九州大学 研究者情報
論文一覧
古川 雅人(ふるかわ まさと) データ更新日:2018.06.28

教授 /  工学研究院 機械工学部門 流体工学講座


原著論文
1. Sasuga Itou, Nobuhito Oka, Masato Furukawa, Kazutoyo Yamada, Seiichi Ibaraki, Kenichiro Iwakiri, Yoshihiro Hayashi, Optimum Aerodynamic Design of Centrifugal Compressor using a Genetic Algorithm and an Inverse Method based on Meridional Viscous Flow Analysis, Proceedings of the 17th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery 2017, 2017.12.
2. Seisiro Saito, Masato Furukawa, Kazutoyo Yamada, Yuki Tamura, Akinori Matsuoka, Naoyuki Niwa, Effects of Blade Tip Clearance on Hub-Corner Separation in a Stator Cascade of a Multi-Stage Transonic Axial Compressor, Proceedings of the Ninth JSME-KSME Thermal and Fluids Engineering Conference, Paper No. TFEC9-1582, 2017.10.
3. Taku Iwase, Tetsushi Kishitani, Masato Furukawa, Study on influence of blade number on aerodynamic noise of half-ducted propeller fans for packaged air-conditioners, International Journal of Fluid Machinery and Systems, 10.5293/IJFMS.2017.10.4.318, 10, 4, 318-327, 2017.10, [URL], Flow fields in 2-blade and 4-blade half-ducted propeller fans for the outdoor units of air-conditioners were calculated with large eddy simulation based on finite element method with the aim of investigating the influence of blade number on aerodynamic noise. We confirmed that the tip vortex had a great influence on aerodynamic noise in half-ducted propeller fans. The length of the tip vortex trajectory and the blade pitch for the 2-blade propeller fan were longer than those for the 4-blade propeller fan. These were suppressed the interaction between the tip vortex and the adjacent blade in the 2-blade propeller fan. The 2-blade propeller fan was therefore more silent than the 4-blade propeller fan..
4. Kazutoyo Yamada, Masato Furukawa, Yuki Tamura, Seishiro Saito, Akinori Matsuoka, Kentaro Nakayama, Large-scale detached-eddy simulation analysis of stall inception process in a multistage axial flow compressor, Transactions of the ASME, Journal of Turbomachinery, 10.1115/1.4035519, 139, 7, 071002-1-071002-11, 2017.07, [URL], This paper describes the flow mechanisms of rotating stall inception in a multistage axial flow compressor of an actual gas turbine. Large-scale numerical simulations of the unsteady have been conducted. The compressor investigated is a test rig compressor that was used in the development of the Kawasaki L30A industrial gas turbine. While the compressor consists of a total of 14 stages, only the front stages of the compressor were analyzed in the present study. The test data show that the fifth or sixth stages of the machine are most likely the ones leading to stall. To model the precise flow physics leading to stall inception, the flow was modeled using a very dense computational mesh, with several million cells in each passage. A total of 2×109 cells were used for the first seven stages (3×108 cells in each stage). Since the mesh was still not fine enough for large-eddy simulation (LES), a detached-eddy simulation (DES) was used. Using DES, a flow field is calculated using LES except in the near-wall where the turbulent eddies are modeled by Reynolds-averaged Navier-Stokes. The computational resources required for such largescale simulations were still quite large, so the computations were conducted on the K computer (RIKEN AICS in Japan). Unsteady flow phenomena at the stall inception were analyzed using data mining techniques such as vortex identification and limiting streamline drawing with line integral convolution (LIC) techniques. In the compressor studied, stall started from a separation on the hub side rather than the commonly observed leading-edge separation near the tip. The flow phenomenon first observed in the stalling process is the hub corner separation, which appears in a passage of the sixth stator when approaching the stall point. This hub corner separation grows with time, and eventually leads to a leading-edge separation on the hub side of the stator. Once the leading-edge separation occurs, it rapidly develops into a rotating stall, causing another leading-edge separation of the neighboring blade. Finally, the rotating stall spreads to the upstream and downstream blade rows due to its large blockage effect..
