Influence of Shock Impingement on Wall Pressure Distribution within a Transpiration Cooled Scramjet

2022 ◽  
Author(s):  
Patrick Cragg ◽  
Friedolin T. Strauss ◽  
Stephan General ◽  
Stefan Schlechtriem
Keyword(s):  
Pressure Distribution ◽  
Wall Pressure ◽  
Shock Impingement

scholarly journals Experimental Research of Wall Pressure Distribution and Effect of Micro Jet at Mach 1.5

2019 ◽  
Vol 8 (2S3) ◽  
pp. 1000-1003 ◽  
Keyword(s):  
Adverse Effect ◽  
Flow Field ◽  
Pressure Distribution ◽  
Area Ratio ◽  
Wall Pressure ◽  
Rapid Expansion ◽  
Base Region ◽  
Active Controls ◽  
Circle Diameter

In this paper, a study on the effect of the control on the wall pressure as well as the quality of the flow when tiny jets were employed. The small jet aimed to regulate the base pressure at the base region of the suddenly expanded duct and wall pressure distribution is carried out experimentally. The convergent-divergent (CD) nozzle with a suddenly expanded duct was designed to observe the wall pressure distribution with and without control using small jets. In order to obtain the results with the effect of controlled four tiny jets of 1 mm diameter located at a ninety-degree interval along a pitch circle diameter (PCD) of 1.3 times the CD nozzle exit diameter in the base, region was employed as active controls. The Mach numbers of the rapidly expanded are 1.5. The jets were expanded quickly into an axis-symmetry duct with an area ratio of 4.84. The length-todiameter (L/D) ratio of the rapid expansion duct was diverse from 10 to 1. There is no adverse effect due to the presence of the tiny jets on the flow field as well as the quality of the flow in the duct

Study of Semi-Inverse Problem for the Design of Annular S-Shaped Compressor Transition Duct

2015 ◽  
Author(s):  
Peng Shan ◽  
Jingyuan Wang ◽  
Zhentao Lv
Keyword(s):  
Inverse Problem ◽  
Pressure Distribution ◽  
Static Pressure ◽  
Pressure Coefficient ◽  
Optimal Solution ◽  
Outer Wall ◽  
Wall Pressure ◽  
Design Parameters ◽  
Gradient Distribution ◽  
Static Pressure Distribution

A new aerodynamic design strategy of the S-shaped transition duct between two compressor components was studied. Based on the controlled wall pressure gradient distribution and the wall velocity distribution, a semi-inverse problem of the transition duct was proposed, the corresponding inverse and direct approach codes were developed. To verify the feasibility of this method, two axial-centrifugal compressor transition ducts were designed. The results show that the static pressure distribution on the inner wall and the duct geometry both can be controlled freely by adjusting the inverse design parameters. The designed inner wall pressure distribution can be realized through a numerical matching procedure of the outer wall geometry based on the direct problem. The new design method is practicable that, without searching the optimal solution of the static pressure distribution of the inner wall, the total pressure coefficient can be at least 0.92.

Use of Subdomains for Inverse Problems in Branching Flow Passages

1992 ◽  
Author(s):  
S. Krishnan ◽  
Ajay K. Agrawal ◽  
Tah-teh Yang
Keyword(s):  
Inverse Problems ◽  
Pressure Distribution ◽  
Incompressible Flows ◽  
Wall Pressure ◽  
Calculation Procedure ◽  
Navier Stokes ◽  
Main Duct ◽  
Complex Flow ◽  
Numerical Predictions ◽  
Branching Flow

For inverse problems in complex flow passages, a calculation procedure based on multizone Navier-Stokes method was developed. A heuristic approach was employed to derive wall shape corrections from the wall pressure error. Only two subdomains sharing a row of control volumes were used in the present work. The grid work in the common region was identical for both subdomains. The flow solver, inverse calculation procedure, multizone Navier-Stokes method and subdomain inverse calculation procedure were validated independently against experimental data or numerical predictions. The subdomain inverse calculation method was applied to determine the wall shape of the main duct of a branching flow passage. This main duct was to minimize the pressure gradient downstream of the sidebranch. Inverse calculations resulted in a range of wall shapes with wall pressure distribution approaching the design (prescribed) wall pressure distribution. The present approach was illustrated for laminar, incompressible flows in branching passages. However, the method presented is flexible and can be extended for inverse turbulent flow calculations in multiply connected domains.

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