Low Aspect Ratio Transonic Rotors: Part 1—Baseline Design and Performance

1993 ◽  
Vol 115 (2) ◽  
pp. 218-225 ◽  
Author(s):  
C. H. Law ◽  
A. R. Wadia
Keyword(s):  
Flow Analysis ◽  
Axial Flow ◽  
Test Point ◽  
Design Parameters ◽  
Design Study ◽  
Baseline Design ◽  
Design Variables ◽  
Compressor Design ◽  
Compressor Performance ◽  
Few Data

The analytical design and experimental test of a single-stage transonic axial-flow compressor are described. This design is the baseline of a compressor design study in which several blade design parameters have been systematically varied to determine their independent effects on compressor performance. The baseline design consisted of ruggedizing an existing compressor design that demonstrated outstanding aerodynamic performance, to correct some undesirable aeromechanical characteristics. The design study was performed by varying only one design parameter at a time, keeping the other design variables as close as possible to the baseline design. Specific design parameters of interest were those for which very few data were available to determine their sensitivity on compressor performance. This paper describes the baseline compressor design and its experimental performance. A detailed definition and flow analysis of the baseline design test point (used as the basis for all subsequent design variations) are provided.

Low Aspect Ratio Transonic Rotors: Part 1 — Baseline Design and Performance

1992 ◽  
Author(s):  
C. H. Law ◽  
A. R. Wadia
Keyword(s):  
Flow Analysis ◽  
Axial Flow ◽  
Test Point ◽  
Design Parameters ◽  
Design Study ◽  
Baseline Design ◽  
Design Variables ◽  
Compressor Design ◽  
Compressor Performance ◽  
And Performance

The analytical design and experimental test of a single-stage transonic axial-flow compressor are described. This design is the baseline of a compressor design study in which several blade design parameters have been systematically varied to determine their independent effects on compressor performance. The baseline design consisted of ruggedizing an existing compressor design, that demonstrated outstanding aerodynamic performance, to correct some undesirable aeromechanical characteristics. The design study was performed by varying only one design parameter at a time, keeping other design variables as close as possible to the baseline design. Specific design parameters of interest were those for which very little data was available to determine their sensitivity on compressor performance. This paper describes the baseline compressor design and its experimental performance. A detailed definition and flow analysis of the baseline design test point (used as the basis for all subsequent design variations) are provided.

Aerodynamic Design Optimization of an Axial Flow Compressor Rotor

2002 ◽  
Author(s):  
Chan-Sol Ahn ◽  
Kwang-Yong Kim
Keyword(s):  
Design Optimization ◽  
Response Surface ◽  
Computing Time ◽  
Flow Analysis ◽  
Three Dimensional ◽  
Axial Flow ◽  
Navier Stokes ◽  
Transonic Compressor ◽  
Compressor Rotor ◽  
Design Variables

Design optimization of a transonic compressor rotor (NASA rotor 37) using the response surface method and three-dimensional Navier-Stokes analysis has been carried out in this work. The Baldwin-Lomax turbulence model was used in the flow analysis. Three design variables were selected to optimize the stacking line of the blade. Data points for response evaluations were selected by D-optimal design, and linear programming method was used for the optimization on the response surface. As a main result of the optimization, adiabatic efficiency was successfully improved. It was found that the optimization process provides reliable design of a turbomachinery blade with reasonable computing time.

Impact of Rotor Wakes on Steady-State Axial Compressor Performance

1996 ◽  
Author(s):  
P. Deregel ◽  
C. S. Tan
Keyword(s):  
Steady State ◽  
Static Pressure ◽  
Axial Compressor ◽  
Pressure Rise ◽  
Initial Step ◽  
Inviscid Flow ◽  
Causal Link ◽  
Design Parameters ◽  
Compressor Design ◽  
Compressor Performance

This paper addresses the causal link first described by Smith between the unsteady flow induced by the rotor wakes and the compressor steady-state performance. As an initial step, inviscid flow in a compressor stage is examined. First of a kind numerical simulations are carried out to show that if the rotor wakes are mixed out after (as opposed to before) the stator passage, the time-averaged overall static pressure rise is increased and the mixing loss is reduced. An analytical model is also presented and shown to agree with the numerical results; the model is then used to examine the parametric trends associated with compressor design parameters.