5. Seishiro Saito, Masato Furukawa, Kazutoyo Yamada, Yuki Tamura, Akinori Matsuoka, Naoyuki Niwa, Vortical flow structure of hub-corner separation in a stator cascade of a multi-stage transonic axial compressor, Proceedings of the ASME 2017 Fluids Engineering Division Summer Meeting, 10.1115/FEDSM2017-69116, 1A-2017, ASME Paper No. FEDSM2017-69116, 2017.07, [URL], In this study, the hub-corner separation in a multi-stage transonic axial compressor has been investigated using a largescale detached eddy simulation (DES) with about 4.5 hundred million computational cells. The complicated flow field near the hub wall in a stator with partial tip clearances was analyzed by data mining techniques extracting important flow phenomena from the DES results. The data mining techniques applied in the present study include vortex identification based on the critical point theory and topological data analysis of the limiting streamline pattern visualized by the line integral convolution (LIC) method. It is found from the time-averaged flow field in the first stator that the hub-corner separation vortex formed near the solid part of the stator tip interacts with the leakage flow and secondary flow on the hub wall, resulting in a complicated vortical flow field. Near the leading edge of the stator, the leakage flow from the front partial clearance generates the tip leakage vortex, which produces loss from the leading edge to 10 percent chord position. At the mid-chord, the hub-corner separation vortex suffers a breakdown, resulting in the widespread huge loss production. It is shown from limiting streamlines on the suction surface of the stator that a reverse flow region expands radially from the solid part of the stator tip toward the downstream. From 50 percent chord position to the trailing edge of the stator, the leakage flow through the rear partial clearance interacts with the secondary flow on the hub wall. The leakage vortex generated along the rear partial clearance becomes a major loss factor there..
6. Nobuhito Oka, Masato Furukawa, Kazutoyo Yamada, Sasuga Itou, Seiichi Ibaraki, Kenichiro Iwakiri, Yoshihiro Hayashi, Optimum aerodynamic design of centrifugal compressor impeller using an inverse method based on meridional viscous flow analysis, Proceedings of the ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, 10.1115/GT2017-63539, 2C-2017, ASME Paper No. GT2017-63539, 2017.06, [URL], An optimum aerodynamic design method for centrifugal compressor impeller has been developed. The present optimum design method is using a genetic algorithm (GA) and a two-dimensional inverse blade design method based on a meridional viscous flow analysis. In the meridional viscous flow analysis, an axisymmetric viscous flow is numerically analyzed on a two-dimensional meridional grid to determine the flow distribution around the impeller. Full and splitter blade effects to the flow field are successfully evaluated in the meridional viscous flow analysis by a blade force modeling. In the inverse blade design procedure, blade loading distribution is given as the design variable. In the optimization procedure, the total pressure rise and adiabatic efficiency obtained from the meridional viscous flow analysis are employed as objective functions. Aerodynamic performance and three-dimensional flow fields in the Pareto-optimum design and conventional design cases have been investigated by three-dimensional Reynolds averaged Navier-Stokes (3D-RANS) and experimental analyses. The analyses results show performance improvements and suppressions of flow separations on the suction surfaces in the optimum design cases. Therefore, the present aerodynamic optimization using the inverse method based on the meridional viscous flow analysis is successfully achieved..
