Design and Performance Evaluation of a 10:1 Pressure Ratio Centrifugal Compressor Impeller

2010 ◽  
Author(s):  
Marco Vagani ◽  
Christopher D. Bolin
Keyword(s):  
Pressure Ratio ◽  
Design Procedure ◽  
Flow Simulation ◽  
Single Stage ◽  
Centrifugal Impeller ◽  
Centrifugal Compressors ◽  
Slip Factor ◽  
Auxiliary Power ◽  
Compressor Impeller ◽  
And Performance

Small gas turbine engines for advanced helicopter application and for auxiliary power have strong interest in centrifugal compressors, where high pressure ratios are required in a single stage. But there are few single stage centrifugal compressors capable of pressure-ratios around 10:1, due to stress considerations which severely limit the compressor’s safety, durability and life expectancy. In this work, design considerations are carried out for single stage centrifugal impeller with a pressure ratio of 10:1 and mass flow of 3 kg/s. One-D design procedure is used to compute the skeletal geometry of the impeller and to set a rough description of the flow at inlet and outlet. The theoretical head will be evaluated from Euler’s equation using slip factor. Determining the pressure ratio and efficiency of the impeller are achieved through evaluation of the slip factor and the internal and external losses. The losses evaluated in the impeller are those due to incidence, transonic inlet, skin friction, blade loading, shroud clearance, and recirculation. The design procedure adopted will be verified and compared with the well-documented Eckardt impellers and data. After one-D design, three-D geometry of the impeller is developed, and CFD flow simulation of the impeller flow is carried out to determine the performance of the impeller.

Gas Dynamic Designs of Centrifugal Compressors for Gas Industry

2015 ◽  
Author(s):  
Y. Galerkin ◽  
A. Rekstin ◽  
K. Soldatova ◽  
A. Drozdov
Keyword(s):  
High Efficiency ◽  
Pressure Ratio ◽  
Design Procedure ◽  
Flow Coefficient ◽  
Design Parameters ◽  
Centrifugal Compressors ◽  
Gas Industry ◽  
Design Point ◽  
Optimal Values ◽  
And Performance

Centrifugal compressors for gas industry consume huge amount of energy. As a rule, they are single-shaft, with two or more stages and with comparatively low pressure ratio. Compressors operate at low Mach numbers and high Reynolds numbers. Two design parameters influence mostly stage performances. Stage flow coefficient optimal values lie in range 0.060–0.11. Chosen number of stages establishes value of this coefficient if speed of a rotor rotation is fixed. Design loading factor optimal values are 0.42–0.52. It corresponds to high efficiency, shifts a surge limit far from a design point and makes power maximal in a design point. Some considerations about impeller and diffuser types are presented. Design procedure consists on application of the Universal modeling programs for main dimensions optimization and performance calculations. Q3D non-viscid velocity diagrams are analyzed for optimization of blade configuration. Samples of design are presented, 32 MW single-stage pipeline compressor stage with record efficiency included.

The influence of the trailing edge angle of the micro centrifugal impeller on the performance of the centrifugal compressor

2021 ◽  
pp. 1-15
Author(s):  
Xu Yu-dong ◽  
Li Cong ◽  
Lv Qiong-ying ◽  
Zhang Xin-ming ◽  
Mu Guo-zhen
Keyword(s):  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Centrifugal Impeller ◽  
Centrifugal Compressors ◽  
Trailing Edge ◽  
Sweep Angle ◽  
Impeller Blade ◽  
Bending Angle ◽  
Edge Angle ◽  
Isentropic Efficiency

