• Title/Summary/Keyword: turbine

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An Experimental Study on Transient Heat Transfer Characteristics of Gas Turbine Cooled Vane by Using Liquid Crystal Thermography (가스터빈 냉각 베인에서 감온액정을 이용한 과도적 열전달 특성에 관한 실험적 연구)

  • Suh Nam-Kyu;Chang Tae-Hyun
    • Journal of Advanced Marine Engineering and Technology
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    • v.30 no.1
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    • pp.22-29
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    • 2006
  • Gas turbine engine among Principal internal combustion engines has been mainly applied as an aero and industrial Power plant. In order to increase its thermal efficiency. it has been raised their pressure ratio of compressor and the turbine inlet temperature. To operate above the limit temperature of turbine material, turbine nozzle vanes should be cooled. For this the cooling air is bled from the compressor section of 9as turbine. Meanwhile, to keep high thermal efficiency of 9as turbine, turbine vanes are to be cooled by using small cooling air Therefore, the complex cooling passages are requested to be designed and evaluated the effectiveness of vane cooling by measuring turbine vane temperature. But it is very difficult or impossible for us to measure local turbine temperatures at actual temperature When local heat transfer coefficients are known these can be calculated, therefore this study has been investigated on obtaining these coefficients of turbine vane at room temperature using TLC.

Design and CFD study of 360 W class wind turbine tree in accordance with environmental scenery (주위 경관을 고려한 360 W급 풍력터빈나무 설계 및 유동해석)

  • Ha, Min-Su;Jung, Won-Hyuk;Choi, Nak-Joon;Park, Young-Chul
    • Journal of Advanced Marine Engineering and Technology
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    • v.37 no.1
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    • pp.78-84
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    • 2013
  • The objective of this paper is to develop 360 W class wind turbine tree using a helical type wind turbine. The performance of 100 W class helical wind turbine which finished the conceptual design has been forecast through the CFD analysis. After performed the analysis of one wind turbine performance, four wind turbine have been installed at the structure of a tree type and then the change of a output data has been verified through the CFD analysis. In this study, the CFD results of a helical wind turbine tree have been shown by a velocity and pressure distribution. The result could obtain more than rated power 360 W through the CFD analysis.

Study on the Performance Analysis of an Axial-Type Turbine with Steam Injection (증기가 분사된 축류형 터빈의 성능해석에 관한 연구)

  • Cho, Soo-Yong;Kim, Soo-Yong
    • The KSFM Journal of Fluid Machinery
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    • v.4 no.4 s.13
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    • pp.28-36
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    • 2001
  • Performance analysis is conducted on an axial-type turbine which is used for fire extinction by injecting water or steam into the turbine. Loss models developed by Hacker and Okapuu are applied for predicting the performance of turbine. Pressure loss generated through a turbine is converted to the thermal efficiency, and thermal and gas properties are calculated within a turbine passage. Total-to-total efficiency, total-to-static efficiency, static temperature at the exit of turbine, output power, flow coefficient, blade loading coefficient, and expansion ratio are predicted with changing the amount of injected steam and the rotational speed. The 74 kW class gas turbine developed at KIMM is chosen for performance analysis. The 74 kW class turbine consists of 1 stage like a current developing gas turbine for fire extinction. Water or steam is injected at the end of combustor, and results show that efficiency and output power are dependent on the temperature of injected water or steam and the static temperature at the exit is decreased.