7. Kazutoyo Yamada, Masato Furukawa, Hiromitsu Arai, Dai Kanzaki, Evolution of reverse flow in a transonic centrifugal compressor at near-surge, Proceedings of the ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, 10.1115/GT2017-63568, 2C-2017, ASME Paper No. GT2017-63568, 2017.06, [URL], In process centrifugal compressors used in various types of plants, the compressor is the heart of a plant, and it requires high reliability. Therefore, prediction of the surge is important for centrifugal compressors. There have been numerous researches on the surge: study on improvement of surge margin, and study on the rotating stall, which is recognized as a precursor to surge, in impeller or diffuser of the compressor. However, the researches have not focused on the surge inception flow phenomena, namely detailed flow mechanism leading to the surge, although understanding of such flow phenomena is important for prediction of the surge. The paper describes in detail unsteady flow fields in a transonic centrifugal compressor at near-surge conditions. The flow fields have been investigated by detached eddy simulations (DES) using 400 million grid points. The simulation results show that the huge reverse flow region occupies the flow field near the shroud in the impeller at off-design condition, triggered by the blade stall at the tip of impeller full-blade, and it drastically develops at near-surge. It is also found that the rotating disturbance with reversed flow appears in the diffuser near the endwall at around peak pressure-rise point, and it eventually evolves into the rotating stall cell with a large reverse flow, blocking the flow inside the diffuser at near-surge..
8. Kazutoyo Yamada, Masato Furukawa, Satoshi Nakakido, Yuki Tamura, Akinori Matsuoka, Kentaro Nakayama, A Study on Unsteady Flow Phenomena at Near-Stall in a Multi-Stage Axial Flow Compressor by Large-Scale DES with K Computer, International Journal of Gas Turbine, Propulsion and Power Systems, Vol. 9, No. 1, 18-26, 2017.02.
9. Kazuya Kusano, Kazutoyo Yamada, Masato Furukawa, Kil-Ju Moon, Direct Numerical Simulation of Turbulent Flow and Aeroacoustic Fields around an Airfoil Using Lattice Boltzmann Method, Proceedings of the ASME 2016 Fluids Engineering Summer Meeting, 1-7, ASME Paper No. FEDSM2016-7585, 2016.07.
10. Kazutoyo Yamada, Masato Furukawa, Yuki Tamura, Seishiro Saito, Akinori Matsuoka, Kentaro Nakayama, Large-Scale DES Analysis of Stall Inception Process in a Multi-Stage Axial Flow Compressor, ASME Turbo Expo 2016, ASME Paper No. GT2016-57104, 2016.06.
11. Nobuhito Oka, Masato Furukawa, Kenta Kawamitsu, Kazutoyo Yamada, Optimum Aerodynamic Design for Wind-Lens Turbine, Journal of Fluid Science and Technology, 10.1299/jfst.2016jfst0011, Vol. 11, No. 2, JFST0011-1-JFST0011-14, 2016.06.
12. Kazutoyo Yamada, Masato Furukawa, Satoshi Nakakido, Yuki Tamura, Akinori Matsuoka, Kentaro Nakayama, A Study on Unsteady Flow Phenomena at Near-Stall in a Multi-Stage Axial Flow Compressor by Large-Scale DES with K Computer, The International Gas Turbine Congress 2015 Tokyo, Paper No. 85, 2015.11.
13. Nobuhito Oka, Masato Furukawa, Kazutoyo Yamada, Yuki Tamura, Shoji Yamada, Takahide Tadokoro, Naohiko Homma, Improvement in Aerodynamic Performance of a Half-Ducted Axial Flow Fan using Meridional Viscous Flow Analysis, The 13th Asian International Conference on Fluid Machinery, Paper No. AICFM13-073, 2015.09.
14. Hideo Mori, Kyohei Maeda, Masato Furukawa, Masao Akiyoshi, Measurement Technique for Unsteady Low-Speed Flow Fields Using Poly (TMSP)-Based Pressure Sensitive Paint, The ASME-JSME-KSME Joint Fluids Engineering Conference 2015, Paper No. AJK2015-20700, 2015.07.
