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174 results on '"Shiga, Seiichi"'

15. 低密度ガスによる高温ジェット音響場の再現とエジェクタノズル性能調査への応用

Author

GONZALEZ, Palencia Juan C., ONO, Takahiro, IMAGAWA, Kei, ARAKI, Mikiya, KOJIMA, Takayuki, TAGUCHI, Hideyuki, and SHIGA, Seiichi

Abstract

令和元年度宇宙輸送シンポジウム（2020年1月16日-17日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2019 (January 16-17, 2020. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000147023, レポート番号: STCP-2019-023

Published
2020

19. 矩形エジェクタノズル形状がジェット騒音低減に及ぼす効果

Author

Gonzalez, Palencia Juan C., Fukashiro, Yuki, Masuda, Shoko, Araki, Mikiya, Kojima, Takayuki, Taguchi, Hideyuki, and Shiga, Seiichi

Abstract

平成29年度宇宙輸送シンポジウム（2018年1月18日-19日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2017 (January 18-19, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000210030, レポート番号: STCP-2017-030

Published
2018

20. 超音速ジェットにおける大規模乱流構造騒音放射機構の調査

Author

Gonzalez, Palencia Juan C., Kuwazoe, Yuto, Araki, Mikiya, Kojima, Takayuki, Taguchi, Hideyuki, and Shiga, Seiichi

Abstract

平成29年度宇宙輸送シンポジウム（2018年1月18日-19日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2017 (January 18-19, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000210031, レポート番号: STCP-2017-031

Published
2018

23. Effects of injection parameters on the amount of wall-wet fuel in a port-fuel-injected spark-ignition engine during cold start.

Author

Araki, Mikiya, Sakairi, Katsuya, Kuribara, Takashi, González Palencia, Juan C, Shiga, Seiichi, Ishima, Tsuneaki, Haibara, Teruaki, and Mitani, Shinichi

Abstract

In a four-stroke cycle port-fuel-injected spark-ignition engine, a significant portion of unburned hydrocarbons is exhausted during the short period of cold start. The aim of this study is to investigate the physics behind the wall-wet phenomena and its determining parameter as simply as possible even though qualitative to some extent. The test engine is driven at a constant speed of 350 r/min. The fuel injection starts at a certain cycle, and the cycles required for the first ignition is counted. Three gasoline injectors having different atomization characteristics are used for port fuel injection, and the droplet size, the spray angle and the spray velocity are varied independently. The fuel transport phenomena from the injector to the cylinder are characterized by only two parameters, α and β, the mass fraction of the fuel without wall-wet and the mass fraction of the evaporated fuel from liquid films on walls. They are determined so that all the first ignition cycles observed experimentally are consistently reproduced by the model. The value of α is successfully determined for every single injector, and it increases monotonously with the decrease in the Stokes number. [ABSTRACT FROM AUTHOR]

Published
2021
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24. 矩形エジェクタノズルが超音速噴流の騒音放射特性に及ぼす影響

Author

Masuda, Shoko, Ide, Katsunobu, Araki, Mikiya, Kojima, Takayuki, Taguchi, Hideyuki, Gonzalez-Palencia, Juan-Carlos, and Shiga, Seiichi

Abstract

平成28年度宇宙輸送シンポジウム（2017年1月19日-20日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2016 (January 19-20, 2017. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000086030, レポート番号: STCP-2016-030

Published
2017

25. Visualization of Acoustic Wave emission in a Rectangular Supersonic Jet

Author

Kunishi, Kengo, Kuwazoe, Yuto, Araki, Mikiya, Kojima, Takayuki, Taguchi, Hideyuki, Gonzalez-Palencia, Juan-Carlos, and Shiga, Seiichi

Abstract

平成28年度宇宙輸送シンポジウム（2017年1月19日-20日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2016 (January 19-20, 2017. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000086031, レポート番号: STCP-2016-031

Published
2017

28. 超音速ジェット騒音の音源位置と周波数特性

Author

Araki, Mikiya, Kojima, Takayuki, Taguchi, Hideyuki, Gonzalez, Palencia Juan C., and Shiga, Seiichi

Abstract

平成27年度宇宙輸送シンポジウム（2016年1月14日-15日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2015 (January 14-15, 2016. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000050043, レポート番号: STCP-2015-044

Published
2016

29. 矩形エジェクタノズルから噴出する超音速噴流の騒音放射特性

Author

Araki, Mikiya, Kojima, Takayuki, Taguchi, Hideyuki, Gonzalez, Palencia Juan C., and Shiga, Seiichi

Abstract

平成27年度宇宙輸送シンポジウム（2016年1月14日-15日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2015 (January 14-15, 2016. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000050045, レポート番号: STCP-2015-046

