Numerical Solution of Inviscid Two-Dimensional Transonic Flow Through a Cascade

1987 ◽  
Vol 109 (1) ◽  
pp. 108-113
Author(s):  
J. Forˇt ◽  
K. Kozel
Keyword(s):  
Experimental Data ◽  
Weak Solution ◽  
Numerical Solution ◽  
Transonic Flow ◽  
Numerical Procedure ◽  
Numerical Results ◽  
Two Dimensional ◽  
System Of Difference Equations ◽  
Flow Through ◽  
Turbine Cascades

The paper presents a method of numerical solution of transonic potential flow through plane cascades with subsonic inlet flow. The problem is formulated as a weak solution with combined Dirichlet’s and Neumann’s boundary conditions. The numerical procedure uses Jameson’s rotated difference scheme and the SLOR technique to solve a system of difference equations. Numerical results of transonic flow are compared with experimental data and with other numerical results for both compressor and turbine cascades near choke conditions.

Time-Marching Analysis of Steady Transonic Flow in Turbomachinery Cascades Using the Hopscotch Method

1983 ◽  
Vol 105 (2) ◽  
pp. 272-279 ◽  
Author(s):  
R. A. Delaney
Keyword(s):  
Experimental Data ◽  
Euler Equations ◽  
Transonic Flow ◽  
Numerical Scheme ◽  
Curvilinear Coordinates ◽  
Two Dimensional ◽  
Analysis Method ◽  
Time Marching ◽  
Turbine Cascades ◽  
Turbomachinery Cascades

A rapid, time-marching, numerical scheme based on the hopscotch method is presented for solution of steady, two-dimensional, transonic flow in turbomachinery cascades. The scheme is applied to the strong-conservation form of the unsteady Euler equations written in arbitrary curvilinear coordinates. Cascade solutions are obtained on an orthogonal, body-centered coordinate system. Numerical solution results for two turbine cascades are presented and compared with experimental data to demonstrate the accuracy and computational efficiency of the analysis method.

The Computation of Transonic Flow Through Two-Dimensional Gas Turbine Cascades

1971 ◽  
Author(s):  
P. W. McDonald
Keyword(s):  
Flow Field ◽  
Gas Turbine ◽  
Transonic Flow ◽  
Equations Of Motion ◽  
Two Dimensional ◽  
Airfoil Surface ◽  
Pressure Distributions ◽  
Flow Through ◽  
Turbine Cascades ◽  
Definition Of

Steady transonic flow through two-dimensional gas turbine cascades is efficiently predicted using a time-dependent formulation of the equations of motion. An integral representation of the equations has been used in which subsonic and supersonic regions of the flow field receive identical treatment. Mild shock structures are permitted to develop naturally without prior knowledge of their exact strength or position. Although the solutions yield a complete definition of the flow field, the primary aim is to produce airfoil surface pressure distributions for the design of aerodynamically efficient turbine blade contours. In order to demonstrate the accuracy of this method, computed airfoil pressure distributions have been compared to experimental results.

Time-Marching Analysis of Steady Transonic Flow in Turbomachinery Cascades Using the Hopscotch Method

1982 ◽  
Author(s):  
R. A. Delaney
Keyword(s):  
Experimental Data ◽  
Euler Equations ◽  
Transonic Flow ◽  
Numerical Scheme ◽  
Curvilinear Coordinates ◽  
Two Dimensional ◽  
Analysis Method ◽  
Time Marching ◽  
Turbine Cascades ◽  
Turbomachinery Cascades

A rapid, time-marching, numerical scheme based on the hopscotch method is presented for solution of steady, two-dimensional, transonic flow in turbomachinery cascades. The scheme is applied to the strong-conservation form of the unsteady Euler equations written in arbitrary curvilinear coordinates. Cascade solutions are obtained on an orthogonal, body-centered coordinate system. Numerical solution results for two turbine cascades are presented and compared with experimental data to demonstrate the accuracy and computational efficiency of the analysis method.

scholarly journals Transonic Flow Through Turbine Cascades With Nonuniform Pitch

1992 ◽  
Author(s):  
R. Kurz
Keyword(s):  
Experimental Data ◽  
Measurement System ◽  
Transonic Flow ◽  
Reynolds Numbers ◽  
Calculation Procedure ◽  
Flow Through ◽  
Turbine Cascades

The flow behind linear turbine cascades with uniform and nonuniform pitches was investigated both theoretically and experimentally. A calculation procedure based on an Euler–code for nonuniform pitch to chord ratios is presented. Experimental data were obtained by using a Laser–2–Focus measurement system and Kiel probes. Outlet Laval numbers range from 0.7 to 1.0, corresponding to Reynolds numbers from 380,000 to 700,000. The pitch–to–chord ratio of the investigated configurations reaches from 0.771 to 0.877.

