Aerodesign and Performance Analysis of a Radial Transonic Impeller for a 9:1 Pressure Ratio Compressor

1993 ◽  
Vol 115 (3) ◽  
pp. 573-581 ◽  
Author(s):  
S. Colantuoni ◽  
A. Colella
Keyword(s):  
Pressure Ratio ◽  
Three Dimensional ◽  
Minimum Cost ◽  
Finite Volume Discretization ◽  
Cost Development ◽  
Air Intake ◽  
Time Marching ◽  
Overall Performance ◽  
And Performance ◽  
Euler Solver

The aerodynamic design of a centrifugal compressor for technologically advanced small aeroengines requires more and more the use of sophisticated computational tools in order to meet the goals successfully at minimum cost development. The objective of the present work is the description of the procedure adopted to design a transonic impeller having 1.31 relative Mach number at the inducer tip, 45 deg back-swept exit blade angle, and a tip speed of 636 m/s. The optimization of the blade shape has been done by analyzing the aerodynamic flowfield by extensive use of a quasi-three-dimensional code and a fully three-dimensional Euler solver based on a time-marching approach and a finite volume discretization. Testing has been done on the impeller-only configuration, using a compressor rig that simulates real engine hardware, i.e., having an S-shaped air-intake. The overall performance of the impeller is presented and discussed.

Aerodesign and Performance Analysis of a Radial Transonic Impeller for a 9:1 Pressure Ratio Compressor

1992 ◽  
Author(s):  
S. Colantuoni ◽  
A. Colella
Keyword(s):  
Pressure Ratio ◽  
Minimum Cost ◽  
Finite Volume Discretization ◽  
Blade Shape ◽  
Cost Development ◽  
Air Intake ◽  
Time Marching ◽  
Overall Performance ◽  
And Performance ◽  
Euler Solver

The aerodynamic design of a centrifugal compressor for technologically advanced small aeroengines requires more and more the use of sophisticated computational tools in order to meet the goals successfully at minimum cost development. The objective of the present work is the description of the procedure adopted to design a transonic impeller having 1.31 relative Mach number at the inducer tip, 45° back-swept exit blade angle, and a tip speed of 636 m/s. The optimization of the blade shape has been done analyzing the aerodynamic flowfield by extensive use of a quasi-3d code and a fully 3D Euler solver based on a time-marching approach and a finite volume discretization. Testing has been done on the impeller-only configuration, using a compressor rig that simulates a real engine hardware, i.e. having an S-shape air-intake. The overall performance of the impeller are presented and discussed.

Three-dimensional unsteady Navier—Stokes analysis of stator—rotor interaction in axial-flow turbines

2000 ◽  
Vol 214 (1) ◽  
pp. 13-22 ◽  
Author(s):  
L He
Keyword(s):  
Three Dimensional ◽  
Axial Flow ◽  
Navier Stokes ◽  
Time Stepping ◽  
Finite Volume Discretization ◽  
Dual Time Stepping ◽  
Passage Vortex ◽  
Speed Up ◽  
Time Marching ◽  
Grid Technique

A three-dimensional full Navier-Stokes method is developed and applied to calculations of unsteady flows through multiple blade rows in axial-flow turbomachinery. The solver adopts the cellcentred finite volume discretization and the four-stage Runge-Kutta time-marching scheme. Unsteady calculations are effectively accelerated by using a time-consistent multi-grid technique, resulting in a speed-up by a factor of 10–20 with adequate temporal accuracy. The computational efficiency and validity of the present multi-grid technique are illustrated by comparisons with the results of the conventional dual time-stepping scheme. Calculated unsteady pressures on blade surfaces for a turbine stage performances at different stator-rotor axial gaps reveals a marked three-dimensional behaviour of the interaction between incoming wakes and rotor passage-vortex structures. The time-averaged losses from unsteady calculations show a noticeable spanwise redistribution compared with the steady results. Two dimensional and three-dimensional calculations indicate opposite trends in stage efficiency variation when the stator—rotor gap is reduced.

