NASA rotor 37 was used as a ’blind’ test case for turbomachinery CFD by the Turbimachinery Com-mittee of the IGTI. The rotor is a transonic compressor with a tip speed of 454 m/s (15OO ft/s) anda relatively high pre...NASA rotor 37 was used as a ’blind’ test case for turbomachinery CFD by the Turbimachinery Com-mittee of the IGTI. The rotor is a transonic compressor with a tip speed of 454 m/s (15OO ft/s) anda relatively high pressure ratio of 2.1. It was tested in isolation with a circumferentially uniform inletflow so that the flow through it should be steady apart from any effects of passage to passage geometry variation and mechanical vibration. As such it represents the simplest possible type of test forthree-dimensional turbomachinery flow solvers. However, the rotor still presents a real challenge to3D viscous flow solvers because the shock wave-boundary layer interaction is strong and the effects ofviscosity are dominant in determining the flow deviation and hence the pressure ratio. Eleven ’blind’solutions were submitted and in addition a ’non-blind’ solution was used to prepare for the exercise-This paper reviews the fiow in the test case and the comparisons of the CFD solutions with the testdata. Lessons for both the Flow Physics in transonic has and for the application of CFD to suchmachines are pointed out.展开更多
An investigation of the passive control of shock wave/boundary laper interaction for reducing the amplitude of the shock oscillation was conducted on the circular arc-wedge (CW) profile cascade in a 220×290 mm tr...An investigation of the passive control of shock wave/boundary laper interaction for reducing the amplitude of the shock oscillation was conducted on the circular arc-wedge (CW) profile cascade in a 220×290 mm transonic compressor cascade wind tunnel. A perforated surface with a cavity beneath it was positioned on the suction surface of the blade at the location of shock impingement. The Schlieren and high-speed photographs for flow over perforated blade are presented and compared with the results for solid blades. With the perforated surface, the high-speed photographs indicated an significant suppression of shock oscillation.展开更多
The effects of boundary layer bleed on the scramjet thrust are studied in the present paper.A theoretical model is developed to evaluate the thrust increment and influencing factors.The thrust increment resulting from...The effects of boundary layer bleed on the scramjet thrust are studied in the present paper.A theoretical model is developed to evaluate the thrust increment and influencing factors.The thrust increment resulting from the bleed is dominated by the rise in total pressure recovery and bleed mass flow rate.The bleed mass flow rate exerts stronger impact on the engine thrust than the total pressure.According to current bleed design,it is a severe challenge for the engine to enhance its total pressure to maintain the original thrust when there is no bleeding.Furthermore,the initial total pressure recovery,fuel mass addition,combustion efficiency and area ratio of engine exit to entrance can affect the contributions of the bleeding to the thrust increment.The scramjet needs a higher rise in total pressure recovery to counteract the negative effect of bleed mass loss at higher initial total pressure recovery or larger area ratio of engine exit/entrance.More heat release results in a little lower demand on the rise in total pressure recovery for maintaining the scramjet thrust.These results will aid in understanding the fundamental mechanism of bleeding on engine thrust.展开更多
As a part of boundaries for a free curved surface of a Pelton bucket,the cutout is indispensable to secure the smooth entrance of the unsteady inflow of water jet into the rotating bucket.The cutout of the rotating bu...As a part of boundaries for a free curved surface of a Pelton bucket,the cutout is indispensable to secure the smooth entrance of the unsteady inflow of water jet into the rotating bucket.The cutout of the rotating bucket unsteadily separates a free jet into two branches in both space and time:the impinging branch landing on the relevant bucket surface,and the flow-off branch separated by the cutout toward the preceding bucket.In order to investigate the unsteady jet separation by the cutout three-dimensionally,a semicircular free jet was discretized into 641 nodes of boundary-fitted grids.The position P of impinging jet branch landing on the bucket surface was acquired with the relative velocity W and the water depth D at each node.The trailing edge surface of the flow-off jet branch was simultaneously computed unsteadily.The complicate unsteady interaction of the bucket cutout with the branched free jets was clarified visually with the 3D view of illustrations in order to research the unsteady hydraulic performance of Pelton turbines in space and time.展开更多
