scholarly journals The Performance Prediction and Demonstration of a Centrifugal Compressor for the Multiple Purpose Small Power Unit (MPSPU)

1989 ◽  
Author(s):  
Tsukasa Yoshinaka ◽  
R. G. Thompson ◽  
Jean Létourneau
Keyword(s):  
Power Unit ◽  
Centrifugal Compressor ◽  
Performance Prediction ◽  
Analytical Procedure ◽  
Pressure Ratio ◽  
Small Power ◽  
Subsequent Performance ◽  
Design Speed ◽  
Possible Cause ◽  
Performance Demonstration

This paper describes an analytical procedure for the prediction of the design point performance of a small centrifugal compressor. Results of a subsequent performance demonstration are presented. The geometry of the compressor was derived from an existing stage used in the PW200 engine, but rematched to 6:1 pressure ratio. Test data obtained from subsequent performance demonstration showed that the predicted performance had been achieved, but at 103% of design speed. A possible cause of this discrepancy is proposed.

scholarly journals Genetic Algorithm Optimization of the Volute Shape of a Centrifugal Compressor

2016 ◽  
Vol 2016 ◽  
pp. 1-13 ◽  
Author(s):  
Martin Heinrich ◽  
Rüdiger Schwarze
Keyword(s):  
Numerical Model ◽  
Centrifugal Compressor ◽  
Total Pressure ◽  
Pressure Ratio ◽  
Pressure Rise ◽  
Maximum Efficiency ◽  
Algorithm Optimization ◽  
Cross Sectional ◽  
Design Variables ◽  
Design Speed

A numerical model for the genetic optimization of the volute of a centrifugal compressor for light commercial vehicles is presented. The volute cross-sectional shape is represented by cubic B-splines and its control points are used as design variables. The goal of the global optimization is to maximize the average compressor isentropic efficiency and total pressure ratio at design speed and four operating points. The numerical model consists of a density-based solver in combination with the SSTk-ωturbulence model with rotation/curvature correction and the multiple reference frame approach. The initial validation shows a good agreement between the numerical model and test bench measurements. As a result of the optimization, the average total pressure rise and efficiency are increased by over1.0%compared to the initial designs of the optimization, while the maximum efficiency rise is nearly 2.5% atm˙corr=0.19 kg/s.

A Deep Insight Into the Transonic Flow of an Advanced Centrifugal Compressor Design

2019 ◽  
Author(s):  
D. Wittrock ◽  
M. Junker ◽  
M. Beversdorff ◽  
A. Peters ◽  
E. Nicke
Keyword(s):  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Three Dimensional ◽  
Leading Edge ◽  
Free Form ◽  
Numerical Verification ◽  
Deep Insight ◽  
Flow Solver ◽  
Compressor Design ◽  
Design Speed

Abstract In the last decades major improvements in transonic centrifugal compressor design have been achieved. The further exploration of design space is enabled by recent progress in structural mechanics and manufacturing. A challenging task of inducer design especially in terms of transonic inflow conditions is to provide a wide flow range and reduced losses due to a sufficient shock control. The use of so called multidisciplinary design optimization with an extensive amount of free parameters leads finally to complex designs. DLR’s latest Fast Rotating Centrifugal Compressor (SRV5) operates at a design speed of Mu2 = 1.72 and a total pressure ratio of 5.72. This compressor design is characterized by an S-shaped leading edge and free-form blade surfaces. Due to the complex design the key design features are difficult to explore. Therefore, non-intrusive measurements are conducted on the highly loaded SRV5. The Laser-2-Focus (L2F) approach that is used in addition with the Doppler Global Velocimetry (DGV) delivers a three dimensional velocity field. Besides the impeller inflow the ouflow is also part of the experimental and numerical verification of the advanced compressor design. Experimental results are compared with the numerical analysis of the compressor using DLR’s RANS Flow Solver TRACE. The deep insight of the inflow leads to a better understanding of the operating behavior of such impeller designs.

scholarly journals Technical Approach for a MultiPurpose Small Power Unit

1988 ◽  
Author(s):  
Robert G. Thompson ◽  
Sidney D. Parker
Keyword(s):  
Gas Turbine ◽  
Power Unit ◽  
Pressure Ratio ◽  
Technical Approach ◽  
Program Goal ◽  
Small Power ◽  
Turbine Engine ◽  
Component Efficiency ◽  
And Performance ◽  
Engine Components