Analysis on the Inhomogeneity of Air Intake and Retrofit Optimization of the Air Intake Pipe in the Engine T12V190

2014 ◽  
Vol 635-637 ◽  
pp. 7-12
Author(s):  
Xiao Jie Li ◽  
Zhong Yu Zhao ◽  
Yu Tian Pan
Keyword(s):  
Flow Field ◽  
Three Dimensional ◽  
Three Dimension ◽  
Intake Pipe ◽  
Performance Reduction ◽  
Cavity Structure ◽  
Air Intake ◽  
Dimensional Simulation ◽  
And Performance ◽  
Retrofit Design

Taking the air intake pipe in the engine as the target of the research, the software STAR-CDE is adopted to build a three-dimensional simulation model for the air intake pipe in the engine T12V190 with the aim to solve the problems of air input deficiency, Combustion deterioration and performance reduction of one cylinder caused by the non-uniformity. Moreover, the non-uniformity of the flux of air intake of the air intake pipe is mainly studied and analyzed through a calculation on the CFD of the inner flow field of the three dimension of the air intake pipe in the engine T12V190. In addition, a retrofit design with multiple schemes is made based on the cavity structure of the original mold for the air intake pipe. Finally, through a comparison among the three selected designs, a more feasible retrofit designing scheme and a designing thought on the air intake pipe in the engine with directional significance are got.

Numerical Analysis of Internal Flow Field in an Impeller with the Time Marching Method

2011 ◽  
Vol 94-96 ◽  
pp. 1476-1480
Author(s):  
Cai Hua Wang
Keyword(s):  
Flow Field ◽  
High Speed ◽  
Pressure Ratio ◽  
Three Dimensional ◽  
Internal Flow ◽  
Centrifugal Impeller ◽  
Three Dimensional Flow ◽  
Vector Distribution ◽  
Time Marching ◽  
Marching Method

Centrifugal compressors are power machineries used widely. Fully understanding of the complex three-dimensional flow field is very important to design higher pressure ratio, higher efficiency centrifugal compressor. In this paper, time marching method is adopted to solve the three-dimensional viscous N-S equations under the relative coordinate system. The internal flow field of the “full controllable vortex” high speed centrifugal impeller is analyzed and the medial velocity vector distribution and the development of the velocity of each section in the impeller are showed. From the figures, it can be seen that the “wake” phenomenon, such as Ecckart described, caused by the curvature, Coriolis force and the boundary layer is exist

Computation of Three-Dimensional Flow Fields Through Rotating Blade Rows and Comparison With Experiment

1982 ◽  
Vol 104 (2) ◽  
pp. 394-400 ◽  
Author(s):  
K. P. Sarathy
Keyword(s):  
Pressure Ratio ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Peak Efficiency ◽  
Three Dimensional Flow ◽  
Flow Solver ◽  
Rotating Blade ◽  
Blade Row ◽  
Time Marching ◽  
Design Speed

A three-dimensional inviscid time-marching calculation solving the unsteady Euler equations in a coordinate system rotating with the blade row has been developed, based on the Denton flow solver. This calculation was used to compute the flow field through the rotor of a transonic axial compressor and compared to measurements made with an advanced laser velocimeter at DFVLR. The comparison is made at design speed at pressure ratio corresponding to peak efficiency. Comparisons of the calculated and experimentally determined Mach number contours indicate excellent agreement in the entrance region where the viscous blockage effects are small. The methodology of the analysis is also described in this paper.

scholarly journals Study of Unsteady Airflow in Muffler and Air Box Equivalent Geometries

2013 ◽  
Author(s):  
Nicolas-Ivan Hatat ◽  
François Lormier ◽  
David Chalet ◽  
Pascal Chesse
Keyword(s):  
Internal Combustion Engines ◽  
Combustion Engine ◽  
Three Dimensional ◽  
Experimental Tests ◽  
Internal Combustion ◽  
Physical Models ◽  
One Dimensional ◽  
1D Modeling ◽  
Air Intake ◽  
And Performance