A REGENERATIVE COOLING SYSTEM FOR THE CHAMBER OF A LIQUID-PROPELLANT ROCKET ENGINE WITH INTERCHANNEL COOLANT FLOW THROUGH A METAL MESH

2021 ◽  
pp. 65-77
Author(s):  
Fedor V. PELEVIN ◽  
Aleksey V. PONOMAREV
Keyword(s):  
Experimental Data ◽  
Heat Exchange ◽  
Porous Metal ◽  
Coolant Flow ◽  
Two Dimensional ◽  
Liquid Propellant ◽  
Metal Mesh ◽  
Regenerative Cooling ◽  
Flow Through ◽  
Propellant Rocket

The paper discusses a new method for regenerative cooling of the chamber of liquid-propellant rocket engines using the concept of interchannel coolant flow through a porous metal mesh made by vacuum diffusion welding of woven metal netting. It provides a theoretical rationale for switching from unidimensional (longitudinally channeled) flow to two-dimensional (interchannel) inter-mesh flow coolant through a porous mesh. It provides experimental data for hydraulic resistance and heat exchange in porous metal meshes. Based on the experimental data, a generalized criterial equation was obtained for surface heat release in the paths with interchannel two-dimensional intermesh coolant flow through metal mesh. The paper examines the efficiency of heat exchange in the paths with interchannel coolant flow. Key words: regenerative cooling, interchannel flow; vacuum diffusion technology, metal mesh; hydraulic resistance; heat exchange, heat exchange efficiency.

Numerical Solution of Periodic Transonic Flow through a Fan Stage

AIAA Journal ◽  
1977 ◽  
Vol 15 (11) ◽  
pp. 1559-1568 ◽  
Author(s):  
J. I. Erdos ◽  
E. Alzner ◽  
W. McNally
Keyword(s):  
Numerical Solution ◽  
Transonic Flow ◽  
Flow Through

scholarly journals MODELING OF ELASTIC-PLASTIC DEFORMATION OF ELEMENTS OF SPATIAL STRUCTURES DURING PULSE INTERACTION WITH FLUID BASED ON THE GODUNOV'S METHOD OF INCREASED ACCURACY

2019 ◽  
Vol 81 (4) ◽  
pp. 488-499
Author(s):  
Wang Cheng ◽  
Yang Tonghui ◽  
Li Wan ◽  
Tao Li ◽  
M.H. Abuziarov ◽  
...  
Keyword(s):  
Experimental Data ◽  
Shock Waves ◽  
Elastoplastic Deformation ◽  
Three Dimensional ◽  
Numerical Results ◽  
Two Dimensional ◽  
Wave Processes ◽  
Detonation Products ◽  
Comparison Of The Results ◽  
Good Agreement

The spatial problem of internal explosive loading of an elastoplastic cylindrical container filled with water in Eulerian - Lagrangian variables using multigrid algorithms is considered. A defining system of three-dimensional equations of the dynamics of gas, fluid, and elastoplastic medium is presented. For numerical modeling, a modification of S.K. Godunov scheme of the increased accuracy for both detonation products and liquids, and elastoplastic container is used. At the moving contact boundaries “detonation products - liquid”, “liquid - deformable body”, the exact solution of the Riemann's problem is used. A time dependent model is used to describe the propagation of steady-state detonation wave through an explosive from an initiation region. In both cases, the initiation of detonation occurs at the center of the charge. Two problems have been solved: the first task for the aisymmetric position of the charge, the second for the charge shifted relative to the axis of symmetry. In the first task, the processes are two-dimensional axisymmetric in nature, in the second task, the processes are essentially three-dimensional. A comparison is made of the results of calculations of the first problem using a three-dimensional method with a solution using a previously developed two-dimensional axisymmetric method and experimental data. Good agreement is observed between the numerical results for the maximum velocities and circumferential strains obtained by various methods and experimental data. There is good agreement between the numerical results obtained by various methods and the known experimental data. Comparison of the results of solving the first and second problems shows a significant effect of the position of the charge on the wave processes in the liquid, the processes of loading the container and its elastoplastic deformation. The dynamic behavior of a gas bubble with detonation products is analyzed. A significant deviation of the bubble shape from the spherical one, caused by the action of shock waves reflected from the structure, is shown. Comparison of the results of solving the first and second problems showed a significant effect of the charge position on wave processes in a liquid, the processes of loading a container and its elastoplastic deformation. In particular, in the second problem, shock waves of higher amplitude are observed in the liquid when reflected from the walls of the container.

scholarly journals Numerical Solution to Transonic Potential Equations on S2 Stream Surface in a Turbomachine

1988 ◽  
Author(s):  
J. Y. Du ◽  
Y. Q. Zhao ◽  
Y. Guo ◽  
J. Z. Xu
Keyword(s):  
Experimental Data ◽  
Numerical Solution ◽  
Potential Method ◽  
Divergence Form ◽  
Numerical Results ◽  
Stream Surface ◽  
Entropy Increase ◽  
Classical Potential ◽  
Good Agreement

A non-isentropic potential method on a S2 stream surface has been developed for the design and analysis of transonic compressors with shocks, in which the entropy increase across a shock may be directly calculated from the momentum equations in the divergence form. The numerical results show that the non-isentropic shock is weaker and placed one or two meches further upstream compared to the classical potential calculation, and is in good agreement with the experimental data.

Transonic Flow in Curved Channels

1967 ◽  
Vol 89 (4) ◽  
pp. 748-752 ◽  
Author(s):  
P. A. Thompson
Keyword(s):  
Transonic Flow ◽  
Approximate Calculation ◽  
Continuity Condition ◽  
Numerical Results ◽  
Two Dimensional ◽  
Curved Channels ◽  
Symmetric Channel ◽  
Analytical Results ◽  
Limiting Case

Transonic flow in a curved two-dimensional throat is considered. The approximate calculation is based on the full nonlinear inviscid equations and an integral continuity condition. Numerical results are presented in the form of curves which permit the determination of the flow in a nozzle of specified geometry. Analytical results reduce after linearization to those of Sauer for the limiting case of a symmetric channel.

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