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Research Papers: Gas Turbines: Marine

# The Performance Evaluation With Diffuser Geometry Variations of the Centrifugal Compressor in a Marine Engine $(70MW)$ Turbocharger

[+] Author and Article Information
Hong-Won Kim

Hyundai Industrial Research Institute, Hyundai Heavy Industries Co., Ltd., 1, Jeonha-Dong, Dong-Gu, Ulsan 682-792, Koreakhw007@hhi.co.kr

Jong-II Park, Seung-Hyup Ryu, Seong-Wook Choi, Sang-Hak Ghal

Hyundai Industrial Research Institute, Hyundai Heavy Industries Co., Ltd., 1, Jeonha-Dong, Dong-Gu, Ulsan 682-792, Korea

J. Eng. Gas Turbines Power 131(1), 012201 (Oct 14, 2008) (7 pages) doi:10.1115/1.2967733 History: Received April 03, 2008; Revised April 07, 2008; Published October 14, 2008

## Abstract

An examination of the condition of the flow leaving the impeller exit kinetic energy often accounts for 30–50% of the shaft work input to the compressor stage; for energy efficiency, it is important to recover as much of this as possible. This is the function of the diffuser, which follows the impeller. Effective pressure recovery downstream of an impeller is very important in order to realize a centrifugal compressor with a high efficiency and a high pressure ratio, and an appropriate selection of a diffuser for a specific impeller is a critical step in order to develop the compressor accordingly. The purpose of this study is to investigate the sensitivity of how compressor performances change as the vaned diffuser geometry is varied. Three kinds of vaned diffusers were studied and compared with its results. The first vaned diffuser type is based on a modified NACA airfoil, the second is a channel diffuser, and the third is a conformal transformation of NACA 65-(4A10)06 airfoil. A mean-line prediction method was applied to investigate the performance and stability for three kinds of diffusers. Computational fluid dynamic (CFD) analyses and a detailed interior flow pattern study have been done. In this study, the off-design behavior of three different types of diffusers, given by the mean-line prediction, was investigated using CFD results and the NACA 65 diffuser geometry, which satisfies a wider operating range and has a higher pressure recovery than the others, was selected. The numerical results were compared with experimental data for validation and showed good agreement.

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## Figures

Figure 1

Studied three different diffuser models: (a) airfoil diffuser (A-type), (b) channel diffuser (B-type), and (c) NACA 65-(4A10)06 (C-type)

Figure 2

Flow field geometries

Figure 3

Airfoil geometries

Figure 4

Configuration for compressor modeling

Figure 5

Contours of the static pressure at midspan

Figure 6

Schematic view of the turbocharger test facilities

Figure 7

Flow rates at the stall and choke conditions

Figure 8

Pressure recovery factor at different diffusers

Figure 9

Total pressure ratio versus flow rate (only predicted data)

Figure 10

A-type total pressure ratio versus flow rate (predicted and measured data)

Figure 11

B-type total pressure ratio versus flow rate (predicted and measured data)

Figure 12

C-type total pressure ratio versus flow rate (predicted and measured data)

Figure 13

Pressure contours at midspan

Figure 14

Mach number contours at midspan

Figure 15

Pressure distribution at midspan

## Errata

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