This paper investigates the relationship between drag coefficient and the Mach number after distortion net and reveals the mechanisms of the rapid increase in total pressure loss when the upstream mach number exceeds the critical mach number based on CFD simulation.The results show that the normal shock wave and oblique shock wave occur in the flow field and result in the rapid increase in total pressure loss when upstream Mach number is beyond the critical Mach number.The critical condition occurs at lower inlet Mach number when the solidity of cylinder increases because the throat reaches the acoustic speed and oblique shock wave emerges in the diffuser part.
ZHANG Sheng, REN Wen-cheng, TU Bao-feng, DING Yi-ming
. CFD numerical simulating investigation on distortion net[J]. Journal of Shenyang Aerospace University, 2013
, 30(5)
: 27
-32
.
DOI: 10.3969/j.issn.2095-1248.2013.05.006
[1]Milt Davis, Alan Hale, Dave Beale.An argument for enhancement of the current inlet distortion ground test practice for aircraft gas turbine engines[J].Journal of Turbomachinery, 2002(124):235-241.
[2]D K Beale, K B Cramer, P S King.Development of improved methods for simulating aircraft inlet distortion in turbine engine ground tests[C].AIAA, St.Louis:Missouri, 2002.
[3]顾杨, 张健.多级轴流压气机总压畸变试验研究[J].燃气涡轮试验与研究, 1999, 12(2):1-5.
[4]William T C.History, philosophy, physics, and future directions of aircraft propulsion system /inlet integration[C].ASME, 2004.
[5]Annand W J D.The resistance to airflow of wire gauzes[J].J Roy Aero Soc, 1953(57):141-146.
[6]Edler J W.Steady flow through non-uniform gauzes of arbitrary shape[J].Journal of Fluid Mechanics, 1959(5):355-368.
[7]McCarthy J H.Steady flow past non-uniform wire grids[J].Journal of Fluid Mechanics, 1964(19):491-512.
[8]Peacock R E, EL-Attar M A, Robison G D.Asymmetric distortion generation in a variable height annlus[R].AIAA-79-7002.
[9]Cornell W G.Losses in flow normal to plane screens[J].Transactions of The ASME, 1958(80):491-512.
[10]Weighardt K E G.On the resistance of screens[J].The Aeronautical Quarterly, 1953(4):186-192.