文摘NASA rotor 37 was used as a ’blind’ test case for turbomachinery CFD by the Turbimachinery Com-mittee of the IGTI. The rotor is a transonic compressor with a tip speed of 454 m/s (15OO ft/s) anda relatively high pressure ratio of 2.1. It was tested in isolation with a circumferentially uniform inletflow so that the flow through it should be steady apart from any effects of passage to passage geometry variation and mechanical vibration. As such it represents the simplest possible type of test forthree-dimensional turbomachinery flow solvers. However, the rotor still presents a real challenge to3D viscous flow solvers because the shock wave-boundary layer interaction is strong and the effects ofviscosity are dominant in determining the flow deviation and hence the pressure ratio. Eleven ’blind’solutions were submitted and in addition a ’non-blind’ solution was used to prepare for the exercise-This paper reviews the fiow in the test case and the comparisons of the CFD solutions with the testdata. Lessons for both the Flow Physics in transonic has and for the application of CFD to suchmachines are pointed out.
文摘An investigation of the passive control of shock wave/boundary laper interaction for reducing the amplitude of the shock oscillation was conducted on the circular arc-wedge (CW) profile cascade in a 220×290 mm transonic compressor cascade wind tunnel. A perforated surface with a cavity beneath it was positioned on the suction surface of the blade at the location of shock impingement. The Schlieren and high-speed photographs for flow over perforated blade are presented and compared with the results for solid blades. With the perforated surface, the high-speed photographs indicated an significant suppression of shock oscillation.
基金supported by the National Natural Science Foundation of China(Grant Nos.90716014 and 91216115)
文摘The effects of boundary layer bleed on the scramjet thrust are studied in the present paper.A theoretical model is developed to evaluate the thrust increment and influencing factors.The thrust increment resulting from the bleed is dominated by the rise in total pressure recovery and bleed mass flow rate.The bleed mass flow rate exerts stronger impact on the engine thrust than the total pressure.According to current bleed design,it is a severe challenge for the engine to enhance its total pressure to maintain the original thrust when there is no bleeding.Furthermore,the initial total pressure recovery,fuel mass addition,combustion efficiency and area ratio of engine exit to entrance can affect the contributions of the bleeding to the thrust increment.The scramjet needs a higher rise in total pressure recovery to counteract the negative effect of bleed mass loss at higher initial total pressure recovery or larger area ratio of engine exit/entrance.More heat release results in a little lower demand on the rise in total pressure recovery for maintaining the scramjet thrust.These results will aid in understanding the fundamental mechanism of bleeding on engine thrust.
基金supported by the National Natural Science Foundation of China(Grant No.50379015)the Major Science and Technology Projects in Zhejiang province(Grant No.2008C11057)
文摘As a part of boundaries for a free curved surface of a Pelton bucket,the cutout is indispensable to secure the smooth entrance of the unsteady inflow of water jet into the rotating bucket.The cutout of the rotating bucket unsteadily separates a free jet into two branches in both space and time:the impinging branch landing on the relevant bucket surface,and the flow-off branch separated by the cutout toward the preceding bucket.In order to investigate the unsteady jet separation by the cutout three-dimensionally,a semicircular free jet was discretized into 641 nodes of boundary-fitted grids.The position P of impinging jet branch landing on the bucket surface was acquired with the relative velocity W and the water depth D at each node.The trailing edge surface of the flow-off jet branch was simultaneously computed unsteadily.The complicate unsteady interaction of the bucket cutout with the branched free jets was clarified visually with the 3D view of illustrations in order to research the unsteady hydraulic performance of Pelton turbines in space and time.