15. Kazutoyo Yamada, Masato Furukawa, Satoshi Nakakido, Akinori Matsuoka, Kentaro Nakayama, Large-Scale DES Analysis of Unsteady Flow Field in a Multi-Stage Axial Flow Compressor at Off-Design Condition Using K Computer, ASME Turbo Expo 2015, ASME Paper No. GT2015-42648, 2015.06.
16. Nobuhito Oka, Masato Furukawa, Kazutoyo Yamada, Akihiro Oka, Yasushi Kurokawa, Aerodynamic Performances and Flow Fields of Pareto Optimal Solutions in an Aerodynamic Design Optimization of a Wind-Lens Turbine, ASME Turbo Expo 2015, ASME Paper No. GT2015-43619, 2015.06.
17. Isao Tomita, Koji Wakashima, Seiichi Ibaraki, Masato Furukawa, Kazutoyo Yamada, Dai Kanzaki, Effects of Flow Height of Impeller Exit and Diffuser on Flow Fields in a Transonic Centrifugal Compressor, ASME Turbo Expo 2015, ASME Paper No. GT2015-43271, 2015.06.
18. 森 英男, 前田恭平, 川幡宏亮, 古川 雅人, 秋吉雅夫, 文 吉周, ポリマー型感圧塗料を用いた低周波数低振幅の非定常圧力変動計測, 日本機械学会論文集, DOI:10.1299/transjsme.15-00058, Vol. 81, No. 826, 2015.06.
19. Kazuya Kusano, Kazutoyo Yamada, Masato Furukawa, Numerical Analysis of Unsteady Three-Dimensional Flow in a Propeller Fan Using Lattice Boltzmann Method, The International Conference on Fan Noise, Technology and Numerical Methods 2015, ASME Paper No. GT2015-43619, 2015.04.
20. Nobuhito Oka, Kota Kido, Kazutoyo Yamada, Masato Furukawa, Aerodynamic Design of Wind-Lens Turbine with Axisymmetric Viscous Flow Calculation using Lattice Boltzmann Method, The 5th Asian Joint Workshop on Thermophysics and Fluid Science, Paper No. JP48, 2014.09.
21. Nobuhito Oka, Masato Furukawa, Kota Kido, Akihoro Oka, Yasushi Kurokawa, Aerodynamic Performance of a Wind-Lens Turbine with Optimized Blade Loading Distribution and Wind-Lens Shape, The Grand Renewable Energy 2014 (GRE2014) International Conference, Paper No. O-Wd-6-1, 2014.07.
22. Nobuhito Oka, Masato Furukawa, Kazutoyo Yamada, Kenta Kawamitsu, Kota Kido, Akihoro Oka, Simultaneous Optimization of Rotor Blade and Wind-Lens for Aerodynamic Design of Wind-Lens Turbine, ASME Turbo Expo 2014, ASME Paper No. GT2014-25770, 2014.06.
23. Kazutoyo Yamada, Masato Furukawa, Takanori Shibata, Satoshi Nakakido, Nobuhito Oka, Suppression of Secondary Flows in an Axial Flow Turbine Rotor with a Novel Blade Design Concept, ASME Turbo Expo 2014, ASME Paper No. GT2014-25630, 2014.06.
24. 草野 和也, 古川 雅人, 山田 和豊, 半開放形プロペラファンにおける翼端渦の三次元構造, 日本機械学会論文集, 10.1299/transjsme.2014fe0024, Vol. 80, No. 810, FE0024, 2014.02.
25. Fujio Akagi, Shota Setoguchi, Youichi Ando, Sumio Yamaguchi, Masato Furukawa, Maximum circulation of vortex ring generated by pulsating jet, Proceedings of the 4th International Conference on Jets, Wakes and Separated Flows, Paper No. ICJWSF2013-1019, 2013.09.
26. Nobuhito Oka, Kenta Kawamitsu, Soichiro Tabata, Masato Furukawa, Kazutoyo Yamada, Kota Kido, Numerical Analysis of Vortical Flow Field around Wind-lens Turbines, Proceedings of the 4th International Conference on Jets, Wakes and Separated Flows, Paper No. ICJWSF2013-1130, 2013.09.