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Development of Radial Turbine for Air Cycle Refriger (공기 사이클 냉동기에 적응되는 반경 터빈의 개발)

  • Kwon, Gi-Hun;Lee, Ki-Ho;Kim, Jong-Seon
    • 유체기계공업학회:학술대회논문집
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    • 2001.11a
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    • pp.281-286
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    • 2001
  • The radial turbine has been successfully applied to the systems which request relatively small output compared with the axial turbine, and has low manufacturing cost due to it's small size and simple structure. Recently, the researches on the development and the efficiency maximization of the radial turbine are in progress corresponding with the trend toward miniaturization in turbo machinery and the development of small dispersed power generation systems. The radial turbine is to be applied to our turbo refrigerator of which engine speed is 26,000 rpm and turbine efficiency is $88\%$. Also, as a heat exchanger is accepted instead of a combustor in our turbo refrigerator, the design of radial turbine has been performed to be appropriate to the circumstance of low temperature air, not high temperature combustor gas, into the turbine inlet . This radial turbine is being developed in consideration with not only the aero-dynamic performance but also the simplification of manufacturing and integration, and the durability at operating condition. This paper refer to the performance evaluation about the radial turbine design by comparison with consulting from Russia and the our evaluation about various design factors which are considered in aero-dynamic design process.

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Numerical investigation of LP turbine-exhaust hood interaction in the steam turbine exhaust system (스팀터빈 Exhaust System에서 LP터빈과 Exhaust Hood 사이의 간섭에 대한 수치해석적 연구)

  • Im, Ji-Hyun;Joo, Won-Gu;Kim, Young-Sang;Im, Hong-Sik
    • 유체기계공업학회:학술대회논문집
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    • 2006.08a
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    • pp.291-294
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    • 2006
  • Exhaust system of steam turbines consists of an annular diffuser and a collector and connects the last stage turbine and the condenser. The system is used to transfer the turbine leaving kinetic energy to potential energy while guiding the flow from turbine exit plane to the downstream condenser. In the steam turbine exhaust system, distorted pressure profile is arisen by the nonaxisymmetric collector structure at the diffuser outlet, and this distorted pressure is propagated to the last stage LP turbine exit plane through the diffuser, then the last stage LP turbine experiences asymmetric back pressure. It is known that the pressure recovery performance of diffuser is strongly influenced by diffuser inflow condition. In this study, the effect of exhaust system due to the changing of inlet flow condition is observed by using CFD, and the interaction of last stage LP turbine and exhaust system is investigated by using actuator disk model as modeling of turbine blade row of exhaust hood inlet.

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Performance Analysis of a Steam Injected Gas Turbine Combined Heat and Power System Considering Turbine Blade Temperature Change (터빈 블레이드 온도 변화를 고려한 증기분사 가스터빈 열병합발전 시스템의 성능해석)

  • Kang, Soo Young;Kim, Jeong Ho;Kim, Tong Seop
    • The KSFM Journal of Fluid Machinery
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    • v.15 no.6
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    • pp.18-24
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    • 2012
  • This study simulated the operation of a steam injected gas turbine combined heat and power (CHP) system. A full off-design analysis was carried out to examine the change in the turbine blade temperature caused by steam injection. The prediction of turbine blade temperature was performed for the operating modes suggested in the previous study where the limitation of compressor surge margin reduction was analyzed in the steam injected gas turbine. It was found that both the fully injected and partially injected operations suggested in the previous study would cause the blade temperature to exceed that of the pure CHP operation and the under-firing operation would provide too low blade temperature. An optimal operation was proposed where both the turbine inlet temperature and the injection amount were modulated to keep both the reference turbine blade temperature and the minimum compressor surge margin. The modulation was intended to maintain a stable compressor operation and turbine life. It was shown that the optimal operation would provide a larger power output than the under-firing operation and a higher efficiency than the original partially injected operation.

Performance Test of the 30-ton Class Liquid Rocket Engine Turbopump Turbine (30톤급 액체로켓 엔진용 터보펌프 터빈 성능시험)

  • Jeong, Eun-Hwan;Park, Pyun-Goo;Kim, Jin-Han
    • Journal of the Korean Society of Propulsion Engineers
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    • v.12 no.1
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    • pp.1-6
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    • 2008
  • Performance test of the 30-ton class liquid rocket engine turbopump turbine has been conducted using high pressure cold air. Overall performance of the two kinds of turbine rotors - rotor with knife-edged L.E blades and with rounded L.E blades - has been measured for various rotational speed and turbine pressure ratio. The effect of rotational speed and turbine pressure ratio on the turbine axial force behavior also has been measured in parallel. Test results have revealed that the efficiency of knife edged L.E. turbine is a little bit higher than that of rounded L.E. turbine. The axial force of the turbine varied linearly with respect to rotational speed and its magnitude largely depended on turbine pressure ratio.

