Flow Nonuniformity in Shock Tubes Operating at Maximum Test Times

1966 ◽  
Vol 9 (10) ◽  
pp. 1907 ◽  
Author(s):  
H. Mirels
AIAA Journal ◽  
1981 ◽  
Vol 19 (5) ◽  
pp. 660-661
Author(s):  
A. J. Cunningham ◽  
G. L. Ogram ◽  
Jen-Shih Chang ◽  
R. M. Hobsons

2020 ◽  
Vol 14 (4) ◽  
pp. 614-617
Author(s):  
A. D. Kiverin ◽  
K. O. Minaev ◽  
I. S. Yakovenko
Keyword(s):  

1958 ◽  
Vol 3 (05) ◽  
pp. 457 ◽  
Author(s):  
R. A. Alpher ◽  
D. R. White
Keyword(s):  

Author(s):  
Ritobrata Sur ◽  
Shengkai Wang ◽  
Kai Sun ◽  
David F. Davidson ◽  
Jay B. Jeffries ◽  
...  
Keyword(s):  

1996 ◽  
Vol 118 (3) ◽  
pp. 529-535 ◽  
Author(s):  
P. W. Giel ◽  
J. R. Sirbaugh ◽  
I. Lopez ◽  
G. J. Van Fossen

Experimental measurements in the inlet of a transonic turbine blade cascade showed unacceptable pitchwise flow nonuniformity. A three-dimensional, Navier–Stokes computational fluid dynamics (CFD) analysis of the imbedded bellmouth inlet in the facility was performed to identify and eliminate the source of the flow nonuniformity. The blockage and acceleration effects of the blades were accounted for by specifying a periodic static pressure exit condition interpolated from a separate three-dimensional Navier–Stokes CFD solution of flow around a single blade in an infinite cascade. Calculations of the original inlet geometry showed total pressure loss regions consistent in strength and location to experimental measurements. The results indicate that the distortions were caused by a pair of streamwise vortices that originated as a result of the interaction of the flow with the imbedded bellmouth. Computations were performed for an inlet geometry that eliminated the imbedded bellmouth by bridging the region between it and the upstream wall. This analysis indicated that eliminating the imbedded bellmouth nozzle also eliminates the pair of vortices, resulting in a flow with much greater pitchwise uniformity. Measurements taken with an installed redesigned inlet verify that the flow nonuniformity has indeed been eliminated.


Author(s):  
Nuntaphong Koondilogpiboon ◽  
Tsuyoshi Inoue

Abstract In this paper, an efficient numerical method consisting of the real mode component mode synthesis (CMS) model reduction, shooting method with parallel computing, and Floquet analysis was developed for nonlinear rotordynamics analysis of a flexible rotor supported by a 4-lobe flexure pivot tilting pad journal bearing (FPTPJB) in load-on-pad (LOP) and load-between-pad (LBP) orientations in comparison to a fixed profile journal bearing (JB) of the same pad geometry. The method used the rotor's finite elements and bearing forces obtained from directly solving the Reynolds equation to determine the limit cycles and Hopf bifurcation types. For the investigated rotor and bearing parameters, the numerical results indicated that the onset speed of instability (OSI) of FPTPJB is considerably higher than that of JB of the same orientation. Also, FPTPJB in LOP orientation yielded higher OSI than the LBP one, whereas the OSI of JB in LOP orientation was substantially higher than the LBP counterpart. Nonlinear calculation results indicated that all bearing types and orientations gave subcritical Hopf bifurcation. The FPTPJB in LOP orientation produced the largest stable operating region, whereas the JB in LBP configuration yield the smallest one. The experiment showed subcritical Hopf bifurcation occurred at speed close to the calculated OSI in all cases except FPTPJB in LOP orientation that the OSI is higher than the maximum test rig speed. The whirling orbit had the same frequency as the first critical speed and precessed in the direction of shaft rotation.


Sign in / Sign up

Export Citation Format

Share Document