Three-Dimensional Rotational Flow in Transonic Turbomachines: Part I—Solution Obtained Using a Number of S1 Stream Filaments of Revolution and a Central S2 Stream Filament

1992 ◽  
Vol 114 (1) ◽  
pp. 38-49 ◽  
Author(s):  
Wu Chung-Hua ◽  
Wang Zhengming ◽  
Chen Hongji
Keyword(s):  
Three Dimensional ◽  
Iterative Solution ◽  
Dimensional Structure ◽  
Rotational Flow ◽  
Three Dimensional Flow ◽  
Dimensional Solution ◽  
Quick Method ◽  
Dimensional Flow ◽  
Complete Procedure ◽  
Flow Variables

The general theory of three-dimensional flow in subsonic and supersonic turbo-machines (Wu, 1952a) is extended to the three-dimensional rotational flow in transonic turbomachines. In Part I of this paper, an approximation that the S1 stream filaments are filaments of revolution is made. Then, the three-dimensional solution is obtained by an iterative solution between a number of S1 stream filaments and a single S2 stream filament. A recently developed relatively simple and quick method of solving the transonic S1 flow is utilized. The complete procedure is illustrated with the solution of the three-dimensional flow in the DFVLR rotor operating at the design point. The solution is presented in detail, special emphasis being placed on the fulfillment of the convergence requirement. The character of the three-dimensional field obtained is examined with the three-dimensional structure of the passage shock, the relative Mach number contours on a number of S1 surfaces, S2 surfaces, and cross surfaces, and the variations of the thickness of S1 and S2 filaments. Comparison between the calculated three-dimensional field with the DFVLR measured data shows that the character of the flow field and the streamwise variation of the flow variables in the middle of the flow channel are in good agreement. It is recommended that the method presented herein can be used for three-dimensional design of transonic turbomachines.

scholarly journals Three-Dimensional Rotational Flow in Transonic Turbomachines: Part I — Solution Obtained by Using a Number of S1 Stream Filaments of Revolution and a Central S2 Stream Filament

1990 ◽  
Author(s):  
Wu Chung-Hua ◽  
Wang Zhengming ◽  
Chen Hongji
Keyword(s):  
Three Dimensional ◽  
Iterative Solution ◽  
Dimensional Structure ◽  
Rotational Flow ◽  
Three Dimensional Flow ◽  
Dimensional Solution ◽  
Quick Method ◽  
Complete Procedure ◽  
Flow Variables ◽  
Good Agreement

The general theory of three-dimensional flow in subsonic and supersonic turbomachines (Wu, 1952) is extended to the three-dimensional rotational flow in transonic turbomachines. In Part I of the paper, an approximation that the S1 stream filaments are filaments of revolution is made. Then, the three-dimensional solution is obtained by an iterative solution between a number of S1 stream filaments and a single S2 stream filament. Recently developed relatively simple and quick method of solving the transonic S1 flow is utilized. The complete procedure is illustrated with the solution of the 3D flow in the DFVLR rotor operating at the design point. The solution is presented in detail, special emphasis being placed on the fulfillment of the convergence requirement. The character of the three-dimensional field obtained is examined with the three-dimensional structure of the passage shock, the relative Mach number contours on a number of S1 surfaces, S2 surfaces, and cross surfaces, and the variations of the thickness of S1 and S2 filaments. Comparison between the calculated three-dimensional field with the DFVLR measured data shows: the character of the flow field and the streamwise variation of the flow variables in the middle of the flow channel are in good agreement. It is recommended that the method presented herein can be used for three-dimensional design of transonic turbomachines.

Quasi-Three-Dimensional and Full Three-Dimensional Rotational Flow Calculations in Turbomachines

1985 ◽  
Vol 107 (2) ◽  
pp. 277-284 ◽  
Author(s):  
Qinghuan Wang ◽  
Genxing Zhu ◽  
Chung-Hua Wu
Keyword(s):  
Flow Field ◽  
Numerical Solutions ◽  
Three Dimensional ◽  
Relaxation Method ◽  
Computing System ◽  
Curvilinear Coordinates ◽  
Rotational Flow ◽  
Three Dimensional Flow ◽  
Dimensional Solution ◽  
Dimensional Flow

Progress in the development of quasi-three-dimensional and full three-dimensional numerical solutions for steady subsonic rotational flow through turbomachines is presented. An iterative calculation between the flow on a mean hub-to-tip S2 stream surface and a number of blade-to-blade S1 stream surfaces gives the quasi-three-dimensional solution, which is very easily extended to give full three-dimensional solution by merely calculating a few more S2 surface flows and relaxing the restriction that S1 surfaces are surfaces of revolution. A new S2–S1 iteration scheme has been developed and employed in the present code. The governing equations on the S1 and S2 surfaces are expressed in terms of general nonorthogonal curvilinear coordinates so that they are body-fitted without any coordinate transformation and are solved by either matrix method or line-relaxation method. An automatic computing system is used, which first computes the quasi-three-dimensional flow for blade design and then computes the full three-dimensional flow for the blade row just designed. The results obtained by applying this computing system to the design and determination of full three-dimensional flow field of a two-stage axial compressor and a high subsonic compressor stator are obtained and shows clearly the amount of the twist of the general S1 surfaces and the difference in the flow field between the quasi-three-dimensional and full three-dimensional solutions.

scholarly journals CROSSINN - a field experiment to study the three-dimensional flow structure in the Inn Valley, Austria

2020 ◽  
pp. 1-55 ◽  
Author(s):  
Bianca Adler ◽  
Alexander Gohm ◽  
Norbert Kalthoff ◽  
Nevio Babić ◽  
Ulrich Corsmeier ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Field Experiment ◽  
Flow Structure ◽  
State Of The Art ◽  
Three Dimensional ◽  
Dimensional Structure ◽  
Three Dimensional Flow ◽  
Three Dimensional Structure ◽  
Alpine Valley ◽  
Dimensional Flow

Capsule SummaryThe CROSSINN field experiment investigates the three-dimensional structure of thermally and dynamically driven flows and their impact on the boundary layer in a large Alpine valley using comprehensive state-of-the-art instrumentation.