27. Isao Tomita, Seiichi Ibaraki, Masato Furukawa, Kazutoyo Yamada, The Effect of Tip Leakage Vortex for Operating Range Enhancement of Centrifugal Compressor, ASME Journal of Turbomachinery, 10.1115/1.4007894, Vol. 135, No. 3, 051020-1-051020-8, 2013.09.
28. Kazuya Kusano, Kazutoyo Yamada, Masato Furukawa, Toward Direct Numerical Simulation of Aeroacoustic Field around Airfoil Using Multi-Scale Lattice Boltzmann Method, Proceedings of the ASME 2013 Fluids Engineering Summer Meeting, ASME Paper No. FEDSM2013-16526, 2013.07.
29. Nobuhito Oka, Masato Furukawa, Kazutoyo Yamada, Kota Kido, Aerodynamic Design for Wind-lens Turbine Using Optimization Technique , Proceedings of the ASME 2013 Fluids Engineering Summer Meeting, ASME Paper No. FEDSM2013-16569, 2013.07.
30. Kazutoyo Yamada, Hiroaki Kikuta, Masato Furukawa, Satoshi Gunjishima, Yasunori Hara, Effects of Tip Clearance on the Stall Inception Process in an Axial Compressor Rotor, ASME Turbo Expo 2013, ASME Paper No. GT2013-95479, 2013.06.
31. 山田 和豊, 喜久田 啓明, 古川 雅人, 郡司嶋 智, 原 靖典, 軸流圧縮機動翼列における旋回失速初生プロセスに及ぼす翼端すき間流れの影響
, 日本機械学会論文集B編, Vol. 79, No. 801, pp. 900-916, 2013.05.
32. Kazutoyo Yamada, Hiroaki Kikuta, Kenichiro Iwakiri, Masato Furukawa, Satoshi Gunjishima, Explanation for Flow Features of Spike-Type Stall Inception in an Axial Compressor Rotor, ASME Journal of Turbomachinery, 10.1115/1.4007570, Vol. 135, 021023-1-021023-11, 2013.03.
33. Kazutoyo Yamada, Hiroaki Kikuta, Kenichiro Iwakiri, Masato Furukawa, Satoshi Gunjishima, Explanation for Flow Features of Spike-Type Stall Inception in an Axial Compressor Rotor, ASME Turbo Expo 2012, ASME Paper No. GT2012-69186, 2012.06.
34. Isao Tomita, Seiich Ibaraki, Masato Furukawa, Kazutoyo Yamada, The Effect of Tip Leakage Vortex for Operating Range Enhancement of Centrifugal Compressor, ASME Turbo Expo 2012, ASME Paper No. GT2012-68947, 2012.06.
35. Taku IWASE, Tetsushi KISHITANI, Masato Furukawa, Influence of Blade Number on Aerodynamic Noise of Propeller Fans for Outdoor Unit of Air-Conditioner, Proceedings of the International Conference on Fan Noise, Technology and Numerical Methods 2012, 2012.04.
36. Isao TOMITA, Seiichi IBARAKI, Masato FURUKAWA and Kazutoyo YAMADA, Feature of Internal Flow Phenomena of Centrifugal Compressor for Turbocharger with Wide Operating Range, Proceedings of the International Gas Turbine Congress 2011 Osaka, Paper No. IGTC2011-0080, 2011.11.
37. Kazutoyo YAMADA, Hiroaki KIKUTA, Masato FURUKAWA and Satoshi GUNJISHIMA , Effects of Tip Leakage Vortex Breakdown on Unsteady Flow Fields at Near-Stall Condition in a Low-Speed Axial Flow Compressor Rotor with Large Tip Clearance, Proceedings of the International Gas Turbine Congress 2011 Osaka, Paper No. IGTC2011-56
, 2011.11.