Aerodynamic Optimization Design of a Turbocharger Compressor Impeller

2012 ◽  
Vol 455-456 ◽  
pp. 389-394
Author(s):  
Chun Jun Ji ◽  
Xiao Qing Li
Keyword(s):  
Optimization Design ◽  
Flow Analysis ◽  
Internal Flow ◽  
Design Parameters ◽  
Trial And Error ◽  
Aerodynamic Optimization ◽  
Compressor Impeller ◽  
Final Design ◽  
Compressor Performance ◽  
Design Software

The flow inside the impeller and diffuser of a turbocharger compressor was analyzed numerically in this paper. The results indicate that the internal flow is disturbed and efficiency is low. There exists a big vortex in the diffuser which dissipates a large amount of energy. Based on the commercial design software, different design parameters were optimized by trial-and-error. Numerical flow analysis results of the final design show that the efficiency is increased by 6.26% and internal flow is improved greatly. It can be concluded that the meridian radius of the impeller flow path has great effect on the compressor performance.

Numerical and Experimental Analyses for the Aerodynamic Design of High Performance Counter-Rotating Axial Flow Fans

2009 ◽  
Author(s):  
Leesang Cho ◽  
Hyunmin Choi ◽  
Seawook Lee ◽  
Jinsoo Cho
Keyword(s):  
High Performance ◽  
Incidence Angle ◽  
Flow Analysis ◽  
Axial Flow ◽  
Flow Fields ◽  
Rotor Blades ◽  
Design Parameters ◽  
Aerodynamic Design ◽  
Axial Fan ◽  
Experimental Analyses

A study was done on the numerical and experimental analyses for the aerodynamic design of high performance of the counter rotating axial fan (CRF). Front rotor and rear rotor blades of a counter rotating axial fan are designed using the simplified meridional flow analysis method with the radial equilibrium equation and the free vortex design condition, according to design requirements. The through-flow fields and the aerodynamic characteristics of the designed rotor blades are analyzed by the matrix method and the frequency domain panel method. Fan performance curves are measured by following the standard fan testing method, KS B 6311. Three-dimensional flow fields in the CRF are analyzed by using the prism type five-hole probe. Performance characteristics of a counter-rotating axial flow fan are estimated for the variation of design parameters such as the hub to tip ratio, the taper ratio and the solidity. The effect of the hub to tip ratio on the fan efficiency is significant compared with the effects of other design parameters such as the solidity and the taper ratio. The fan efficiency is peak at the hub to tip ratio of 0.4, which is almost same point for the front rotor efficiency and rear rotor efficiency. The magnitudes of the meridional and relative velocities on the front and rear rotors are increased with the radial direction from hub to tip. This results in the reverse pressure gradient at the blade leading edges of both the front rotor and the rear rotor. Axial velocities of the CRF, which are measured by the prism type five-hole probe, are gradually increased at the mean radius due to the flow contraction effect. At the hub region, axial velocity is gradually decreased due to the flow separation and the hub vortex compare with design results. This result induces the increment of the incidence angle and the diffusion factor of the front rotor and the rear rotor.

scholarly journals Flow Analysis through Collector Well Laterals: A Case Study from Sonoma County Water Agency, California

Water ◽  
2018 ◽  
Vol 10 (12) ◽  
pp. 1848
Author(s):  
Matteo D’Alessio ◽  
John Lucio ◽  
Ernest Williams ◽  
James Warner ◽  
Donald Seymour ◽  
...  
Keyword(s):  
Optimal Design ◽  
Visual Inspection ◽  
Flow Analysis ◽  
Axial Flow ◽  
Design Parameters ◽  
Sonoma County ◽  
Russian River ◽  
North Western ◽  
Entrance Velocity

The Sonoma County Water Agency (SWCA) uses six radial collector wells along the Russian River west of Santa Rosa, to provide water for several municipalities and water districts in north-western California. Three collector wells (1, 2, and 6) are located in the Wohler area, and three collector wells (3, 4, and 5) are located in the Mirabel area. The objective of this paper is to highlight the performance of the three collector wells located in the Mirabel area since their construction. The 2015 investigation showed a lower performance of Collectors 3 and 4 compared to their original performances after construction in 1975, while the performance of Collector 5 was relatively stable since 1982. The potential change in capacity could be due to the increase in encrustation observed during the visual inspection of laterals in all three collector wells. Overall, the three collectors are still within the optimal design parameters (screen entrance velocity < 0.305 m min−1 and axial flow velocity of lateral screens < 1.524 m s−1).