Published
2016

36. 矩形プラグノズルの排気騒音低減

Author

Sano, Takayuki, Araki, Mikiya, Sone, Yusuke, Kojima, Takayuki, Taguchi, Hideyuki, Shiga, Seiichi, and Obokata, Tomio

Abstract

平成18年度宇宙輸送シンポジウム（2007年1月18日-19日. 宇宙航空研究開発機構宇宙科学研究本部）, 相模原市, 神奈川県, Space Transportation Symposium FY2006 (January 18-19, 2007. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000005007

Published
2007

38. Takeoff Noise Estimation of a Hypersonic Aircraft Equipped with the Precooled Turbojet Engine

Author

Sano, Norihisa, Tanaka, Kyohei, Kojima, Takayuki, Taguchi, Hideyuki, Gonzalez, Palencia Juan C., Araki, Mikiya, and Shiga, Seiichi

Abstract

平成26年度宇宙輸送シンポジウム（2015年1月15日-16日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2014 (January 15-16, 2015. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000036023, レポート番号: STCP-2014-023

Published
2015

39. Vegetable Oils as Diesel Fuel Alternatives

Author

Shiga Seiichi and H.T.C. Machacon

Subjects
Spray characteristics, Engineering, Biodiesel, Waste management, business.industry, Winter diesel fuel, Renewable fuels, Combustion, Diesel fuel, chemistry.chemical_compound, chemistry, Biofuel, Petroleum, business
Abstract

Biomass fuels or Biodiesel fuels are a viable alternative to petroleum fuels due to their renewability, low or no emission and the potential to provide energy security and local economic benefits. This paper presents the results of various oils being tested as diesel fuel alternatives, including coconut oil unblended and blended with diesel fuel. The effects on engine performance and efficiency, the corresponding problems associated with their use, the atomization characteristics in the process of spray formation, engine combustion and the mechanism of the effect is also discussed on the basis of emissions, combustion parameters and spray characteristics.

Published
2005

40. スリット噴射位置が矩形極超音速ノズルから噴出する排気騒音に及ぼす影響

Author

Tajima, Keisuke, Muraki, Mizuho, Araki, Mikiya, Kojima, Takayuki, Taguchi, Hideyuki, Shiga, Seiichi, and Gonzalez, Juan

Abstract

平成25年度宇宙輸送シンポジウム（2014年1月16日-17日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2013 (January 16-17, 2014. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000016040, レポート番号: STCP-2013-040

Published
2014

41. 矩形極超音速ノズルから噴出する高温ジェットの音響シミュレーション

Author

Tanaka, Kyohei, Ijuin, Yasuhiro, Nishida, Shunsuke, Imamura, Osamu, Araki, Mikiya, Kojima, Takayuki, Taguchi, Hideyuki, and Shiga, Seiichi

Abstract

平成25年度宇宙輸送シンポジウム（2014年1月16日-17日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2013 (January 16-17, 2014. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000016039, レポート番号: STCP-2013-039

Published
2014

42. Interaction Effects on Combustion of Alcohol Droplet Pairs

Author

OKAI, Keiichi, ONO, Yutaka, MORIUE, Osamu, SHIBA, Seiji, ARAKI, Mikiya, NOMURA, Hiroshi, SHIGA, Seiichi, TSUE, Mitsuhiro, and KONO, Michikata

Subjects
Physics::Fluid Dynamics, endocrine system, Liquid Fuel, Interaction Effects, technology, industry, and agriculture, Physics::Atomic and Molecular Clusters, Combustion, Physics::Chemical Physics, complex mixtures, Disruptive Combustion, eye diseases, Astrophysics::Galaxy Astrophysics, High Pressure Combustion
Abstract

Experimental investigation was conducted on two droplet-array combustion of methanol and methanol/dodecanol mixture fuels in microgravity. For methanol, effects of ambient pressure and droplet spacing were examined. Results show that the droplet lifetime decreases with increasing spacing at relatively low pressure and the droplet lifetime becomes independent of spacing at higher-subcritical and supercritical pressures. For methanol/dodecanol mixture, effects of pressure, fuel composition were investigated in terms of occurrence of disruption. Disruption of droplet during combustion was demonstrated both for single droplet and droplet pairs.