38. 岩瀬拓,日沖哲也,加藤義彦,旦野太郎,関口治,古川雅人, 小型軸流ファンにおける前進翼と箱形ケーシングの干渉が翼通過周波数騒音に与える影響, 日本機械学会論文集B編, Vol. 77, No. 780, pp. 1620-1629, 2011.08.
39. Kazuya KUSANO, Jae-ho JEONG, Kazutoyo YAMADA and Masato FURUKAWA, Detached Eddy Simulation of Unsteady Flow Field and Prediction of Aerodynamic Sound in a Half-Ducted Propeller Fan, Proceedings of the ASME-JSME-KSME Joint Fluids Engineering Conference 2011
, Paper No. AJK2011-22048
, 2011.07.
40. Hiroaki KIKUTA, Ken-ichiro IWAKIRI, Masato FURUKAWA, Kazutoyo YAMADA, Satoshi GUNJISHIMA and Goki OKADA, Unsteady and Three-Dimensional Flow Mechanism of Spike-Type Stall Inception in an Axial Flow Compressor Rotor, Proceedings of the ASME-JSME-KSME Joint Fluids Engineering Conference 2011
, Paper No. AJK2011-22079, 2011.07.
41. Fujio AKAGI, Keisuke KAWABATA,Youichi ANDO, Sumio YAMAGUCHI and Masato FURUKAWA, Circulation of Vortex Ring Generated by Pulsating Jet Flow, Proceedings of the ASME-JSME-KSME Joint Fluids Engineering Conference 2011, Paper No. AJK2011-16015, 2011.07.
42. 山田和豊,古川雅人,福島久剛,茨木誠一, スプリッタ付遠心圧縮機インペラの非設計点における剥離渦流れ構造, ターボ機械, Vol. 39, No. 6, pp. 332-339, 2011.06.
43. Yamada, K., Furukawa, M., Fukushima, H., Ibaraki, S. and Tomita, I., The Role of Tip Leakage Vortex Breakdown in Flow Fields and Aerodynamic Characteristics of Transonic Centrifugal Compressor Impellers, ASME Turbo Expo 2011, ASME Paper No. GT2011-46253, 2011.06.
44. 赤木 富士雄, 奥苑 勇生, 安東 洋一, 山口 住夫, 古川 雅人 , 脈動噴流による渦輪の形成過程 , 日本機械学会論文集B編, Vol. 77, No. 775, pp. 546-556, 2011.03.
45. Kazuya KUSANO, Jae-ho JEONG and Masato FURUKAWA, Unsteady Flow Phenomena Dominating Aerodynamic Noise in a Half Ducted Propeller Fan, Proceedings of the 7th International Conference on Flow Dynamics, pp. 316-317, 2010.11.
46. Soichiro TABATA, Masato FURUKAWA, Sinpei KOJIMA and Nobuhito OKA, Aerodynamic Blade Design for Wind-Lens Turbine, Proceedings of the 7th International Conference on Flow Dynamics, pp.314-315, 2010.11.
47. Kazutoyo YAMADA, Yusuke TAMAGAWA, Hisataka FUKUSHIMA, Masato FURUKAWA, Seiichi IBARAKI and Kenichiro IWAKIRI, Comparative Study on Tip Clearance Flow Fields in Two Types of Transonic Centrifugal Compressor Impeller with Splitter Blades, ASME TURBO EXPO 2010, ASME Paper No. GT2010-23345, 2010.06.
48. Hidenobu OKAMOTO, Akira GOTO and Masato FURUKAWA, Design of a Propeller Fan Using 3-D Inverse Design Method and CFD for High Efficiency and Low Aerodynamic Noise, Proceedings of the ASME 2009 Fluids Engineering Division Summer Meeting, ASME Paper No. FEDSM2009-78454, 2009.08.