The Internal Combustion Engines (ICE) are inherently sources of the flow’s unsteadiness in the intake and exhaust ducts. Unsteady flow has a direct impact on the engine’s behavior and performance by influencing the filling and emptying of the cylinder. Air intake boxes as well as muffler geometries, which are very commonly used on the two-wheeled vehicles, have an impact on pressure levels and so, on air filling and performances levels. Thus, the purpose of this paper is to identify and analyze different typical geometries of these elements (air box and muffler) by comparing the test bench results with those obtained by 3D and 1D calculations. In this way, it is possible to establish a methodology for modeling the air box and muffler based on experimental tests and the development of 3D and then 1D model. In a beginning, studies consist in describing the geometry of the air box and muffler using a combination of tubes and simple volumes. During one-dimensional simulations, the gases properties in a volume must be calculated taking into account a method of filling and emptying. Under transient conditions, the pipe element is considered essentially as one-dimensional. The gas dynamic is described by a system of equations: the equations of continuity, momentum and energy. In the three-dimensional case, all tubes and volumes are meshed and solved using various physical models, equations and hypotheses that will be detailed subsequently. The study is performed on a shock tube bench. One of the main points is that this type of experimental test allows to test easily different pressure ratios, different geometries and to measure direct and inverse flow. In this way, the propagation of a shock wave is studied in our different geometries and is compared to the pressure signals obtained with 1D and 3D simulations. Once the 1D modeling is obtained, it must be validated in order to be applied in a simulation for Internal Combustion Engine. Validation will be done by direct comparison of results at each stage to ensure that the models and assumptions used in the calculations are correct.

Validation of Steady Average-Passage and Mixing Plane CFD Approaches for the Performance Prediction of a Modern Gas Turbine Multistage Axial Compressor

2008 ◽  
Author(s):  
Mahmoud L. Mansour ◽  
John Gunaraj ◽  
Shraman Goswami
Keyword(s):  
Flow Field ◽  
Turbulence Modeling ◽  
Pressure Ratio ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Turbulence Models ◽  
Leading Edge ◽  
Sensitivity Study ◽  
Leakage Flow ◽  
Overall Performance

This paper summarizes the results of a validation and calibration study for two modern Computational Fluid Dynamics programs that are capable of modeling multistage axial compressors in a multi-blade row environment. The validation test case is a modern 4-stage high pressure ratio axial compressor designed and tested by Honeywell Aerospace in the late 90’s. The two CFD programs employ two different techniques for simulating the steady three-dimensional viscous flow field in a multistage/multiblade row turbo-machine. The first code, APNASA, was developed by NASA Glenn Research Center “GRC” and applies the approach by Adamczyk [1] for solving the average-passage equations which is a time and passage-averaged version of the Reynolds Averaged Navier Stokes (RANS) equations. The second CFD code is commercially marketed by ANSYS-CFX and applies a much simpler approach, known as the mixing-plane model, for combining the relative and the stationary frames of reference in a single steady 3D viscous simulation. Results from the two CFD programs are compared against the tested compressor’s overall performance data and against measured flow profiles at the leading edge of the fourth stator. The paper also presents a turbulence modeling sensitivity study aimed at documenting the sensitivity of the prediction of the flow field of such compressors to use of different turbulence closures such as the standard K-ε model, the Wilcox K-ω model and the Shear-Stress-Transport K-ω/SST turbulence model. The paper also presents results that demonstrate the CFD prediction sensitivity to modeling the compressor’s hub leakages from the inner-banded stator cavities. Comparison to the test data, using the K-ε turbulence closure, show that APNASA provides better accuracy in predicting the absolute levels of the performance characteristics. The presented results also show that better predictions by CFX can be obtained using the K-ω and the SST turbulence models. Modeling of the hub leakage flow was found to have significant and more than expected impact on the compressor predicted overall performance. The authors recommend further validation and evaluation for the modeling of the hub leakage flow to ensure realistic predictions for turbo-machinery performance.

