• 한국유체기계학회 논문집
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• 제18권4호
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• pp.30-35
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• 2015

This study analyzed the variations in the performance and operation of a 200 kW class micro gas turbine according to performance degradation of compressor and turbine. An in-house code, developed by the present authors and presented in the first part of these series of papers, were used for the analysis. The degradation of compressor and turbine were simulated by modifications in the their performance maps: mass flow rate, pressure ratio and efficiency were decreased from the reference values. Firstly, the variations in the operating conditions (air flow rate, pressure ratio) were predicted for the full load condition. Then, the same analysis were performed for a wide partial load operating range. The change in engine's performance (power output and efficiency) due to the component degradation was predicted. In addition, the change in the compressor surge margin, which is an important indicator for safe engine operation, was evaluated.

• 한국유체기계학회 논문집
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• 제10권4호
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• pp.29-38
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• 2007

In this study, flow structure in a two-stage centrifugal compressor for a turbo-chiller with the refrigerant, R134a, was numerically investigated at the design point of the compressor using a commercial code. Flow characteristics in the passages of impeller, diffuser and return channel were analyzed in detail including velocity vector, secondary flow, Mach number and pressure contours in blade spanwise and meridional plane for each stage. The estimation on the one-dimensional output from the preliminary design and three-dimensional shape of the impeller blade and the meridional shape of the return channel were performed through the flow analysis, while some numerical schemes and techniques including Multiple Frames of Reference technique, real gas property data and inlet boundary condition changes, which were used in CFD, were compared with their features. The results will be used as reference data for a new design of 3-D impeller shape to improve R134a compressor performance.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2001년도 제16회 학술발표회 논문초록집
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• pp.54-58
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• 2001

본 연구에서는 MAT(Moisture Air Turbine) 사이클이 압축기 입구에 미세한 물방울을 분무함에 따라, 가스터빈 엔진의 성능을 향상시킬 수 있음을 제시하였다. 혼합물이 상변화하는 동안의 압축기 일은 이론적으로 등 엔트로피 압축 일로 고려하였다. 여기서 습증발의 영향을 고려함에 따라 압축기 일이 감소함을 알 수 있었다. 성능해석 프로그램을 이용해서 1000, 1210, 1350 rps 조건에서, 압축기 유입공기에 대한 1.5% 의 물 분무시 사이클 모델 계산을 이용해서 각각 21.7%, 20.2%, 18.4%의 출력이 증가함을 확인하였다. 또한 효율도 압축기 일의 감소에 의해 개선되어짐을 확인하였다.

• 한국산학기술학회논문지
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• 제20권1호
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• pp.419-425
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• 2019

본 연구의 목적은 상용차 운행 시, 야간 및 운휴중에 냉방시스템을 운전하기 위하여서, 기계식과 전동식 압축기를 적용한 하이브리드 냉방시스템에 대한 냉방성능 특성을 분석하는 것이다. 기계식압축기는 170cc의 왕복동 형식이고, 전동식 압축기는 18cc 스크롤 형식이다. 전동식 압축기는 운휴시나 야간에 사용할 목적으로 적용되었기 때문에, 냉방용량은 기계식 압축기 대비 낮은 성능을 가지고 있다. 기계식 압축기를 사용하였을 경우, 6.0kW 수준의 냉방성능을 보이고 있고, 시스템 효율은 2.0이하의 결과를 가졌다. 반면, 전동식 압축기는 냉방성능 4.0kW수준, 시스템 효율은 3.5 수준을 가지고 있었다. 본 연구에서는 전동식 압축기는 냉방성능 4.0kW수준, 시스템 효율은 3.5 수준을 가지고 있었다. 기계식 압축기와 전동식 압축기를 운전조건에 따라서, 선택적으로 운전하는 것을 고려하였기 때문에, 운전모드가 바뀔 때의 시스템 특성을 분석하기 위하여서, 운전모드 변경에 대한 영향을 알아보았다. 운전모드가 변경될 때, 토출압력이 일시적으로 증가하는 경향을 보이는데, 안정적인 운전을 위하여서, 외기 부하 등을 고려한 운전모드 변경 로직에 대한 연구가 필요할 것으로 판단된다.

• 설비공학논문집
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• 제28권3호
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• pp.89-94
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• 2016

In this experimental study, the effects of top clearance on the performance of automotive a/c compressor were studied. Top clearance measuring device was also developed to ensure the reliability using vacuum conditions to secure constant control of top clearance without external environmental influence. Our results revealed that the improvements in compressor performance according to different top clearance values using the same compressor and same operator were about 4.12% at 800 rpm and about 7.8% at 2,000 rpm in 0.243~0.252 mm of top clearance compared to 0.431~0.456 mm of top clearance. To confirm the consistency in measuring top clearance affecting compressor performance, the top clearance measuring device was developed in this study using a vacuum pump. After performing reliable tests repeatedly, the distribution of measuring values under this device was within 0.99~1.83%, indicating that the constant test data in compressor performance was not affected by any other external environment.