49. Ken-ichiro IWAKIRI, Masato FURUKAWA, Seiichi IBARAKI and Isao TOMITA, Unsteady and Three-Dimensional Flow Phenomena in a Transonic Centrifugal Compressor Impeller at Rotating Stall, ASME TURBO EXPO 2009, ASME Paper No. GT2009-59516, 2009.06.
50. Jae-ho JEONG, Soichiro TABATA, Satoshi GUNJISHIMA, Masato FURUKAWA and Tsuyoshi EGUCHI, Analysis of Unsteady Flow Phenomena Related to Aero-Acoustic Noise in an Air Conditioning System, Proceedings of the 7th JSME-KSME Thermal and Fluids Engineering Conference, Paper No. L221, 2008.10.
51. Soichiro TABATA and Masato FURUKAWA, Three-Dimensional Aerodynamic Design Method for Half-Ducted Propeller Fan, Proceedings of the 7th JSME-KSME Thermal and Fluids Engineering Conference, Paper No. G225, 2008.10.
52. Kazuo HARA, Masato FURUKAWA and Naoki AKIHIRO, Experimental and Numerical Analysis of High Heat Transfer Phenomenon in Minichannel Gaseous Cooling, Transactions of the ASME, Journal of Turbomachinery, , Vol. 130, No. 2, pp. 021017-1 - 021017-8, 2008.04.
53. Soichiro TABATA, Fumito HIRATANI and Masato FURUKAWA, Axisymmetric Viscous Flow Modeling for Meridional Flow Calculation in Aerodynamic Design of Half-Ducted Blade Rows, Memoirs of the Faculty of Engineering, Kyushu University, Vol. 67, No. 4, pp. 199-208, 2007.12.
54. Ken-ichiro IWAKIRI, Masato FURUKAWA, Isao TOMITA, Takuro KAMEDA, Motoo KUROUMARU and Masahiro INOUE, Unsteady Flow Phenomena in an Axial Flow Compressor Rotor at Near-Stall Condition, Proceedings of the International Gas Turbine Congress 2007, Paper No. TS-046, 2007.12.
55. Ken-ichiro IWAKIRI, Masato FURUKAWA, Ryota SUZUKI, Seiichi IBARAKI and Isao TOMITA, Analysis of Vortical Flow Field in a Centrifugal Compressor Impeller with Vaneless Diffuser, Proceedings of the 9th Asian International Conference on Fluid Machinery, Paper No. AICFM9-092, 2007.10.
56. Jaeho JEONG, Masato FURUKAWA and Yoriko NINOMIYA, On the Relationship Between Vortical Flow Behavior and Aerodynamic Noise in Propeller Fans, Proceedings of the 9th Asian International Conference on Fluid Machinery, Paper No. AICFM9-089, 2007.10.
57. Jaeho JEONG, Kazuya TAKAHASHI, Ken-ichiro IWAKIRI and Masato FURUKAWA, Three-Dimensional Structure of Separated and Vortical Flows in a Half-Ducted Propeller Fan, Proceedings of the 5th Joint ASME/JSME Fluids Engineering Conference, Paper No. FEDSM2007-37607, 2007.07.
58. Kazuo HARA, Masahiro INOUE and Masato FURUKAWA, Heat Transfer in Minichannel Gaseous Cooling, JSME Journal of Environment and Engineering, Vol. 2, No. 3, pp. 525-534, 2007.07.
59. Seiichi IBARAKI, Masato FURUKAWA, Ken-ichiro IWAKIRI and Kazuya TAKAHASHI, Vortical Flow Structure and Loss Generation Process in a Transonic Centrifugal Compressor Impeller, ASME Paper No. GT2007-27791, 2007.06.
60. Kazuo HARA, Masato FURUKAWA and Naoki AKIHIRO, Experimental and Numerical Analysis of High Heat Transfer Phenomenon in Minichannel Gaseous Cooling, Proceedings of the 4th ASME International Conference on Nanochannels, Microchannels and Minichannels, Paper No. 2006-96213, 2006.06.