This paper describes the technical approach used to select the engine configuration and performance cycle for a small gas turbine engine. The work was done during the preparation of a proposal to the U.S. Army for an advanced gas-turbine-based MultiPurpose Small Power Unit (MPSPU) in the 50–75 SHP class. Uprating to 100 hp (74.6 kw) with the fewest possible component changes was also desired and will be demonstrated. The proposal was successful, and the resultant engine offering, the T-100 MPSPU, is currently under development. The performance analyses used to quantify the T-100 MPSPU cycle were unique in that component efficiency correlations were used interactively when estimating performance at high levels of work (or pressure ratio per stage) with relatively small size components. The MPSPU program goal is to verify gas turbine technology advancements in small engine components, materials and design techniques that will lead to significant reductions in fuel consumption for this size class engine. Successful incorporation of these technologies will lead to significant savings in fuel usage and logistic requirements.

Evaluation of a High Hub/Tip Ratio Centrifugal Compressor

1970 ◽  
Vol 92 (3) ◽  
pp. 419-428 ◽  
Author(s):  
F. G. Groh ◽  
G. M. Wood ◽  
R. S. Kulp ◽  
D. P. Kenny
Keyword(s):  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Tip Clearance ◽  
Total Efficiency ◽  
Compressor Stage ◽  
Vaneless Diffuser ◽  
Centrifugal Stage ◽  
Design Speed ◽  
Multistage Axial Compressor

A centrifugal compressor stage with an unusually high inlet hub/tip ratio of 0.87 was designed for a pressure ratio of 2.0 at a corrected mass flow of 2.45 lb per sec. The geometry was selected so that the centrifugal stage could replace several of the last stages of a multistage axial compressor. The stage was tested with two diffuser schemes. One diffuser consisted of a series of drilled conical pipes, whereas the other employed multirow vaned cascades. Sea level aerodynamic tests of the compressor stage with each diffuser showed a peak total-to-total efficiency at design speed of 83.8 percent for the pipe diffuser and 82.9 percent for the vaned cascade diffuser. Additional tests were conducted with a vaneless diffuser to determine effects of impeller discharge tip clearance and inlet prewhirl on impeller performance.

A Deep Insight Into the Transonic Flow of an Advanced Centrifugal Compressor Design

2020 ◽  
Vol 142 (9) ◽  
Author(s):  
David Wittrock ◽  
Martin Junker ◽  
Manfred Beversdorff ◽  
Andreas Peters ◽  
Eberhard Nicke
Keyword(s):  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Three Dimensional ◽  
Leading Edge ◽  
Navier Stokes ◽  
Free Form ◽  
Numerical Verification ◽  
Deep Insight ◽  
Compressor Design ◽  
Design Speed

Abstract In the last decades, major improvements in transonic centrifugal compressor design have been achieved. The further exploration of design space is enabled by recent progress in structural mechanics and manufacturing. A challenging task of inducer design especially in terms of transonic inflow conditions is to provide a wide flow range and reduced losses due to a sufficient shock control. The use of so-called multidisciplinary design optimization with an extensive amount of free parameters leads finally to complex designs. DLR’s latest fast rotating centrifugal compressor (SRV5) operates at a design speed of Mu2 = 1.72 and a total pressure ratio of 5.72. This compressor design is characterized by an S-shaped leading edge and free-form blade surfaces. Due to the complex design, the key design features are difficult to explore. Therefore, nonintrusive measurements are conducted on the highly loaded SRV5. The laser-2-focus (L2F) approach that is used in addition with the doppler-global-velocimetry (DGV) delivers a three-dimensional velocity field. Besides the impeller inflow, the outflow is also part of the experimental and numerical verification of the advanced compressor design. Experimental results are compared with the numerical analysis of the compressor using DLR’s Reynolds-averaged Navier–Stokes Flow Solver TRACE. The deep insight of the inflow leads to a better understanding of the operating behavior of such impeller designs.

