• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2004년도 유체기계 연구개발 발표회 논문집
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• pp.109-115
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• 2004

The micro turbo generator is new portable power source based on the Brayton cycle, which consists of a compressor, a turbine, a generator, and a combustion chamber. In this paper, the thermodynamic analysis was performed to find the required condition for hundreds watts power in the micro turbo generator, and also the rotordynamic stability was predicted using the numerical analysis of air foil bearings which support the micro turbo generator. By experimental works, the rotordynamic stability of the micro turbo generator with foil bearings was verified. While various transient dynamic situation, the micro turbo generator had stable performances. From the result, it was demonstrated that air foil bearings could be adapted to the micro turbo generator as a excellent lubrication element.

• 제어로봇시스템학회논문지
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• 제10권3호
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• pp.286-293
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• 2004

This paper presents the result of a study on the starter control for a turbo generator. Because a starter in gear box type turbo-generator system is composed of gearbox and brush DC motor, it should be replaced with High Speed Generator(HSG)) in HSG type Turbo-generator. There-ore, it is necessary to design a new starting algorithm and starter. In gearbox type system, brush DC motor is rotated to the designed speed using low voltage-high current battery power. After brush DC motor speed is increased to several times by gearbox, gas turbine engine can be rotated to designed starting speed. If we implement a starter with High Speed Generator(HSG), it is necessary to drive high-speed generator to high-speed motor. High-speed generator with permanent magnet on rotor has a low leakage inductance fur driving high-speed rotation, and it is necessary high DC link voltage for inverter when High-speed generator is driven to high speed. This paper presents result of development of the boost converter for converting high voltage DC from low battery voltage and design of the inverter for controlling a high frequency current to be injected to motor winding. Also, we show performance of the designed starter by driving the turbo generator.

• 전자공학회논문지SC
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• 제40권6호
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• pp.87-94
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• 2003

본 연구에서는 고속 발전기를 고속의 가스 터빈 엔진에 직결 장착한 터보 제너레이터 시스템의 개발 연구결과를 보인다. 고속 발전기를 직결 장착한 터보 제너레이터 시스템은 터보 샤프트 발전 시스템에 비하여 무게, 크기, 윤활 시스템, 시스템의 복잡성 측면에서 많은 장점을 가지고 있다. 그러나 고속 회전체 시스템의 직접 운전에 따른 안정된 고속 제너레이터의 설계, 가스 터빈 엔진의 시동 시의 신뢰성 있는 점화를 위한 고속 모터 구동 알고리즘 구현, 고 주파수의 출력 전력을 상용 교류전력 혹은 필요한 직류 전력을 얻기 위한 전력 변환 장치의 설계를 요구한다.

• 한국분무공학회지
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• 제24권3호
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• pp.130-136
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• 2019

Spray visualization of a vaporizer fuel injection system of a micro turbo jet engine was experimentally studied. The fuel heating by combustion was simulated by the high pressure steam generator and combustor inlet air from the centrifugal compressor was simulated by compressed air stored in the high pressure air tank. Spray visualization was performed with single vaporizer, and then six vaporizers which are same number of micro turbojet engine were used. As a results, the spray characteristics of the vaporizer were understood with pressure difference of the combustor inlet air and the fuel supply pressure. Spray angles with three types of vaporizer configuration were measured. In the results, guide vane configuration has a wider spray angle than the straight tube and smooth curve tube with a swirler, so it is expected that the fuel will be effectively distributed inside the combustor flame tube.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2001년도 유체기계 연구개발 발표회 논문집
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• pp.361-366
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• 2001

A mim turbo-shaft engine of 50HP for UAV, which can be easily modified to turbo-prop and turbo-jet engine by sharing the core engine and has many applications to civilian demands and munitions, will be developed This kind of micro gas turbine engine has been developed mostly by the corporations which have special technology but are small in its scale. Especially, the gas turbine engine can be easily applied to other fields and developed by domestic technology, so that the sharing of technology is planed to realize through the cooperations with academies and research institutes. In this paper, the gas turbine engine, which has the compressor ratio of 3.8, the turbine inlet temperature of l180K and the engine speed higher than 100,000 rpm, is composed of centrifugal compressor, combustor, gas generator turbine, free power turbine and gear box. The competitiveness of the gas turbine engine can be obtained from minimizing its cost by the utilization of domestic infrastructure for the performance test and the decisive outsourcing.

• 한국유체기계학회 논문집
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• 제19권1호
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• pp.24-30
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• 2016

In this study, a 2W micro-gas turbine engine was designed using micro-electro-mechanical systems (MEMS) technology, and experimental investigations of its potential under actual combustion conditions were performed. A micro-gas turbine (MGT) contains a turbo-charger, combustor, and generator. Compressor and turbine blades, and generator coil were manufactured using MEMS technology. The shaft was supported by a precision computer numerical control (CNC) machined static air bearing, and a permanent magnet was attached to the end of the shaft for generation. A heat transfer analysis found that the cooling effect of the air bearing and compressor was sufficient to cover the combustor's high temperature, which was verified in an actual experiment. The generator performance test showed that it can generate 2W at design rotational speed. Prototype micro-gas turbine generated maximum 1 mW electric power and lasted up to 15 minutes.

• 한국윤활학회:학술대회논문집
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• 한국윤활학회 2004년도 학술대회지
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• pp.232-232
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• 2004

• 대한기계학회논문집B
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• 제39권2호
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• pp.153-159
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• 2015

본 연구에서는 MEMS기술을 적용한 2W급 초소형 가스터빈엔진의 개발과 실제 연소 환경에서의 발전 가능성을 해석적, 실험적으로 입증하였다. 초소형 가스터빈엔진은 터보차저, 연소기, 발전기로 이루어져 있다. 터보차저는 각각 직경 10mm와 9mm의 MEMS 공정 압축기와 터빈으로 구성되어 있으며 발전코일 또한 MEMS공정으로 설계되었다. 제작된 압축기와 터빈은 정밀 기계 가공된 축과 공기 베어링으로 지지되고 회전하며, 회전축 끝단에 영구자석을 설치하여 발전을 하게 된다. 공기 베어링과 압축기를 통한 냉각 효과를 해석하여 연소기에서 발생한 열을 충분히 차단할 수 있는 것으로 분석되었고, 이를 실험을 통해 검증하였다.