An Investigation of a Highly Loaded Transonic Turbine Stage With Compound Leaned Vanes

1986 ◽  
Vol 108 (2) ◽  
pp. 265-269 ◽  
Author(s):  
Jing Shi ◽  
Jianyuan Han ◽  
Shiying Zhou ◽  
Mingfu Zhu ◽  
Yaoko Zhang ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Velocity Profile ◽  
Three Dimensional ◽  
Turbine Stage ◽  
Time Marching ◽  
Overall Performance ◽  
Transonic Turbine ◽  
Volume Method ◽  
Stage Efficiency ◽  
Highly Loaded

An investigation was made to compare the performance of a highly loaded transonic turbine stage with and without compound leaned vanes. In both cases, velocity distribution along the vane surfaces was calculated from a full three-dimensional time-marching finite volume method. Nozzles were tested in a wind tunnel. Through rig tests, velocity profile at the stage exit was measured and the stage overall performance obtained. Performance in both tip and hub regions was improved by using the compound leaned vanes so that the stage efficiency increased by approximately 1 percent. The improvement is particularly remarkable at off-design points.

Conceptual Design and Performance Analysis of SOFC/MGT Hybrid Distributed Energy System

2011 ◽  
Author(s):  
Zheng Dang ◽  
Hua Zhao ◽  
Guang Xi
Keyword(s):  
Performance Analysis ◽  
Hybrid System ◽  
Pressure Ratio ◽  
Energy System ◽  
Inlet Temperature ◽  
Distributed Energy ◽  
Reaction Heat ◽  
Distributed Energy System ◽  
Overall Performance ◽  
And Performance

A numerical model has been developed for the performance analysis of SOFC/MGT hybrid systems with pre-reforming of natural gas, in which a quasi-2 dimensional model has been built up to simulate the cell electrochemical reaction, heat and mass transfer within tubular SOFC. The developed model can be used not only to predict the overall performance of the SOFC/MGT hybrid system but also to reveal the nonuniform temperature distribution within SOFC unit. The effects of turbine inlet temperature (TIT) and pressure ratio (PR) to the performance of the hybrid system have been investigated. The results show that selecting smaller TIT or PR value will lead to relative higher system efficiency and lower CO2 emission ratio; however this will raise the risk to destroy SOFC beyond the limitation temperature of electrolyte.

Investigation on the Prestage of a Water Hydraulic Jet Pipe Servo Valve Based on CFD

2012 ◽  
Vol 197 ◽  
pp. 144-148 ◽  
Author(s):  
Xin Hua Wang ◽  
Zhi Jie Li ◽  
Shu Wen Sun ◽  
Gang Zheng
Keyword(s):  
Pressure Ratio ◽  
Servo Valve ◽  
Offset Distance ◽  
Computer Emulation ◽  
Nozzle Hole ◽  
Overall Performance ◽  
Water Hydraulic ◽  
Structure Dimension ◽  
And Performance ◽  
Analysis Models

In a water hydraulic jet pipe servo valve, the overall performance of the valve is directly influenced by the structure dimension of the receiver and the prestage— jet pipe amplifier. This paper deals with the influence rules of the structure dimension parameters and performance parameters on the buildup pressure in the two receiving holes, including the vertical clearance between the nozzle and the receiver, the diameter of the nozzle hole, the diameter of the receiving orifice, and the nozzle offset distance. The best combination of structure size is finally obtained by using numerical simulation, computer emulation and experiment analysis methods. Then build up the finite volume analysis models about the pressure field and the speed field of the jet pipe amplifier. Through analyzing the characteristics of the flow field, a mathematics relation between the jet nozzle offset and the pressure ratio inside the two receiver holes is established, which reveals the energy distribution and conversion mechanism. The conclusion could be an important reference for the design and research of jet pipe servo valve.

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