61. Kazutoyo YAMADA, Masato FURUKAWA, Masahiro INOUE, Ken-ichi FUNAZAKI, Numerical Analysis of Tip Leakage Flow Field in a Transonic Axial Compressor Rotor, 日本ガスタービン学会誌, Vol. 34, No. 2, pp. 42-50., 2006.04.
62. Ken-ichiro IWAKIRI, Masato FUKAWA, Isao TOMITA, Kazutoyo YAMADA, and Motoo KUROUMARU, Vortical Flow Field in an Axial Flow Compressor Rotor at Rotating Stall Inception, Proceedings of the 3rd International Conference on Vortex Flows and Vortex Models, pp. 211-216., 2005.11.
63. K. YAMADA, M. FURUKAWA, T. NAKANO, M. INOUE and K. FUNAZAKI, Unsteady Three-Dimensional Flow Phenomena due to Breakdown of Tip Leakage Vortex in a Transonic Axial Compressor Rotor, ASME Paper, No. GT2004-53745, pp. 1-12., 2004.06.
64. Choon-Man JANG, Tohru FUKANO and Masato FURUKAWA, Effects of the Tip Clearance on Vortical Flow and Its Relation to Noise in an Axial Flow Fan, JSME International Journal, Series B, 10.1299/jsmeb.46.356, 46, 3, 356-365, Vol. 46, No. 3, pp. 356-365., 2003.08.
65. Jang, C-M, Furukawa, M. and Inoue, M., Frequency Characteristics of Fluctuating Pressure on Rotor Blade in a Propeller Fan, JSME International Journal, Series B, 10.1299/jsmeb.46.163, 46, 1, 163-172, Vol. 46, No. 1, pp. 163-172., 2003.02.
66. Jang, C-M, Furukawa, M. and Inoue, M., Analysis of Vortical Flow Field in a Propeller Fan by LDV Measurements and LES: Part 1. Three-Dimensional Vortical Flow Structures, Transactions of the ASME, Journal of Fluids Engineering, 10.1115/1.1412565, 123, 4, 748-754, Vol. 123, No. 4, pp. 748-754., 2001.12.
67. Jang, C-M, Furukawa, M. and Inoue, M., Analysis of Vortical Flow Field in a Propeller Fan by LDV Measurements and LES: Part 2. Unsteady Nature of Vortical Flow Structures due to Vortex Breakdown, Transactions of the ASME, Journal of Fluids Engineering, 10.1115/1.1412566, 123, 4, 755-761, Vol. 123, No. 4, pp.755-761., 2001.12.
68. Jang, C-M, Furukawa, M. and Inoue, M., Noise Reductiion by Controlling Tip Vortex in a Propeller Fan, JSME International Journal, Series B, 10.1299/jsmeb.44.748, 44, 4, 748-755, Vol. 44, No. 4, pp. 748-755., 2001.11.
69. Furukawa, M., Saiki, K., Yamada, K. and Inoue, M., Unsteady Behavior Due to Breakdown of Tip Leakage Vortex in an Axial Compressor Rotor at Near-Stall Condition, ASME Paper, No. 2000-GT-0666, pp. 1-12., 2000.05.
70. 古川雅人, 才木一寿, 山田和豊, 井上雅弘, 軸流圧縮機動翼の失速点近傍における翼端漏れ渦の崩壊に伴う異常流動現象, 日本機械学会論文集B編, 66巻644号, pp. 1029-1037., 2000.04.
71. Furukawa, M., Inoue, M., Saiki, K. and Yamada, K., The Role of Tip Leakage Vortex Breakdown in Compressor Rotor Aerodynamics, Transactions of the ASME, Journal of Turbomachinery, 121, 3, 469-480, Vol. 121, No. 3, pp. 469-480., 1999.07.
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