• Title/Summary/Keyword: 터빈 입구온도 분포

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Numerical Study of Turbine Blade Surface Gas Temperature with Various RPM and Pyro Starter Pressure (파이로 시동기의 압력변화와 터빈 블레이드 회전수 변화에 따른 충동형 터빈 블레이드 입구의 가스온도 분포 해석)

  • Lee, In-Chul;Byun, Yong-Woo;Koo, Ja-Ye;Lee, Sang-Do;Kim, Kui-Soon;Moon, In-Sang;Lee, Soo-Young
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.94-97
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    • 2008
  • As the partial admission turbine has a intrinsically unsteady and three dimensional flow region, numerical calculation time of these study has been too long time. The numerical analysis for gas temperature of turbine blade surface has been performed to investigate development of temperature with various pyro start pressure. Computations have been carried out several turbine rotational speeds in the range from 0 to 16000 rpm and inlet conditions with 1423K, 7.2MPa. As a result, the more rotational speed and pyro starter pressure of turbine increased, the more turbine blade's temperature decreased. It is also found that flow field of turbine blade inlet area at pyro starter pressure of 5.75MPa and rotational speed of 12100 rpm formed surface temperature uniformly.

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A Study on Variations of the Low Cycle Fatigue Life of a High Pressure Turbine Nozzle Caused by Inlet Temperature Profiles and Installation Conditions (고압터빈 노즐에서 입구온도분포와 장착조건에 따른 저주기 피로 수명 영향에 대한 연구)

  • Huh, Jae Sung;Kang, Young Seok;Rhee, Dong Ho;Seo, Do Young
    • Transactions of the Korean Society of Mechanical Engineers A
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    • v.39 no.11
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    • pp.1145-1151
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    • 2015
  • High pressure components of a gas turbine engine must operate for a long life under severe conditions in order to maximize the performance and minimize the maintenance cost. Enhanced cooling design, thermal barrier coating techniques, and nickel-base superalloys have been applied for overcoming them and furthermore, material modeling, finite element analysis, statistical techniques, and etc. in design stage have been utilized widely. This article aims to evaluate the effects on the low cycle fatigue life of the high pressure turbine nozzle caused by different turbine inlet temperature profiles and installation conditions and to investigate the most favorable operating condition to the turbine nozzle. To achieve it, the structural analysis, which utilized the results of conjugate heat transfer analysis as loading boundary conditions, was performed and its results were the input for the assessment of low cycle fatigue life at several critical zones.

Aerodynamic Rig Test of Radial Turbine for APU (APU용 구심터빈의 공력리그시험)

  • Kang, Jeong-Seek;Lim, Byeung-Jun;Ahn, Iee-Ki
    • Transactions of the Korean Society of Mechanical Engineers B
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    • v.37 no.1
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    • pp.1-7
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    • 2013
  • An aerodynamic rig test of a radial turbine for an auxiliary power unit (APU) was performed at a high-temperature turbine test facility at the Korea Aerospace Research Institute. The pressure ratio, Mach number, and flow coefficient in the rig test are the same as those under normal engine operation conditions. The design pressure ratio is 3.096, design test speed is 34909 rpm, and turbine inlet temperature is $160^{\circ}C$. The turbine has airfoil-type nozzles, and the diameter of the turbine wheel is 175.74 mm. The turbine map is experimentally measured, and the detailed flow at the turbine inlet is measured. The pressure distribution in the nozzle at both the hub and the shroud sides and the pressure distribution along the shroud casing of the turbine wheel were measured, and this confirmed that the expansion process in the turbine wheel is acceptable.

Design Study of Engine Inlet Duct for Measurement Improvement of the Flow Properties on AIP (AIP면 유동측정 정확도 향상을 위한 가스터빈엔진 입구덕트 설계 연구)

  • Im, Ju Hyun;Kim, Sung Don;Kim, Yong Ryeon
    • Journal of the Korean Society of Propulsion Engineers
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    • v.21 no.3
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    • pp.49-55
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    • 2017
  • In this study, gas turbine engine inlet duct was designed to satisfy uniform flow at aerodynamic interface plane (AIP). Haack-series was selected as nose cone profile and duct outer radius($r_o$) was designed to satisfy to match with area change rate between the nose cone and outer duct wall by the 1-D sizing. The design object of the inlet duct wall profile which has the gradual area change rate was uniform Mach number in the core flow region and minimum boundary later thickness at the both inner nose wall and outer duct wall. The flow characteristics inside the inlet duct was evaluated using CFD. The static pressure distribution at the AIP showed uniform pattern within 0.16%. Based on Mach number profile, the boundary layer thickness was 2% of channel height. Kiel temperature rake location was decided less than 100 mm in front of nose cone where the Mach number is less than 0.1 in order to maximize the temperature probe recovery rate.

Thermodynamic Performance Characteristics of Transcritical Organic Rankine Cycle Depending on Source Temperature and Working Fluid (열원온도와 작동유체에 따른 초월임계 유기랭킨사이클의 열역학적 성능 특성)

  • Kim, Kyoung Hoon
    • Transactions of the Korean Society of Mechanical Engineers B
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    • v.41 no.11
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    • pp.699-707
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    • 2017
  • This study presents a comparative thermodynamic analysis of subcritical and transcritical organic Rankine cycles for the recovery of low-temperature heat sources considering nine substances as the working fluids. The effects of the turbine inlet pressure, source temperature, and working fluid on system performance were all investigated with respect to metrics such as the temperature distribution of the fluids and pinch point in the heat exchanger, mass flow rate, and net power production, as well as the thermal efficiency. Results show that as the turbine inlet pressure increases from the subcritical to the supercritical range, the mismatch between hot and cold streams in the heat exchanger decreases, and the net power production and thermal efficiency increase; however, the turbine size per unit power production decreases.

The Performance Evaluation of a Gas Turbine Combustor (가스터빈 연소기의 성능평가)

  • Ahn, Kook-Young;Kim, Han-Seok;Ahn, Jin-Hyuk;Pae, Hyoung-Su
    • Transactions of the Korean Society of Mechanical Engineers B
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    • v.24 no.10
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    • pp.1294-1299
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    • 2000
  • The combustion characteristics have been investigated to develop the 50 kW-class gas turbine combustor. The combustor design program was developed and applied to design this combustor. The combustion air which has the temperature of 45, 200, $300^{\circ}C$ were supplied to combustor for elucidating the effect of inlet air temperature on CO, NOx emissions and flame temperature. The exit temperature and NO were increased and CO was decreased with increasing inlet air temperature. Also, the effect of equivalence ratio was considered to verify the combustor performance. The emissions of CO and NO with inlet air temperature can be analyzed qualitatively by measuring the temperature inside the combustor. The combustion performance with fuel schedule was evaluated to get the informations of the starting and part loading process of gas turbine. The combustion was stable above the equivalence ratio of 0.18. The pattern factor which is the important parameter of combustor performance was satisfied with the design criterion. Consequently the combustor was proved to meet the performance goal required for the target gas turbine system.