Numerical and experimental investigation of a compressor with active self-recirculation casing treatment for a wide operation range

Author:

Hu Liangjun1,Sun Harold2,Yi James2,Curtis Eric2,Zhang Jizhong3,Yang Ce1,Krivitziky Eric4

Affiliation:

1. School of Mechanical Engineering, Beijing Institute of Technology, Beijing, People’s Republic of China

2. Ford Motor Company, Dearborn, Michigan, USA

3. National Key Laboratory of Diesel Engine Turbocharging Technology, Datong, Shanxi, People’s Republic of China

4. Concepts NREC, White River Junction, Vermont, USA

Abstract

A turbocharger compressor with a wide flow range and a high efficiency is important to the application of advanced clean combustion technologies, such as homogeneous charge compression ignition and low-temperature combustion, in diesel engines. Self-recirculation casing treatment is one of the techniques that can extend the compressor surge margin without much efficiency penalty. The underlying physics of the self-recirculation casing treatment technology were investigated with computational fluid dyamics modeling and bench testing in this study. It is identified that, if the bleed slot of the self-recirculation casing treatment is located upstream of the impeller passage’s throat area, self-recirculation casing treatment improves the surge margin but the throat still limits the maximum flow capacity of the compressor. On the other hand, if the bleed slot of the self-recirculation casing treatment is located at the impeller passage’s throat area, the self-recirculation casing treatment improves the maximum flow capacity but results in a significant compressor efficiency penalty in the low-flow range. An active self-recirculation casing treatment design was proposed. The active self-recirculation casing treatment design extends the compressor flow capacity and improves the surge margin without an efficiency penalty through dual bleed slots with one upstream and the other downstream of the leading edge of the splitter blades. In the choke condition, the upstream bleed slot will be closed; near the surge condition, the downstream bleed slot will be closed. In the middle flow range, both bleed slots are closed. Both the numerical data and the bench testing results show that the maximum flow rate could be extended by about 15% and the surge margin by about 20% without an efficiency penalty. The mechanism of the performance improvement is also numerically studied.

Publisher

SAGE Publications

Subject

Mechanical Engineering,Aerospace Engineering

Reference13 articles.

1. Centrifugal Compressor Inlet Guide Vanes for Increased Surge Margin

2. Investigation of Vaned Diffusers as a Variable Geometry Device for Application to Turbocharger Compressors

3. Koch CC, Smith LH. Experimental evaluation of outer case blowing or bleeding of single axial flow compressor, Part II – performance of plain casing insert configuration with undistorted inlet flow and boundary layer trip. NASA Contractor Report CR-54588, National Aeronautics and Space Administration, Washington, DC, USA, 1968.

4. Bailey EE. Effects of grooved casing treatment on the flow range capability of a single stage axial-flow compressor. NASA Technical Memorandum TM X-2459, Lewis Research Center, National Aeronautics and Space Administration, Cleveland, Ohio, USA, 1972.

5. Prince DC, Wisler DC, Hilvers DE. Study of casing treatment stall margin improvement phenomena. NASA Contractor Report CR-134552, National Aeronautics and Space Administration, Washington, DC, USA, 1974.

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