• Title/Summary/Keyword: Micro turbine engine

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Experimental Study of the Micro Gas Turbine Engine Performance Test (마이크로 가스터빈 엔진 성능실험 연구)

  • Kim, Seungjae;Choi, Seongman;Rhee, Dongho
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.587-590
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    • 2017
  • Performance test was conducted by micro gas turbine engine. A small test rig was established for the performance measurement of the micro gas turbine engine. The performance was conducted by the Olympus HP engine. Engine inlet mass flow rate, static thrust, fuel consumption rate, air and gas temperature at the inlet of major components were measured. In the test results, we could well understand about the micro gas turbine engine performance characteristics.

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Development of a 50kW Micro Gas Turbine Engine (50kW 마이크로 가스터빈 개발)

  • Kim, Sooyong;Park, MooRyong;Choi, Bumseok;Ahn, Kookyoung;Choi, SangKyu
    • 유체기계공업학회:학술대회논문집
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    • 2002.12a
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    • pp.314-319
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    • 2002
  • Performance analysis and test of a 50kW micro gas turbine is carried out. The present study was initiated in 1996 by KIMM researchers to develope a 50kW class turbogenerator gas turbine engine for hybrid vehicle propulsion system. but with its low emission and compactness, it seemed that it can also be applied as a source of distributed power generation. In this study, general description of the KIMM's efforts to acquire performance test skills of the self-made 50kW micro gas turbine engine. At present, non-load performance test up to 615000 rpm was accomplished and is expected to make through 80,000 rpm by the end of year. Several revisions in design and manufacture were made during the course of experiments. The resulting outputs is thought to be valuable for the further refinement of the system for eventual commercialization of the product.

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Development of the Micro Gas Turbine Engine (마이크로 가스터빈 엔진 개발)

  • Kim, Seung-Woo;Kwon, Gii-Hun;Jang, Il-Hyeong
    • 유체기계공업학회:학술대회논문집
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    • 2001.11a
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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.

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Performance test of a micro-turbine jet engine (초소형 가스터빈 엔진 성능시험)

  • Shin, Young-Gy;Kim, Jong-Moon
    • Proceedings of the KSME Conference
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    • 2001.11b
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    • pp.788-793
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    • 2001
  • Test experience with a micro-turbine jet engine is introduced. The engine provides us with valuable opportunities to experience know-hows essential for engine development. It consists of a single radial compressor and a single stage turbine. Engine starting procedure has been established after many trials and errors. Static and dynamic engine performance tests were conducted. Static performance was found to be inferior to that advertised by the manufacturer. Further improvement is needed. Dynamic performance revealed that engine thrust overshoots unfavorably for the purpose of UAV control.

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Evaluation of Component Performance of a Commercial Micro Gas Turbine (상용 마이크로 가스터빈의 구성부 성능분석)

  • Lee, J.J.;Yun, J.E.;Kim, T.S.
    • 유체기계공업학회:학술대회논문집
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    • 2005.12a
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    • pp.331-337
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    • 2005
  • This study aims at evaluation of component performance of a commercial micro gas turbine by detailed measurements of various system parameters. A test facility to measure performance of a micro gas turbine was set up. Performance parameters such as turbine exit temperature, exhaust gas temperature, engine inlet temperature, compressor discharge pressure and fuel flow rate were measured. Variations in measured data and estimated performance parameters were analyzed. In addition to overall engine performance, component characteristic parameters including the turbine inlet temperature, the compressor efficiency, the turbine efficiency, the recuperator effectiveness were estimated. Behaviors of the estimated characteristic parameters with operating condition change were examined.

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Off-design Performance Analysis based on Experimental Data of a Micro Gas Turbine Engine (실험데이터 기반 마이크로 가스터빈엔진 탈 설계점 성능해석)

  • Kim, Seungjae;Choi, Seongman;Rhee, Dongho
    • Journal of the Korean Society of Propulsion Engineers
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    • v.22 no.6
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    • pp.64-71
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    • 2018
  • It is essential to understand the characteristics of gas turbine components in order to carry out an off-design analysis of a gas turbine engine. In this study, a micro gas turbine engine test system was constructed to understand the performance characteristics of gas turbines. The temperature and pressure in the flow path of the micro gas turbine was collected by measuring the engine spool speed, and a compressor map was constructed by using the experimental data. The exhaust gas was collected at the turbine outlet and the combustion efficiency was calculated. An off-design performance analysis at ground static was performed using GasTurb software by applying the compressor map and combustion efficiency obtained from the experimental data. Futhermore, we compared and evaluated the analysis results with engine operating data.

Development of a Integrated Modifiable Micro Gas Turbine Engine Test Rig using LabVIEW (LabVIEW를 이용한 소형 가스터빈 엔진의 통합 시험장치 개발)

  • Kang, Young-Soo;Kim, Do-Hun;Lee, In-Chul;Yoon, Sang-Hoon;Koo, Ja-Ye
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.05a
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    • pp.354-358
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    • 2009
  • Micro gas turbine engine is well known as a power plant of unmanned aerial vehicle and a small scale emergency generation system and also, it is significant as initial research of large gas turbine and educational purpose of gas turbine. Many sort of Micro gas turbine test set for education is produced by several manufacturers, but all of the engine control system of them is separated with data acquisition system; moreover, the engine control algorithms are inaccessible and related variables could not be collected. In this investigation, the Integrated Modifiable Test Rig which has modifiable engine start-up, drive and situational control logics is developed by LabVIEW with I/O devices and it provides wide experimental applicability to studies of dynamic characteristics of fuel system and combustion instability.

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Analysis of Design and Operation Performance of Micro Gas Turbine : Part 2 - Variations in Engine's Operation and Performance Caused by Performance Degradation of Compressor and Turbine (마이크로 가스터빈 설계 및 운전 성능 분석 : 제2부 - 압축기와 터빈 성능저하에 의한 엔진 운전 및 성능변화)

  • Kim, Jeong Ho;Kim, Min Jae;Kim, Tong Seop
    • The KSFM Journal of Fluid Machinery
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    • v.18 no.4
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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.

Preliminary Study of Hybrid Micro Gas Turbine Engine (하이브리드 타입 초소형 가스터빈엔진 개발 및 초도 시운전)

  • Seo, Junhyuk;Choi, Juchan;Kwon, Kilsung;Baek, Jehyun
    • The KSFM Journal of Fluid Machinery
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    • v.19 no.1
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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.

Performance Test of Metal 3D Printed Micro Gas Turbine Engine Combustor (초소형 가스터빈 엔진용 금속 3D 프린팅 연소기 성능 시험)

  • Kim, Jaiho;Kim, Hyungmo;Park, Poomin;Rhee, Dongho
    • Journal of the Korean Society of Propulsion Engineers
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    • v.23 no.6
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    • pp.51-58
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    • 2019
  • In this study, a set of performance tests on 3D-printed combustor components were carried out to investigate the performance of 3D-printed component and its feasibility for micro gas turbine engines. The test were conducted for four different equivalence ratios under two different engine operating conditions. The measurement results show that the tested combustor had a low total pressure loss coefficient and a uniform exit temperature distribution. However, the combustion efficiency values are less than 93.5% owing to the large amount of UHC and CO, which is considerably lower than a typical gas turbine engine combustor. The performance data obtained from the tests will be used for combustor performance improvements using 3D-printing technology.