• Tribology and Lubricants
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• 제17권6호
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• pp.426-434
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• 2001

The hermetic reciprocating compressor driven by the BLDC motor rotating with variable speeds, is modelled and analyzed for dynamic characteristics. The governing equations of piston, connecting rod and crank-shaft of the reciprocating compression mechanism and characteristics of driving torque of the motor are obtained. Dynamic behavior of the crankshaft supported on 2 journal bearings is analyzed considering compression load and eccentric unbalance for the 4 rotating speeds of crankshaft. And. reaction forces generated from oil film in the journal bearings are analyzed under transient condition using Reynolds' equation. To take into account the dynamic characteristics depending on the variable rotating speeds, comparison on the dynamic behavior of crank-shaft is made for the 4 operating modes of the compressor. Results show that the magnitude of crankshaft locioperating on the lower rotating speeds is more larger than the higher ones due to reduction of inertia force of the reciprocating piston.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2008년도 춘계학술대회논문집
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• pp.674-681
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• 2008

The main noise source of the BLDC rotary compressor for air conditioner was analyzed by using the measurement of noise and vibration, noise contour, and experimental modal analysis. The source is presumed to the mechanical resonance excited by the electromagnetic attractive force of the BLDC motor. To reduce the excessive noise of the BLDC rotary compressor due to the mechanical resonance, air-gap was enlarged. Its validation was conducted by the analysis of the electromagnetic attractive force which is generated by the BLDC motor. By enlarging the length of air-gap, the noise in the compressor and air conditioner was significantly improved by 2.5dB(A) and 4.5dB(A), respectively.

• 한국초전도저온공학회:학술대회논문집
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• 한국초전도저온공학회 2000년도 KIASC Conference 2000 / 2000년도 학술대회 논문집
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• pp.81-84
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• 2000

This paper presents operating process and design method on the linear compressor Stirling cryocooler for cooling infrared detector. The free piston-type Stirling cryocooler, which applies 1) the Stirling cycle for refrigeration, 2) linear motors for driving, 3) flexure bearings for support systems, and 4) fine gap for clearance seals, is the most suitable design for a mechanical cryocooler utilized in a night vision environment.

• 설비공학논문집
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• 제21권2호
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• pp.94-102
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• 2009

Conceptual design of scroll expander and scroll compressor for 10kW-class Stirling engine utilizing solar energy as heat source has been carried out to estimate the applicability of scroll mechanism for Stirling cycle. CO2 was chosen as working fluid, since it has lower expansion index and higher density among probably usable gases. Gas temperature at the expander inlet was set at $700^{\circ}C$, and that at the compressor inlet was at $40^{\circ}C$. System efficiency reached maximum at the pressure ratio of about 2.5, and the peak efficiency increased with increasing high side pressure. Due to safety concern, the pressure condition of 6 MPa/2.5 MPa was chosen as design condition. Orbiting scroll members for the expander and compressor were designed to have double-sided structure in order to reduce the overall scroll size and to cancel out the axial gas forces acting on the orbiting scroll base plate. By parametric study on the scroll profile, smaller possible size for the scroll members was obtained. With the shaft speed of 3600rpm, the shaft output of the designed scroll expander was calculated to be 45.4kW, while input power for the scroll compressor was 34.5kW, yielding 10.9kW for the output power of the Stirling engine. System efficiency was estimated to be about 7.3%, and overall efficiencies of the scroll expander and compressor were around 84.1% and 88.3%, respectively.

• 한국유체기계학회 논문집
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• 제14권6호
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• pp.96-101
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• 2011

Korea Aerospace Research Institute is performing 3 stage transonic axial compressor development program. This paper introduces design step of the compressor, the performance test results and its analysis. In the fore part of the paper, aerodynamic process of the 3 stage axial compressor is presented. To satisfy both of the mass flow and pressure rise, the compressor should rotate at a high rotational speed. Therefore the transonic flow field forms in the rotor stages and it is designed with a relatively high pressure rise per stage to satisfy its design target. The compressor stage consists of 3 stages, and the bulk pressure ratio is 2.5. The first stage is burdened with the highest pressure ratio and less pressure rises occur in the following stages. Also it is designed that tip Mach number of the first rotor row does not exceed 1.3, while the maximum relative Mach number in the rotor stage is between 1.3~1.4 to increase the compressor flow coefficient. The final design has been confirmed by iterating three dimensional CFD calculations to verify design target and some design intentions. In the latter part of the paper, its performance test processes and results are presented. The performance test result shows that the overall compressor performance targets; pressure ratio and efficiency are well achieved. The stator static pressure distributions show that the blade loading is gradually increasing from the downstream of the compressor.