In order to study the effect of the trailing edge sweep angle of the centrifugal impeller on the aerodynamic performance of the centrifugal compressor, 6 groups of centrifugal impellers with different bending angles and 5 groups of different inclination angles were designed to achieve different impeller blade trailing edge angle. The computational fluid dynamics (CFD) method was used to simulate and analyze the flow field of centrifugal compressors with different blade shapes under design conditions. The research results show that for transonic micro centrifugal compressors, changing the blade trailing edge sweep angle can improve the compressor’s isentropic efficiency and pressure ratio. The pressure ratio of the compressor shows a trend of increasing first and then decreasing with the increase of the blade bending angle. When the blade bending angle is 45°, the pressure ratio of the centrifugal compressor reaches a maximum of 1.69, and the isentropic efficiency is 67.3%. But changing the inclination angle of the blade trailing edge has little effect on the isentropic efficiency and pressure ratio. The sweep angle of blade trailing edge is an effective method to improve its isentropic efficiency and pressure ratio. This analysis method provides a reference for the rational selection of the blade trailing edge angle, and provides a reference for the design of micro centrifugal compressors under high Reynolds numbers.

scholarly journals Flow Simulation And Performance Analysis Of Centrifugal Compressor Using Cfd_Tool

2021 ◽  
Vol 23 (11) ◽  
pp. 693-703
Author(s):  
Tesfaye Barza ◽  
◽  
G. Lakshmikanth ◽  
Keyword(s):  
Performance Analysis ◽  
Pressure Distribution ◽  
Turbulence Model ◽  
Centrifugal Compressor ◽  
Flow Simulation ◽  
Internal Flow ◽  
Design System ◽  
Turbulent Fluid Flow ◽  
Compressor Impeller ◽  
And Performance

This paper is concerned the flow simulation and performance analysis of the Centrifugal Compressor Using CFD – Tool. The complex internal flow of centrifugal compressor can be well analyzed, and the unique design system needs to be developed. It should be early to use the interface and also flexible for input and output. A 3-D flow simulation of turbulent – fluid flow is presented to visualize the flow pattern in-terms of velocity, streamline and pressure distribution on the blade surface are graphically interpreted. The standard K- e turbulence model and the simple model algorithm were chosen for turbulence model and pressure distribution well determined. The simulation was steady Heat transfer and moving reference frame was used to consider the impeller interaction under high resolution. Furthermore, A computational Fluid Dynamics (CFD) 3-D simulation is done to analyze the impeller head and efficiency required of centrifugal compressor. The impeller is rotated for a constant revolution and mass flow rate, in this study initially the geometry of centrifugal compressor impeller is created by an ANSYS Vista CCD, and the Blade modeller done by Bladegen, Finally, CFD analysis was performed in ANSYS CFX using the ANSYS Turbo grid meshing tool. According to the analysis, as the number of impeller blades increases, so does the value of the head and power imparted, as well as the impeller’s efficiency.

Effect of Tip Clearance Flow on the Evaluation of Slip Factor for Micro Impellers

2012 ◽  
Author(s):  
Qianwei Sun ◽  
Yifang Gong ◽  
Qiushi Li
Keyword(s):  
Flow Behavior ◽  
Pressure Ratio ◽  
Extensive Study ◽  
Tip Clearance ◽  
Centrifugal Impeller ◽  
Tip Clearance Flow ◽  
Slip Factor ◽  
Clearance Flow ◽  
Actual Flow ◽  
The Comparative Study

It is quite evident that the slip factor is extremely important as it enables the energy transfer between the impeller and fluid to be calculated. Therefore, it has been the subject of extensive study so that the stagnation pressure ratio developed and the power absorbed by the compressor could be accurately predicted during design process. This paper describes a CFD investigation on tip clearance flow in micro centrifugal impeller. A study is performed to analyze the influence of comparatively low operating Reynolds numbers on tip clearance flow behavior. The flow structure within micro impeller affected by tip clearance flow is then discussed. The comparative study on shrouded and unshrouded impellers is carried out to evaluate the effect of tip clearance flow on slip factor prediction for micro impeller. The result stressed significant influence of tip clearance flow on micro impeller performance revealing the failure of conventional slip factor prediction model which proposed the demand for proper evaluation of slip factor based on actual flow field.