Published
2001

43. Scale effect of jet noise emitted from a rectangular plug nozzle

Author

Sano, Takayuki, Fukuda, Masayuki, Araki, Mikiya, Kojima, Takayuki, Taguchi, Hideyuki, Nishida, Shunsuke, Imamura, Osamu, Shiga, Seiichi, and Tsue, Mitsuhiro

Abstract

平成20年度宇宙輸送シンポジウム(2009年1月19日-20日, 宇宙航空研究開発機構宇宙科学研究本部), 形態: カラー図版あり, 資料番号: AA0064292061

Published
2009

45. Investigation of Supersonic Jet Noise Sources Using the Optical CT Method and a Microphone Array

Author

Takahashi, Yasuhiro, Morita, Kohei, Araki, Mikiya, Kojima, Takayuki, Taguchi, Hideyuki, and Shiga, Seiichi

Abstract

平成24年度宇宙輸送シンポジウム (2013年1月17日-1月18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県, Space Transportation FY2012 (January 17-18, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, By use of schlieren optics and microphones, jet noise sources of a rectangular hypersonic nozzle are investigated experimentally. Tomographic reconstruction of density fluctuation distribution of the jet and the cross-correlation analysis between the schlieren optics and the microphones are carried out. Maximum cross-correlation distributions show that the sound wave is highly directional within the downstream cone angle. In order to discuss the intensity of noise sources, the amplitude of the light intensity fluctuation and the maximum cross-correlations are multiplied at each measured point, which indicate the contribution of local noise sources to each microphone. The accuracy of the optical CT method is verified using a microphone array., 形態: カラー図版あり, 形態: PDF, Physical characteristics: Original contains color illustrations, Physical characteristics: PDF, 資料番号: AA0061856025, レポート番号: STCP-2012-025

Published
2013

46. Effect of Nozzle Configuration on Takeoff Noise of a Hypersonic Transport

Author

Gonzalez, Palencia Juan C., Sano, Norihisa, Tanaka, Kyohei, Araki, Mikiya, Kojima, Takayuki, Taguchi, Hideyuki, and Shiga, Seiichi

Subjects
Nozzle Configuration, Hypersonic Transport, Effective Perceived Noise Level, Takeoff Noise
Abstract

Effect of nozzle configuration on the takeoff noise of a hypersonic transport is investigated based on small-scale nozzle experiments. In the Japan Aerospace Exploration Agency, the precooled turbojet (PCTJ) engine aimed at the hypersonic flight is under development. The takeoff noise of the full-scale vehicle is assessed before it is put into the operation using an acoustic simulation method. By matching the jet velocity and jet Mach number with the realistic PCTJ engine condition, the acoustic characteristics of the hypersonic nozzle are duplicated with a small-scale nozzle model. The jet noise database around the hypersonic nozzle is established through a number of experiments, and by taking into account 1) the nozzle scale, 2) the number of nozzles, 3) the direction of installation, 4) the measurement distance and angle based on the flight trajectory, and 5) the atmospheric absorption, the effective perceived noise level (EPNL) at the flyover point is calculated. It is shown that the nozzle configuration has a large impact on the takeoff noise, and that such an assessment could contribute to the improvement of the integration design of the vehicle., 形態: 図版あり, Physical characteristics: Original contains illustrations, 資料番号: DS1540529005

Published
2016

47. Thrust Measurement of a Rectangular Hypersonic Nozzle by an Inclined Baffle Plate

Author

Tsukamoto, Masahiro, Ijuin, Yasuhiro, Morita, Kohei, Araki, Mikiya, Kojima, Takayuki, Taguchi, Hideyuki, and Shiga, Seiichi

Abstract

平成23年度宇宙輸送シンポジウム（2012年1月19日-20日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)（ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2011 (January 19-20, 2012. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000003062, レポート番号: STCP-2011-062

Published
2012

48. Effects of Equivalence Ratio of Afterburner and Temperature Distribution on Jet Noise from Rectangular Plug Nozzle

Author

Ijuin, Yasuhiro, Tsukamoto, Masahiro, Morita, Kohei, Araki, Mikiya, Kojima, Takayuki, Taguchi, Hideyuki, Nishida, Shunsuke, Imamura, Osamu, Shiga, Seiichi, and Tsue, Mitsuhiro

Abstract

平成22年度宇宙輸送シンポジウム(2011年1月20-21日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, Space Transportation FY2010 (January 20-21, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan, Jet noise characteristics radiated from a rectangular plug nozzle of a pre-cooled turbojet engine are investigated, experimentally. In the present study, the nozzle scale (1.0 %, 2.4 %), total temperature (T(sub t) = 290 K-1720 K), afterburner (AB on or AB off), and hydrogen equivalence ratio (phi = 0.14 - 4.20) are varied. Temperature measurement was carried out using temperature measurement section. By use of A(U(sub j ))(exp n) law, normalized jet noise spectra are obtained. Normalized jet noise spectra with afterburner are lower than that for without afterburner. Combustion afterburner. Combustion afterburner. Combustion which takes place out of nozzle are dominant in a hydrogen rich burn afterburner. It is supposed that diffusion combustion of such an afterburner is dominant, and that the velocity index n=4 is more suitable, which corresponds to "monopole" sound source., 形態: カラー図版あり, 形態: CD-ROM1枚, Physical characteristics: Original contains color illustrations, Note: One CD-ROM, 資料番号: AA0065073008

Published
2011

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