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.

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.

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.

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.

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.

Investigation on Material Selection in Missan Oilfields Similar Environment

2014 ◽  
Vol 641-642 ◽  
pp. 427-433
Author(s):  
Shuang Cheng ◽  
Feng Lin ◽  
Pei Long Yang ◽  
Pei Ke Zhu ◽  
Jin Gen Deng ◽  
...  
Keyword(s):  
Stainless Steel ◽  
Carbon Steel ◽  
Nickel Alloy ◽  
Martensitic Stainless Steel ◽  
Material Selection ◽  
Pressure Ratio ◽  
Service Condition ◽  
Corrosion Mechanism ◽  
Test Results ◽  
Chrome Steel

This paper analyzed the corrosion environment of Missan oilfields and investigated the oilfield country tubular goods used in other similar oilfields. Summarized the effect of partial pressure ratio of H2S/CO2 and Cl-to the corrosion behavior of OCTG. This paper concluded the service condition, test results and anti-corrosion mechanism of carbon steel, low-chrome steel, modified martensitic stainless steel and nickel alloy. Finally arrived at conclusion that the nickel alloy can meet the requirement of Missan oilfields, some literature reported that the modified martensitic stainless steel can apply in H2S/CO2 environment. In the condition that be easy to replace the tubular, carbon steel and low-chrome steel tubular can meet the requirement with corrosion inhibitor.

scholarly journals MS7001F Prototype Test Results

1989 ◽  
Author(s):  
D. E. Brandt
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Load Test ◽  
Test Results ◽  
Critical Temperatures ◽  
Prototype Test ◽  
Surge Margin ◽  
Pertinent Data ◽  
Post Test ◽  
Heavy Duty Gas Turbine

The MS7001F heavy–duty gas turbine has been designed utilizing advanced analytical methods and a substantial array of component tests. The integrity of the system required that the prototype unit, with its accessories, be rigorously tested under load. The factory load test was completed on May 18, 1988 after 387 hours and 134 start/stop cycles. The MS7001F prototype gas turbine was instrumented with more than 3000 pieces of instrumentation in order to record all critical temperatures, pressures, flows, strains, displacements, and other pertinent data. The load device was a modified MS7001E compressor, which also supplied the means by which the MS7001F prototype compressor’s pressure ratio was increased to provide for surge margin determination. Inlet throttling of the MS7001F compressor allowed for full firing temperature operation, at reduced load. The results of this factory prototype load test are reported in the paper as are observations made during post test teardown.

An Investigation of Flow Characteristics and Parameter Effects for a New Concept of Hybrid SVC Nozzle

2018 ◽  
Author(s):  
F. Song ◽  
J. W. Shi ◽  
L. Zhou ◽  
Z. X. Wang ◽  
X. B. Zhang
Keyword(s):  
Static Pressure ◽  
Pressure Ratio ◽  
Flow Characteristics ◽  
Exhaust System ◽  
Aircraft Engine ◽  
Thrust Coefficient ◽  
Thrust Vectoring ◽  
Static Pressure Distribution ◽  
Thrust Vector ◽  
Vector Angle

Lighter weight, simpler structure, higher vectoring efficiency and faster vector response are recent trends in development of aircraft engine exhaust system. To meet these new challenges, a concept of hybrid SVC nozzle was proposed in this work to achieve thrust vectoring by adopting a rotatable valve and by introducing a secondary flow injection. In this paper, we numerically investigated the flow mechanism of the hybrid SVC nozzle. Nozzle performance (e.g. the thrust vector angle and the thrust coefficient) was studied with consideration of the influence of aerodynamic and geometric parameters, such as the nozzle pressure ratio (NPR), the secondary pressure ratio (SPR) and the deflection angle of the rotatable valve (θ). The numerical results indicate that the introductions of the rotatable valve and the secondary injection induce an asymmetrically distributed static pressure to nozzle internal walls. Such static pressure distribution generates a side force on the primary flow, thereby achieving thrust vectoring. Both the thrust vector angle and vectoring efficiency can be enhanced by reducing NPR or by increasing θ. A maximum vector angle of 16.7 ° is attained while NPR is 3 and the corresponding vectoring efficiency is 6.33 °/%. The vector angle first increases and then decreases along with the elevation of SPR, and there exists an optimum value of SPR for maximum thrust vector angle. The effects of θ and SPR on the thrust coefficient were found to be insignificant. The rotatable valve can be utilized to improve vectoring efficiency and to control the vector angle as expected.

scholarly journals ANALISA KUALITAS AIR LIMBAH TAHU DI KECAMATAN NANGGALO KOTA PADANG

2020 ◽  
Vol 5 (1) ◽  
pp. 74
Author(s):  
Ariyetti Ariyetti ◽  
Malse Anggia ◽  
Ruri Wijayanti
Keyword(s):  
Quality Standard ◽  
Disposal Site ◽  
Test Results ◽  
Sampling Points ◽  
Wastewater Quality ◽  
Community Residence ◽  
Conducting Research ◽  
Wastewater Samples ◽  
Parameter Values ◽  
Industry Wastewater