Performance of Three Vaned Radial Diffusers With Swirling Transonic Flow

1975 ◽  
Vol 97 (2) ◽  
pp. 155-160 ◽  
Author(s):  
S. Baghdadi ◽  
A. T. McDonald
Keyword(s):  
Transonic Flow ◽  
Static Pressure ◽  
Pressure Ratio ◽  
Motion Pictures ◽  
Back Pressure ◽  
Pressure Measurements ◽  
Performance Measurements ◽  
High Pressure Ratio ◽  
Compressor Impeller ◽  
And Performance

A unique vortex nozzle facility has been conceived and developed to simulate the exit flow from a high pressure ratio centrifugal compressor impeller. Visual studies and performance measurements have been made for three vane sets representing common designs for vaned radial diffusers. Motion pictures show the progression from choke through operating to surge conditions as the back pressure on the diffuser is increased. The films, together with total and static pressure measurements, indicate that surge is an instability triggered by flow separation in the vaneless or quasivaneless space ahead of the diffuser throat. A geometrical criterion for the onset of surge is identified. The surge-to-choke operating range of the three diffusers appears to be a function of the number of diffuser vanes only.

Design and Performance Prediction of Centrifugal Impellers

1996 ◽  
Vol 210 (6) ◽  
pp. 463-476 ◽  
Author(s):  
Y Wang ◽  
S Komori ◽  
Z Xu
Keyword(s):  
Boundary Layer ◽  
Performance Prediction ◽  
Three Dimensional ◽  
Axial Direction ◽  
Centrifugal Impeller ◽  
Angle Distribution ◽  
Simple Method ◽  
Viscous Loss ◽  
Compressor Impeller ◽  
And Performance

This study presents a simple method for designing the blade geometry of a centrifugal compressor impeller. In this method, instead of giving the mean swirl distribution on the meridional surface, the blade angle distribution is specified and the blade shape is derived, making it easier to perform the design. The quasi-three-dimensional potential flow field inside the impeller is obtained using the streamline curvature method, which solves the Euler equation along arbitrary quasi-orthogonals. The viscous effect is incorporated indirectly into the inverse design of the impeller via the simplified three-dimensional boundary layer calculation and the performance prediction. A three-dimensional centrifugal impeller was designed using this inviscid-viscous method and eventually manufactured. The newly designed impeller (B) and another impeller (A) designed previously were tested on a standard apparatus for model impellers. With the aid of three-hole probes and thermocouples, the flow parameters downstream of the exit of the impellers were measured along the axial direction of the impellers. A viscous loss model related to the boundary parameters is developed and used for the performance predictions of the impellers together with other loss models. From both the boundary layer analysis and the performance prediction, it is concluded that impeller B is superior to impeller A, which is in close accordance with the measurements.

scholarly journals The GTCP36-300, a Gas Turbine Auxiliary Power Unit for Advanced Technology Transport Aircraft

1986 ◽  
Author(s):  
L. M. Stohlgren ◽  
Lutz D. Werner
Keyword(s):  
Power Unit ◽  
State Of The Art ◽  
Pressure Ratio ◽  
Single Stage ◽  
Advanced Technology ◽  
Transport Aircraft ◽  
Auxiliary Power Unit ◽  
Cost Of Ownership ◽  
Auxiliary Power ◽  
Electrical Generator

The Garrett GTCP36-300 Series Auxiliary Power Unit is being developed for use on advanced technology transport aircraft in the 150-passenger size class. The first application will be the Airbus Industries A320 Aircraft. The APU uses a 6:1 pressure ratio, single-stage compressor and turbine, driving a single-stage load compressor and accessory gearbox. The 480 horsepower APU delivers compressed air to the aircraft pneumatic system and drives a customer furnished 90 kva, 24,000 rpm electrical generator. State-of-the-art aerodynamics, materials, and digital electronics are used to give the user-airlines an APU delivering maximum performance with minimum envelope, weight, and cost of ownership.

