• Title/Summary/Keyword: 원심 압축기

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Optimal Design of Impeller Shroud for Centrifugal Compressor Using Response Surface Method (반응표면법을 이용한 원심압축기 임펠러 쉬라우드 형상최적설계)

  • Kang, Hyun-Su;Hwang, In-Ju;Kim, Youn-Jea
    • The KSFM Journal of Fluid Machinery
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    • v.18 no.4
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    • pp.43-48
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    • 2015
  • In this study, a method for optimal design of impeller shroud for centrifugal compressor using response surface method (RSM) and multi-objective genetic algorithm (MOGA) was studied. Numerical simulation was conducted using ANSYS CFX with various configurations of shroud. Each of the design parameters was divided into 3 levels. Total 15 design points were planned by central composite design (CCD) method, which is one of the design of experiment (DOE) techniques. Response surfaces based on the results of DOE were used to find the optimal shape of impeller shroud for high aerodynamic performance. The whole process of optimization was conducted using ANSYS Design Xplorer (DX). Results showed that the isentropic efficiency, which is the main performance parameter of the centrifugal compressor, was increased 0.4% through the optimization.

Assessment of Slip Factor Models for Centrifugal Compressor at Off-Design Condition (탈설계 조건에서 원심압축기의 미끄럼 계수 모델들의 평가)

  • Yun, Seong-Ho;Baek, Je-Hyeon
    • Transactions of the Korean Society of Mechanical Engineers B
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    • v.25 no.11
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    • pp.1459-1466
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    • 2001
  • A slip factor is defined as an empirical factor, which should be multiplied to theoretical energy transfer to estimate real work input of a centrifugal compressor. During the last century, researchers have tried to develop simple empirical models to predict the slip factor. However most of these models have been developed based only on design point data. Furthermore flow is assumed inviscid. As a result, these models often fail to predict the correct slip factor at off-design condition. In this study, various models for the slip factor were analysed and compared with experimental and numerical data at off-design conditions. As a result of this study, Wiesner's and Paeng and Chung's models are shown to be applicable for radial impeller, but all the models are found to be inappropriate for backswept impellers.

Geometrical Effects of an Active Casing Treatment on Aerodynamic Performance of a Centrifugal Compressor (능동형 케이싱 트리트먼트의 형상 변화가 원심압축기의 공력성능에 미치는 영향)

  • Ma, Sang-Bum;Kim, Kwang-Yong
    • The KSFM Journal of Fluid Machinery
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    • v.19 no.4
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    • pp.5-12
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    • 2016
  • In this study, a parametric study on a cavity as casing treatment of a centrifugal compressor has been conducted using three-dimensional Reynolds-averaged Navier-Stokes equations with shear stress transport turbulence model. Two kinds of cavity were applied at choke and surge conditions, respectively, in this work. Inlet and outlet port widths, angle of outlet port, and length of cavity were chosen as the geometric parameters and investigated to find their effects on the aerodynamic performances such as adiabatic efficiency at design mass flow rate and stall margin of the centrifugal compressor. It was found that the aerodynamic performances of the centrifugal compressor were affected considerably by the four geometric parameters. The adiabatic efficiency was hardly changed by the geometric parameters, excepts for the angle of outlet port. With an increase in the angle of outlet port, the adiabatic efficiency and the stall margin decreased. The stall margin was more sensitive to the outlet port width than to the other geometric parameters. And, with a decrease in the outlet port width, the stall margin increased by 2% compared to that of the reference.

Aerodynamic Three Dimensional Geometry and Combustor Design for the Compressor of the Medium Speed Diesel Engine Turbocharger (중형 엔진 터보차져의 원심압축기에 관한 공력학적 3차원 형상 및 구동용 연소기 설계)

  • Ryu, Seung-Hyup;Ghal, Sang-Hak;Ha, Ji-Soo;Kim, Seung-Kuk;Kim, Hong-Won
    • The KSFM Journal of Fluid Machinery
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    • v.9 no.2 s.35
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    • pp.30-38
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    • 2006
  • An aerodynamic design for centrifugal compressor which was applied to medium speed diesel engine has been done. First of all, exact compressor specifications must be defined by accurate engine system matching. This matching program has been developed. Using the meanline prediction method, geometric design and performance curves for compressor were established and verified by comparing three dimensional viscous CFD results. The deviation at the design point was about 2.3%. Combustor has been designed and manufactured for the performance test of medium speed diesel engine turbocharger. Fuel nozzle of combustor was designed and its characteristics was analyzed by PIV and PDPA test equipment. Through these results, spray characteristics were studied and flow coefficient equation was deduced.

A Study on Steady-State Simulation and Experimental Test of Small Turbo Shaft Engine with Free Power Turbine (분리축 방식 소형 터보축 엔진의 정상상태 모사 및 실험연구)

  • 공창덕;기자영;고광웅
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 1997.11a
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    • pp.23-23
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    • 1997
  • 다목적으로 활용할 수 있는 분리축 방식의 터보축 엔진 개발을 위한 정상상태 해석 프로그램의 개발과 함께 동일 형식의 가스터빈엔진 시험장치를 이용한 실험을 통해 프로그램의 해석결과와 비교, 그 타당성을 입증하였다. 실험에 이용된 시험장치는 1단 원심형 압축기, Can형 연소기, 1단 Radial형 압축기 터빈 및 동력터빈으로 구성되어 있으며 출력은 3상 교류발전기를 통해 획득된다. 해석에 사용된 주요 구성품의 성능곡선은 시험장치 제작자로부터 획득된 자료를 이용하였으며, 경우에 따라 시험장치를 이용한 실험을 통하여 보정하였다. 시험장치를 이용한 실험결과를 프로그램 해석결과와 비교한 결과, 시험장치의 운용제한에 의해 실제 자동영역이 제한되기는 했으나, 압력비, 출력 등 주요 변수들에서 10% 미만의 오차를 보였다.