Improved High Pressure Ratio Centrifugal Compressor

2007 ◽  
Author(s):  
H. Krain ◽  
B. Hoffmann ◽  
K.-H. Rohne ◽  
G. Eisenlohr ◽  
F.-A. Richter
Keyword(s):  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Optical Measurements ◽  
Performance Measurements ◽  
Vaned Diffuser ◽  
Laser Measurements ◽  
High Pressure Ratio ◽  
Compressor Rotor ◽  
Design Speed ◽  
Internal Rotor

The paper describes the development and the experimental as well as theoretical investigation of a new transonic, high specific speed centrifugal compressor rotor of 6.2:1 pressure ratio. Performance measurement results, laser measurements and calculated 3D results are shown for the new rotor and are compared with the corresponding data of a same type predecessor rotor. A 2% gain in stage efficiency and a 0.2 bar increase in stage pressure ratio are found at design speed by performance measurements. With the help of optical measurements and 3D stage calculations it is shown that the flow at the exit of the new rotor is more uniform/homogeneous. The degree of uniformity increases with decreasing pressure ratio, i.e. in the compressor part load region. Deeper insight into the internal rotor and the vaned diffuser flow is obtained from the 3D stage calculations showing less flow separation in the new rotor but significant secondary flow in the small span diffuser. The investigations are indicating that a further improvement of stage performance seems to be possible by an additional optimization of the vaned diffuser.

Design and Experiment of Casing Treatment for a Centrifugal Compressor

2018 ◽  
Vol 0 (0) ◽  
Author(s):  
Wenwen Peng ◽  
Xueqi Zou ◽  
Sunde Qin
Keyword(s):  
Centrifugal Compressor ◽  
Experimental Validation ◽  
Pressure Ratio ◽  
Design Principles ◽  
Centrifugal Compressors ◽  
Casing Treatment ◽  
Light Duty ◽  
Design Speed ◽  
Stable Flow

Abstract Centrifugal compressors have been widely used in light-duty turboshaft engines and automotive turbochargers. One of the essential requirements for centrifugal compressors in these applications is to have adequate stable flow range. As the pressure ratio increases, the stable flow range drops dramatically, and this highlights the importance of stability improvement for centrifugal compressors. This paper first gives a brief review on the measures available for extending the stable flow range, and then focuses on the realization of self-recirculating casing treatment for a centrifugal compressor. The design principles of the casing treatment were introduced. Then the simulations were conducted to design and optimize the geometry of the casing treatment, and finally an optimum case was selected for experimental validation. The experiment results indicate that the designed casing treatment improve the stable flow range by about 5 percent at design speed, while keeping the efficiency almost identical.

Low Fidelity Design and Analysis Parametric Tool for General Centrifugal Compressors

2019 ◽  
Author(s):  
Sai Muppana ◽  
Kiran Siddappaji ◽  
Shaaban Abdallah ◽  
Mark Turner
Keyword(s):  
Centrifugal Compressor ◽  
Performance Prediction ◽  
Pressure Ratio ◽  
Design Stage ◽  
Analysis Tool ◽  
Preliminary Design ◽  
Centrifugal Compressors ◽  
Preliminary Design Stage ◽  
Successful Design ◽  
Definition Of

Abstract Performance prediction and blade generation in a preliminary design stage of centrifugal compressors is critical to have a successful design. In this paper, a one-dimensional meanline design and analysis tool has been developed for single-rotor and novel multi-rotor centrifugal impellers. Loss models used for performance prediction of single stage compressors have been extended to single hub multi-rotor compressors to evaluate isentropic efficiency and pressure ratio. Stage conditions like work ratio and stator turning angle are given as input parameters and the tool computes flow properties along the meanline and also, generates velocity triangles, streamlines, smooth definition of blade angles at different spanwise sections. The tool acts a preprocessor for Tblade3 which is an in-house 3D parametric blade geometry generator to create blades. A 0D tool has been developed for multi-rotor impellers to provide an estimate of work ratio. 0D coupled with 1D tool can provide a good preliminary design point. The process of 0D to blade generation has been automated enabling it to connect with high-fidelity analysis. The motivation to create this tool is to calculate flow angles, metal angles, velocity triangles, ease of parametric modification and reduce aero-design cycle time. This tool is modular which adds the flexibility of capability extension. The code is validated with DLR centrifugal compressor experimental data. The 1D tool is also used to calculate performance and blade angles for the novel single hub multi-rotor centrifugal compressor demonstrating the versatility of the low fidelity tool. The tool suite is written in Python and is open source https://github.com/msaisiddhartha/CIMdes.

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