Effects of Asymmetric Radial Clearance on Performance of a Centrifugal Compressor

2017 ◽  
Vol 140 (5) ◽  
Author(s):  
Cheng Xu ◽  
Ryoichi S. Amano
Keyword(s):  
Pressure Ratio ◽  
Industrial Applications ◽  
Radial Clearance ◽  
Centrifugal Compressors ◽  
Numerical Studies ◽  
Compressor Design ◽  
Compressor Performance ◽  
Manufacturing Tolerances ◽  
And Performance ◽  
Design Pressure

The centrifugal compressors are widely used in industrial applications. The design, manufacturing, and installation are all critical for the compressor performance. Many studies have been carried out in the past to optimize the compressor performance during compressor design. The manufacturing tolerances and installation errors can cause the performance drop. There are many compressor performance distortions that are not fully understood due to manufacturing and facilities. In this paper, an asymmetrical radial clearance of the impeller due to manufacturing and installation is studied in detail for the performance impacts. The numerical studies and experiments indicated that the asymmetric radial clearance impacts the compressor flow field structure and performance. Experimental results suggested that the manufacturing and installation cause asymmetric radial clearance which decreased the compressor performance in whole operating range. The numerical analysis demonstrated that the impeller asymmetric clearance impacts performance near the design pressure ratio more than other pressure ratios. The numerical studies showed that the maximum clearance location of asymmetric clearance might impact the compressor performance. The proper asymmetricity of diffuser verse the volute may benefit the compressor performance. The excellent compressor performances for centrifugal compressors especially for small centrifugal compressors not only need to have a good aerodynamic design but also need to control manufacturing and installation carefully.

Design and Performance of a High-Pressure Ratio Turbocharger Compressor Part 1: Design Considerations

1993 ◽  
Vol 207 (2) ◽  
pp. 115-124 ◽  
Author(s):  
A Whitfield ◽  
M D C Doyle ◽  
M R Firth
Keyword(s):  
High Pressure ◽  
Peak Pressure ◽  
Pressure Ratio ◽  
Design Procedure ◽  
Design Requirement ◽  
High Pressure Ratio ◽  
Design Considerations ◽  
Compressor Design ◽  
Turbo Charger ◽  
And Performance

The compressor design requirement was for a pressure ratio of 3.6, with a peak pressure ratio of 4.3 at the maximum non-dimensional speed of the impeller of 1.66. Due to the stress-limited speed, an aluminium alloy impeller was specified, the impeller discharge blade backsweep had to be restricted and the application of prewhirl was considered from the outset as a means of extending the operating range. A non-dimensional conceptual design procedure, including the effect of inlet prewhirl, was applied to the design of three turbo- charger impellers. An impeller, designated A, was designed with the inclusion of 25° of prewhirl. A second impeller, designated B, was designed with zero prewhirl for comparison purposes, but was not manufactured. A third impeller, C, was manufactured through the modification of an existing design and the design study was applied to the assessment of this third design.

The Development of Centrifugal Compressor Impeller

2008 ◽  
Author(s):  
C. Xu ◽  
R. S. Amano
Keyword(s):  
Centrifugal Compressor ◽  
State Of The Art ◽  
Pressure Ratio ◽  
Structure Design ◽  
Centrifugal Compressors ◽  
Rotating Speed ◽  
Operating Range ◽  
High Pressure Ratio ◽  
Current State ◽  
Compressor Impeller

Impeller is one of the key components of industrial centrifugal compressors and turbochargers. Aerodynamic and structure designs of the impeller are critical to the success of the whole compressor stages. The requirements for efficiency and operating range of industrial centrifugal compressors and turbochargers have been increased dramatically compared with the situation in the past. The efficiency of newly developed low-pressure ratio centrifugal compressor has reached the possible level of the machine. However, the efficiency level of intermediate and high-pressure ratio machine still have gap between the current state-of-the-art and possible level. The challenge for centrifugal compressor design is to keep the efficiency level at state-of-the-art and increase the compressor operating range. Increase of the compressor operating range without sacrificing compressor peak efficiency is difficult to achieve. The product globalization requires one product design, which can be used in all locations. In some counties, due to the technology differences, electricity frequencies variations could be 10%. Turbocharger compressors work at different rotational speeds for majority of the time. The compressor impeller rotating speeds change in certain range. The impeller rotating speed variation makes the impeller structure design more challenging. In this study, a full-3D impeller was designed to optimize impeller aerodynamic performance and structure characteristics.

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