pilot mixer and a main one in a coaxial arrangement has been developed by single-sector combustor tests under LTO cycle conditions of the target engine with a total pressure ratio of 25.8. In this study, effects of air jets through combustion liner holes on combustion characteristics was investigated. Combustion tests were conducted by using four single-sector combustor liners with different air holes, no air holes, six air holes with short distance from the fuel nozzle, six air holes with long distance from the fuel nozzle, and one air flow path with three swirlers. From these results, air jets affect NOx emissions and combustion efficiency. Numerical analyses are also conducted by using a commercial large eddy simulation code, Front Flow Red. Quench of high temperature of pilot burned gas and NOx generation by air jets are captured by numerical simulations.

Combustion Characteristics of Fuel Staged Combustor for Aeroengines at LTO Cycle Conditions

2011 ◽  
Author(s):  
Takeshi Yamamoto ◽  
Kazuo Shimodaira ◽  
Yoji Kurosawa ◽  
Seiji Yoshida
Keyword(s):  
Pressure Ratio ◽  
Nox Reduction ◽  
Combustion Characteristics ◽  
Nox Emissions ◽  
Staged Combustion ◽  
Drastic Reduction ◽  
Fuel Nozzle ◽  
Reduction Of Nox

In JAXA, combustion technologies have been developed with an aggressive target that is an 80% NOx reduction of CAEP/4. For the drastic reduction of NOx emissions, a fuel nozzle was designed based on the lean staged combustion concept. This paper describes single-sector combustor tests of a fuel staged combustor at ICAO LTO cycle conditions of an assumed engine with rated output of 40 kN and overall pressure ratio of 25.8. The results showed that the combustor enables a 77% reduction of the NOx standard of CAEP/4.

Investigations of a Staged Fuel Nozzle for Aeroengines by Multi-Sector Combustor Test

2010 ◽  
Author(s):  
Takeshi Yamamoto ◽  
Kazuo Shimodaira ◽  
Yoji Kurosawa ◽  
Seiji Yoshida ◽  
Kazuaki Matsuura
Keyword(s):  
Nox Reduction ◽  
Combustion Efficiency ◽  
Nox Emissions ◽  
Fuel Injectors ◽  
Middle Power ◽  
Fuel Staging ◽  
Annular Combustor ◽  
Fuel Nozzle ◽  
Reduction Of Nox ◽  
Conducting Research

The reduction of NOx emissions from aeroengines is very important to protect the local air quality near the airports and prevent the climate change. ICAO CAEP has been stepped up the NOx standard frequently. Therefore, the engine manufacturers and national research institutes are actively working on the low-NOx technologies to meet the lower NOx emissions standard. JAXA is conducting research and development of the aeroengine technologies for the environmental adaptation in the TechCLEAN project. As a part of the project, combustion technologies have been developed with an aggressive target that is an 80% NOx reduction of CAEP/4. For the drastic reduction of NOx emissions, the fuel nozzles were designed based on the lean staged combustion concept. At first, five fuel nozzles were tested in a single-sector combustor at LTO cycle conditions of small aeroengine and it was confirmed that one fuel nozzle enabled 72% NOx reduction of CAEP/4. This lean low NOx fuel nozzle was tested in the present work in a multi-sector combustor at the same conditions with the single-sector combustor test. Test results showed that the combustor had combustion characteristics enabling 70% NOx reduction of CAEP/4, which was almost same with the single-sector combustor. For the improvement of combustion efficiency at middle power conditions, fuel staging among the main fuel injectors was also investigated at the MCL condition. The results showed that the fuel staging among the main fuel nozzles is effective to improve the combustion efficiency of the annular combustor.

Detailed Research on Rich-Lean Type Single Sector Combustor for Small Aircraft Engine Tested Under Practical Conditions Up to 3MPa

2012 ◽  
Author(s):  
Mitsumasa Makida ◽  
Hideshi Yamada ◽  
Kazuo Shimodaira
Keyword(s):  
Experimental Research ◽  
Aircraft Engine ◽  
Emission Characteristics ◽  
Nox Emissions ◽  
Additional Test ◽  
Lean Combustion ◽  
Test Conditions ◽  
The Rich ◽  
Combustion Tests ◽  
Small Aircraft

In the TechCLEAN project of JAXA, experimental research has been conducted to develop a combustor for a small aircraft engine. The combustor was tuned to show the behavior of the Rich-Lean combustion through tests under atmospheric and practical conditions. Finally, through full annular combustion experiments under practical conditions, the combustor was tuned to reduce NOx emissions to almost 40% of the ICAO CAEP4 standard, also sustaining low CO and THC emissions. To investigate the performance of the combustor in detail, parametric experiments were conducted with single-sector combustors under additional test conditions in addition to design conditions of the target engine. Also the performance as a combustor for higher-efficient aircraft engine is examined by increasing inlet air pressure and temperature up to 3MPa and 825K in combustion tests. Obtained results of emission characteristics are discussed in this report.