Prediction of Compressor Performance in Rotating Stall

1978 ◽  
Vol 100 (1) ◽  
pp. 1-12 ◽  
Author(s):  
I. J. Day ◽  
E. M. Greitzer ◽  
N. A. Cumpsty
Keyword(s):  
Axial Velocity ◽  
Hysteresis Loops ◽  
Rotating Stall ◽  
Design Parameters ◽  
Heuristic Model ◽  
Axial Compressors ◽  
Large Hysteresis ◽  
Compressor Design ◽  
Compressor Performance ◽  
Design Value

A correlation is presented for predicting the performance characteristics of single and multistage axial compressors in rotating stall. The correlation is derived from new measurements of stalled compressor performance which have been obtained using a series of different compressor builds. In these experiments the compressor design parameters were systematically varied so that the influence of each could be clearly seen. It is shown that the stall cell blockage is an important parameter for correlating the flow regimes in stall, and hence the overall compressor performance. The resulting correlation, which has been developed based on a heuristic model of the stalled flow, can be applied to predict whether a given compressor will exhibit full-span or part-span stall, as well as the extent of the stall-unstall hysteresis loop. In particular, it is shown that as the number of stages and/or the design value of axial velocity parameter increases, the trend is toward both full-span stall and large hysteresis loops.

Axial Flow Compressor Design Optimization: Part II — Through-Flow Analysis

1989 ◽  
Author(s):  
Aristide Massardo ◽  
Antonio Satta ◽  
Martino Marini
Keyword(s):  
Design Optimization ◽  
Flow Analysis ◽  
Three Dimensional ◽  
Axial Flow ◽  
Axial Flow Compressor ◽  
Through Flow ◽  
Compressor Design ◽  
Type Calculation ◽  
A New Technique ◽  
Flow Compressor

A new technique is presented for the design optimization of an axial-flow compressor stage. The procedure allows for optimization of the complete radial distribution of the geometry since the variables, chosen to represent the three dimensional geometry of the stage, are coefficients of suitable polynomials. Evaluation of the objective function is obtained with a through-flow type calculation, which has acceptable speed and stability qualities. Some examples are given of the possibility to use the procedure both for redesign and, together with what was presented in Part I, for the complete design of axial-flow compressor stages.

scholarly journals 3-D Viscous Flow Analysis of an Axial Flow Pump Impeller

1997 ◽  
Vol 3 (3) ◽  
pp. 153-161 ◽  
Author(s):  
Steven M. Miner
Keyword(s):  
Stokes Equations ◽  
Flow Analysis ◽  
Axial Flow ◽  
Flow Coefficient ◽  
Navier Stokes ◽  
Design Parameters ◽  
Pump Impeller ◽  
Flow Angle ◽  
Axial Flow Pump ◽  
Flow Pump

A commercial CFD code is used to compute the flow field within the first stage impeller of a two stage axial flow pump. The code solves the 3-D Reynolds Averaged Navier Stokes equations in a rotating cylindrical coordinate system using a standardk−εturbulence model. Stage design parameters are, rotational speed 870 rpm, flow coefficientφ=0.12, head coefficientψ=0.06, and specific speed 2.86 (8070 US). Results from the study include relative and absolute velocities, flow angles, and static and total pressures. Comparison is made to measured data available for the same impeller at two planes, one upstream of the impeller and the other downstream. The comparisons are for circumferentially averaged results and include axial and tangential velocities, impeller exit flow angle, static pressure, and total pressure. Results of this study show that the computational results closely match the shapes and magnitudes of the measured profiles, indicating that CFD can be used to accurately predict performance.

A Multi-Objective Optimization for a Centrifugal Fan Impeller

2012 ◽  
Author(s):  
Yu-Tai Lee ◽  
Paul Cooper
Keyword(s):  
Flow Field ◽  
Performance Improvement ◽  
Flow Analysis ◽  
Design Parameters ◽  
Order Flow ◽  
Centrifugal Fan ◽  
Reduced Order ◽  
Fan Performance ◽  
Multi Objective ◽  
Design Variables

A reduced-order flow analysis method is developed to predict impeller flow field and impeller performance characteristics for a high-specific-speed centrifugal fan attached with a double-discharge volute. The method is validated by comparing its performance prediction for a baseline fan with measurements. The flow analysis calculation not only predicts impeller flow field, but also generates impeller configurations based on given impeller design parameters. A multi-objective genetic algorithm is also developed and coupled with the reduced-order flow analysis to perform a direct online search of the nominal (deterministic) optimum impeller design envelope. An existing fan serving as the baseline fan was reverse engineered to regenerate its geometry using the current method. The optimization calculations were used to explore design variables including blade inlet and outlet angles, shroud angle and blade leading-edge span as 2, 3 and 4-variable design calculations. The 2-variable prediction concludes that the fan is limited in its performance improvement if only the blade shape is changed, which agrees with early CFD prediction results of the baseline fan. Comparing 3 and 4-variable predictions with the 2-variable predictions, larger ranges of improvement in fan performance are feasible by only considering fan aerodynamics. Furthermore the conflicting nature of design variables with regard to the fan performance improvement is also demonstrated by the prediction results.

Sign in / Sign up

Export Citation Format

Share Document