Performance Analysis of Turbofan Engine for Turbine Cooling Design (터빈 냉각설계를 위한 터보팬 엔진의 성능해석)

  • Kim, Chun-Taek;Rhee, Dong-Ho;Cha, Bong-Jun
    • The KSFM Journal of Fluid Machinery
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    • v.15 no.5
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    • pp.27-31
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    • 2012
  • Turbine inlet temperature is steadily increasing to achieve high specific thrust and efficiency of gas turbine engines. Turbine cooling technology is essential to increase turbine inlet temperature. For this study, a small or medium sized aircraft engine of 10,000 lbf class with the turbine inlet temperature of $1,400^{\circ}C$, the engine overall pressure ratio of 32.2, and the bypass ratio of 5 was set as the baseline model and its performance analysis was performed at the design point. The engine has the performance of 10,013 lbf thrust and the specific fuel consumption of 0.362 lbm/hr/lbf. The thrust and the specific fuel consumption of the baseline model were compared with those of similar class engines. Based on these results, the turbine design requirements were assigned. In addition, the parametric analysis of the engine, related to aerodynamic and cooling design of the high pressure turbine, was performed. Based on the baseline model engine, the influence of turbine inlet temperature, cooling flow ratio, and high pressure turbine efficiency variations on the engine performance was analyzed.

Technology Research on Gas Turbine Combustor Utilizing Melt-Growth Composite Ceramics

  • Konoshita, Yasuhiro;Hagari, Tomoko;Matsumotoi, Kiyoshi;Ogata, Hideki;Ishida, Katsuhiko
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2004.03a
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    • pp.854-860
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    • 2004
  • "Research and Development of Melt-Growth Composite (MGC) Ultra High Efficiency Gas Turbine System Technology" program has been started in JFY2001. The main objective of the program is to establish basic component technologies to apply MGC material to an efficient gas turbine system successfully. It is known that MGC material maintains its mechanical strength at room temperature up to about 2000 K, which is ideal for the high temperature gas turbine. The purposes of the present study are to develop the cooling structure of the gas turbine combustor liner where MGC material is applied as the heat shield panel, also to develop the low NOx combustion system for a 1970 K (1700 deg.C) class gas turbine combustor. To start with, basic heat transfer characteristics were investigated by one-dimensional calculation and heat transfer experiment for the cooling structure. Axially staged configuration and fuel preparation were investigated by CFD calculation and experiments for the low NOx combustor.

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Air Similarity Test for the Evaluation of Aerodynamic Performance of Steam Turbine (스팀터빈의 공력성능 평가를 위한 공기 상사실험)

  • Lim, Byeung-Jun;Lee, Eun-Seok;Yang, Soo-Seok;Lee, Ik-Hyoung;Kim, Young-Sang;Kwon, Gee-Bum
    • The KSFM Journal of Fluid Machinery
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    • v.7 no.5 s.26
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    • pp.29-35
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    • 2004
  • The turbine efficiency is an important factor in power plant, and accurate evaluation of steam turbine performance is the key issue in turbo machinery industry. The difficulty of evaluating the steam turbine performance due to its high steam temperature and pressure environment makes the most steam turbine tests to be replaced by air similarity test. This paper presents how to decide the similarity conditions of the steam turbine test and describes its limitations and assumptions. The test facility was developed and arranged to conduct an air similarity turbine performance test with various inlet pressure, temperature and mass flow rate. The eddy-current type dynamometer measures the turbine-generated shaft power and controls the rotating speed. Pressure ratio of turbine can be controled by back pressure control valve. To verify its test results, uncertainty analysis was performed and relative uncertainty of turbine efficiency was obtained.