Suppression of NOx Emission of a Lean Staged Combustor for an Aircraft Engine

2011 ◽  
Author(s):  
H. Fujiwara ◽  
K. Matsuura ◽  
K. Shimodaira ◽  
S. Hayashi ◽  
M. Kobayashi ◽  
...  
Keyword(s):  
High Pressure ◽  
Fuel Injection ◽  
Laser Diagnostics ◽  
Pressure Ratio ◽  
Aircraft Engine ◽  
Elevated Pressure ◽  
Nox Emission ◽  
Fuel Spray ◽  
Nox Emissions ◽  
Joint Research

Due to the increasing demands for environment protection, the regulation of NOx emissions from aircraft engines specified by ICAO have become more stringent year by year. A combustor with lean staged fuel injectors is one of the effective methods to reduce NOx emissions. Kawasaki heavy industries Ltd GTBC and Japan Aerospace Exploration Agency (JAXA) have been conducting joint research on a lean staged concentric fuel nozzle for a high pressure ratio aero engine. High pressure combustion tests were performed to clarify the effect of the contour of the air flow passage of the main premix duct, the arrangement of the swilers and the fuel injection position on the NOx emission especially at high power. Visualization of the fuel spray at elevated pressure inside of the premix duct using a model with transparent walls and a laser diagnostics technique showed clear relationship between the distribution of the fuel spray and the NOx emission.

The Performance of the Low NOx Aero Gas Turbine Combustor Under High Pressure

2001 ◽  
Author(s):  
Takashi Ikezaki ◽  
Jun Hosoi ◽  
Hidemi Toh ◽  
Toshiro Fujimori ◽  
Motohide Murayama ◽  
...  
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Nox Reduction ◽  
Gas Turbine Combustor ◽  
High Pressure And Temperature ◽  
Auto Ignition ◽  
Annular Combustor ◽  
Fuel Nozzle ◽  
Combustion Tests ◽  
Emission Index

We have developed a new fuel staged combustor, which consists of diffusion flame pilot burners and lean premixing prevaporizing main burners and is therefore called a multiple fuel nozzle type low NOx gas turbine combustor. The goal for NOx reductions was set to 70 to 80% compared with conventional gas turbine combustors. Combustion tests for a section of the annular combustor have been performed for pressures P3 up to 2.9Mpa and temperatures T3 up to 823K with kerosene. As the results, even under high pressure and temperature condition, stable combustion without the problem of auto-ignition or flashback could be achieved. NOx emission index is 13 [g/kg,fuel] which is equivalent to more than 70% NOx reduction. The liner wall temperature is lower than the durability limit. The dependency of NOx emissions on pressure and temperature for this combustor are reported.

Verification of Low NOx Performance of Simple Primary Rich Combustion Approach by a Newly Established Full Annular Combustor Test Facility

2008 ◽  
Author(s):  
Mitsumasa Makida ◽  
Hideshi Yamada ◽  
Kazuo Shimodaira ◽  
Seiji Yoshida ◽  
Yoji Kurosawa ◽  
...  
Keyword(s):  
Pressure Ratio ◽  
Aircraft Engine ◽  
Test Facility ◽  
Nox Emissions ◽  
Temperature Profiles ◽  
Experimental Facility ◽  
Lean Combustion ◽  
Annular Combustor ◽  
Exit Temperature ◽  
The Rich

In the TechCLEAN project of JAXA, experimental research has been being conducted to develop a combustor for a small aircraft engine (with pressure ratio of about 20). The combustor was tuned to show the behavior of the Rich-Lean combustion through tests under atmospheric and practical conditions. And in 2006, by a designed multi-sector combustor, NOx emissions were reduced to lower than 42% of the ICAO CAEP4 standard. Based on the tuned combustor, full annular combustors were designed. In parallel, an experimental facility to test the full annular combustors under practical conditions was newly constructed in the spring of 2007. The inlet air conditions were set to the ICAO LTO cycle conditions of the target engine; 0.3–1.8MPa for pressure, 400–700K for temperature and 4–18kg/s for air mass flow rate. Through the full annular combustion experiments under practical conditions, the combustors were tuned to keep good combustion performance which was verified by the multi-sector combustors. The optimized full annular combustor finally achieved the following performance; NOx emissions were reduced to lower than 40% of the ICAO CAEP4 standard, maintaining low CO and THC emissions, good exit temperature profiles (P.T.F. = 0.19 at the take-off condition) and good lean blow-out performance (AFR>200 at the idle condition). The process of the optimization is discussed in this report.

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