Three-Dimensional Rotational Flow in Transonic Turbomachines: Part II—Full Three-Dimensional Flow in CAS Rotor Obtained by Using a Number of S1 and S2 Stream Filaments

1992 ◽  
Vol 114 (1) ◽  
pp. 50-60
Author(s):  
Wu Chung-Hua ◽  
Zhao Xiaolu ◽  
Qin Lisen
Keyword(s):  
Transonic Flow ◽  
Present Method ◽  
Three Dimensional ◽  
Flow Fields ◽  
Rotational Flow ◽  
Three Dimensional Flow ◽  
Measured Velocity ◽  
Dimensional Flow ◽  
Iterative Calculation ◽  
Good Agreement

The general theory for three-dimensional flow in subsonic and supersonic turbo-machines has recently been extended to transonic turbomachines. In this paper, which is Part II of the study, quasi- and full three-dimensional solutions of the transonic flow in the CAS rotor are presented. The solutions are obtained by iterative calculation between a number of S1 stream filaments and, respectively, a central S2m Stream filament and a number of S2 stream filaments. Relatively simple methods developed recently for solving the transonic flow along S1 and S2 stream filaments are used in the calculation. The three-dimensional flow fields in the CAS rotor obtained by the present method are presented in detail with special emphasis on the converging process for the configuration of the S1 and S2 stream filaments. The three-dimensional flow fields obtained in the quasi- and full three-dimensional solutions are quite similar, but the former gives a lower peak Mack number and a smaller circumferential variation in Mach number than the latter. A comparison between the theoretical solution and the Laser-2-Focus measurement shows that the character of the transonic flow including the three-dimensional shock structure is in good agreement, but the measured velocity is slightly higher than the calculated one over most of the flow field.

The Three-Dimensional Flow and Blade Wake in an Axial Plane Downstream of an Axial Compressor Rotor

1978 ◽  
Author(s):  
P. Kool ◽  
J. DeRuyck ◽  
Ch. Hirsch
Keyword(s):  
Three Dimensional ◽  
Axial Compressor ◽  
Axial Plane ◽  
Hot Wire ◽  
Three Dimensional Flow ◽  
Dimensional Flow ◽  
Wall Boundary Layer ◽  
Compressor Rotor ◽  
Three Dimensional Finite Element ◽  
Flow Variables

The three-dimensional flow field has been measured in an axial plane downstream of a low speed axial compressor rotor with a rotated single slanted hot wire. A method is described which allows one to calculate three mutually perpendicular velocity components from hot-wire data, and use is made of the technique of periodic sampling and averaging to extract the pitchwise fluctuating flow from the stationary hot-wire signals. These data contain useful information. The radial distribution of the pitchwise averaged flow variables is compared with classical pneumatic measurements and with the results of a quasi three-dimensional finite-element calculation and a three-dimensional end-wall boundary layer calculation. Finally, the wake characteristics are given and a simple correlation is presented which allows one to determine the wake velocity defect from a single wake shape factor.

Three-Dimensional Rotational Flow in Transonic Turbomachines: Part II — Full 3D Flow in CAS Rotor Obtained by Using a Number of S1 and S2 Stream Filaments

1990 ◽  
Author(s):  
Wu Chung-Hua ◽  
Zhao Xiaolu ◽  
Qin Lisen
Keyword(s):  
Mach Number ◽  
Transonic Flow ◽  
Three Dimensional ◽  
Flow Fields ◽  
Rotational Flow ◽  
Three Dimensional Flow ◽  
Measured Velocity ◽  
Dimensional Flow ◽  
Iterative Calculation ◽  
Good Agreement

The general theory for three–dimensional flow in subsonic and supersonic turbomachines has recently been extended to transonic turbomachines. In Part II of the paper, quasi– and full three–dimensional solutions of the transonic flow in the CAS rotor are presented. The solutions are obtained by iterative calculation between a number of S1 stream filaments and, respectively, a central S2 stream filament and a number of S2m stream filaments. Relatively simple methods developed recently for solving the transonic flow along S1 and S2 stream filaments are used in the calculation. The three–dimensional flow fields in the CAS rotor obtained by the present method are presented in detail with special emphasis on the converging process for the configuration of the S1 and S2 stream filaments. The three–dimensional flow fields obtained in the quasi– and full 3D solutions are quite similar, but the former gives a lower peak Mach number and a smaller circumferential variation in Mach number than the latter. A comparison between the theoretical solution and the Laser–2–Focus measurement shows that the character of the transonic flow including the 3D shock structure is in good agreement, but the measured velocity is slightly higher than the calculated one over most of the flow field.

Sign in / Sign up

Export Citation Format

Share Document