<p>Air limbah industri tahu berpotensi mencemari lingkungan, maka sebelumnya perlu dilakukan pengolahan sebelum dibuang ke lingkungan. Dimana salah satu upaya awal untuk menangani hal tersebut dengan melakukan penelitian. Penelitian ini bertujuan untuk mengidentifikasi cemaran air limbah industri tahu terutama di Kecamatan Nanggalo Kota Padang. Metoda penelitian dilakukan dengan mengambil sampel air limbah industri tahu pada dua lokasi dan dua titik pengambilan sampel untuk masing-masing lokasi, yaitu didekat tempat pembuangan air limbah dan yang berdekatan dengan tempat tinggal masyarakat. Parameter pengujiannya meliputi : <em>BOD</em>, <em>COD</em>, pH, <em>TSS</em>, N-NH<sub>3</sub>, dan N-Total. Hasil pengujian pada lokasi pertama dan titik pertama, nilai parameter secara berurutan dari BOD, COD, pH, TSS, N-NH<sub>3</sub> dan N-Total adalah 226 mg/L; 387 mg/L; 5,10; 156 mg/L; 2,20 mg/L dan 2,54 mg/L, sedangkan pada titik kedua nilainya 153 mg/L; 287 mg/L; 5,82; 128 mg/L; 1,17 mg/L dan 2,02 mg/L. Kemudian pada lokasi kedua dan titik pertama nilai nya secara berurutan, yaitu 154 mg/L; 282 mg/L; 4,87; 120 mg/L; 2,06 mg/L dan 2,76 mg/L, sedangkan pada titik kedua nilainya 121 mg/L; 234 mg/L; 5,11; 88 mg/L; 1,24 mg/L dan 1,67 mg/L. Hasil yang didapatkan menunjukkan kondisi air limbah tahu dengan parameter pH pada semua lokasi dan titik  melewati batas baku mutu yang diizinkan menurut Permen Lingkungan Hidup No.5 Tahun 2014 tentang Baku Mutu Air Limbah Bagi Usaha dan/atau Kegiatan Pengolahan Kedelai.</p><p> </p><p>Tofu industry wastewater has the potential to pollute the environment, so it needs to be trated before it is discharged into the environment. Where is one of the initial efforts to deal with this by conducting research. This study aims to identify tofu industry wastewater contamination, especially in Nanggalo District, Padang City. The research method is carried out by taking tofu industrial wastewater samples at two locations and two sampling points for each location and two sampling points for each location, which are near the waste water disposal site and which is adjacent to the community residence. The testing parameters include : BOD, COD, pH, TSS, N-NH<sub>3</sub> and N-Total. The test results at the first location and first point, the parameter values in arrow of BOD, COD, pH, TSS, NH<sub>3</sub> and N-Total are 226 mg/L; 387 mg/L; 5,10; 156 mg/L; 2,20 mg/L and 2,54 mg/L, while at the second point the value is 153 mg/L; 287 mg/L; 5,82; 128 mg/L; 1,17 mg/L and 2,02 mg/L. Then  at the second location and the first point the values are in sequence, which is 154 mg/L; 282 mg/L; 4,87; 120 mg/L; 2,06 mg/L and 2,76 mg/L, while at the second point the value is 121 mg/L; 234 mg/L; 5,11; 88 mg/L; 1,24 mg/L and 1,67 mg/L. The results obtained indicate the condition of tofu wastewater with pH parameters at all location and the point of exceeding the permitted quality standard according to Environmental Regulation No.5 of 2014 concerning Wastewater Quality Standars for Soybean Business and / or Processing Activities.</p>

scholarly journals Impact of a Structure on Durability of Modified Nickel-Base Superalloys in Creep Conditions/ Wpływ Struktury Na Trwałość W Warunkach Pełzania Modyfikowanych Nadstopów Na Bazie Niklu

2014 ◽  
Vol 59 (4) ◽  
pp. 1559-1563 ◽  
Author(s):  
M. Ciesla ◽  
M. Manka ◽  
P. Gradon ◽  
F. Binczyk
Keyword(s):  
Creep Resistance ◽  
Morphological Structure ◽  
Aircraft Engine ◽  
Coarse Grained ◽  
Test Results ◽  
Cast State ◽  
Accelerated Creep ◽  
Nickel Base ◽  
The Impact ◽  
Modification Treatment

Abstract The study assesses the impact of surface and bulk modification and filtration during pouring on a durability under accelerated creep conditions of casts made of IN-713C and MAR-247 nickel superalloys scrap used for manufacturing of aircraft engine parts. The impact of solutionizing (1185°C/2 h) with subsequent ageing (870°C/20 h) on the creep resistance of a casting made from MAR-247 coarse-grained superalloy was also examined. Morphological structure parameters were determined with the use of Met-Ilo software. Macrostructure analysis of casts showed very significant impact of surface modification treatment. Creep test results clearly showed that coarse grained samples of IN-713C and MAR-247 superalloys have higher creep resistance. Moreover alloy MAR-247 had higher creep durability after heat treatment compared to as-cast state.

Experimental Test Results for Four High-Speed, High-Pressure, Orifice-Compensated Hybrid Bearings

1994 ◽  
Vol 116 (1) ◽  
pp. 147-153 ◽  
Author(s):  
N. M. Franchek ◽  
D. W. Childs
Keyword(s):  
High Speed ◽  
Load Capacity ◽  
Pressure Ratio ◽  
Reynolds Numbers ◽  
Orifice Diameter ◽  
Test Results ◽  
Rotordynamic Coefficients ◽  
Geometric Configurations ◽  
Overall Performance ◽  
Mass Terms

In this study, four hybrid bearings having different geometric configurations were experimentally tested for their static and dynamic characteristics, including flowrate, load capacity, rotordynamic coefficients, and whirl frequency ratio. The four bearings included a square-recess, smooth-land, radial-orifice bearing (baseline), a circular-recess bearing, a triangular-recess bearing, and an angled-orifice bearing. Each bearing had the same orifice diameter rather than the same pressure ratio. Unique to these test results is the measurement of the added mass terms, which became significant in the present tests because of high operating Reynolds numbers. Comparisons of the results were made between bearings to determine which bearing had the best performance. Based on the parameters of interest, the angled-orifice bearing has the most favorable overall performance.

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