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Performance Analysis of a Centrifugal Compressor for HFC-134a with Variation of Diffuser Vane Angle (디퓨저 베인 설치각 변화에 따른 R134a 원심압축기 성능 분석)

  • Park, Han-Young;Shin, You-Hwan;Lee, Yoon-Pyo;Kim, Kwang-Ho;Chung, Jin-Taek;Cho, Yong-Hun;Kim, Jong-Seong
    • Proceedings of the KSME Conference
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    • 2007.05b
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    • pp.2823-2828
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    • 2007
  • Numerical simulation on the two-stage centrifugal compressor with Low Solidity Vaned Diffuser LSVD) for HFC-134a Turbo-chiller was performed using a commercial code. The comparative study with experimental results from other compressor was also investigated to testify the simulation schemes. The numerical analysis was separately simulated for each stage of the compressor and the effect of impeller-diffuser flow interaction was considered. Setting angle of the diffuser vane changed in the range of 15 deg. and the effects on its variation were discussed in detail including the flow analysis in the passage of the compressor. The vane setting angle obtained from the preliminary design was slightly adjusted to the optimal value by the performance enhancement in terms of pressure recovery and flow characteristics.

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The Design and Performance Test of a Centrifugal Compressor for HFC-134a Refrigerant (HFC-134a용 원심압축기의 성능시험 및 설계방안)

  • Sin, Jung-Kwan;Kim, Kyung-Hoon;Kang, Shin-Hyoung
    • Korean Journal of Air-Conditioning and Refrigeration Engineering
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    • v.22 no.3
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    • pp.139-148
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    • 2010
  • A centrifugal compressor for HFC-134a has been newly designed and developed. Flow analysis using commercial programs was used to evaluate performance and internal flow of the impeller, inlet guide vane and diffuser etc. The purpose of this study is to establish the design theory necessary to the development of HFC-134a centrifugal compressors and to supply basic data related to design by reviewing design values and experimental values through the performance test. The compressor for HFC-134a was also investigated experimentally to check compression performance. The calculated data coincide the test results of compressor. The data obtained in the present study are useful for design of HFC-134a centrifugal compressors.

Optimum Structural Design for Centrifugal Compressor Impeller (원심 압축기 임펠러의 최적 구조 설계)

  • Choi, Yoo Jin;Song, Jun Young;Kim, Seung Jo;Kang, Shin Hyung
    • The KSFM Journal of Fluid Machinery
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    • v.2 no.4 s.5
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    • pp.31-39
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    • 1999
  • Using basic shape and aerodynamic data for the designed impeller, basic structure analysis such as stress analysis and eigenvalue analysis was carried out. Also, we made the optimization program that was designed for optimum thickness within the adaptive stress limits. For the structural optimum theory, we used the BFGS(Broydon Fletcher Goldfarb Shanno) Method which is one of the searching methods. Through this program we managed optimization of the blade. For numerical simulation, we used the optimization program to compose Cyclic Module of NASTRAN and the Optimization Program which was implemented by C and fortran language.

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PERFORMANCE BY WIDTH CONTRACTION IN VANELESS DIFFUSER OF CENTRIFUGAL COMPRESSOR BY COMPUTATIONAL FLUID DYNAMICS (전산해석을 통한 원심압축기용 디퓨저의 폭변화에 따른 성능 연구)

  • Lee, S.C.;Lee, W.S.;Shin, Y.H.;Chung, J.T.
    • 한국전산유체공학회:학술대회논문집
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    • 2010.05a
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    • pp.136-141
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    • 2010
  • This study describes effects of width contraction in vaneless diffuser on the performance of centrifugal compressors using commercial CFD code. Numerical analysis for three different diffusers such as Parallel, half contraction, and full contraction was performed. The results show that the performance of the centrifugal compressor is improved through the use of the diffusers with width parallel in high flow rate. The width contraction of diffusers is influenced static pressure rises. Comparison with the experimental data shows agreement.

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Performance Evaluation and Numerical Calculation of Flows through a Vaned Diffuser for Centrifugal Compressor (원심압축기용 베인 디퓨저 내부유동의 수치해석 및 성능평가)

  • Choi, Yun-Ho;Kang, Shin-Hyoung;Lee, Jang-Chun
    • Transactions of the Korean Society of Mechanical Engineers B
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    • v.23 no.10
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    • pp.1296-1309
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    • 1999
  • A three dimensional compressible Navier-Stokes code is developed to analyze flowfields and performance of a vaned diffuser in a centrifugal compressor. It employs scalar implicit approximate factorization, finite volume formulation, second order upwind differencing and a two-equation $q-{\omega}$ turbulence model based on the integration to the wall. Pressure recovery and loss coefficients of a vaned diffuser are evaluated using a developed computer code. The simulated three dimensional flows show how through flow structure affects pressure recovery performance and loss coefficients of a vane for design and off-design inlet flow angles. Development of complex three dimensional flow over the inlet region and leading edge are very influential to the overall flow and performance.