• Title/Summary/Keyword: 터빈 동익

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Optimal Design for the Rotor Overlap of a Supersonic Impulse Turbine to Improve the Performance (초음속 충동형 터빈 성능개선을 위한 동익 오버랩 최적설계)

  • Cho, Jong-Jae;Seo, Jong-Chul;Kim, Kui-Soon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.325-330
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    • 2011
  • A rotor overlap technique was adapted to improve the performance of a axial turbine. The technique secured sufficient flow passage by additional height at the rotor tip and hub. especially in a supersonic turbine, the technique reduced the chance of chocking in the rotor passage, and made to be satisfied the design pressure ratio. However, the technique also made additional losses, like a pumping loss, expansion loss, etc. Therefore, a optimization technique was appled to maximize the improvement of the turbine performance. An approximate optimization method was used for the investigation to secure the computational efficiency. The design variables was shape factors of a rotor overlap. Results indicated that a significant improvement in turbine performance can be achieved through the optimization of the rotor overlap.

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Success Run Test for Reliability Demonstration of 1100℃ Gas Turbine Blades (1100℃급 가스터빈 동익의 무고장시험을 통한 HCF 신뢰성 평가)

  • Lee, Dooyoung;Goo, Jaeryang;Kim, Doosoo;Kim, Donghwan
    • KEPCO Journal on Electric Power and Energy
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    • v.3 no.2
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    • pp.107-111
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    • 2017
  • The reliability on high cycle fatigue damage mechanism for new blades manufactured by reverse-engineering is demonstrated by success-run test. Turbine blades always experience various dynamic loads in turbine operation, as well as being in resonance condition and forced by fluid-induced vibrations mostly during run-up/down, which may accumulate high cycle damage to the blades. The accidents caused by blade failure especially incur not only a lot of troubles to the machinery but also huge financial losses. Therefore it is necessary to verify the reliability of blades in advance for the safe use. The success run test for the reliability demonstration is designed and performed for the new blades using the technique known as resonant high cycle fatigue testing.

Performance Characteristics of Velocity Compound Supersonic Impulse Turbine with the Rotor Overlaps (속도 복합형 초음속 충동형 터빈의 동익 오버랩에 따른 성능특성)

  • Cho, Jong-Jae;Kim, Kui-Soon;Jeong, Eun-Hwan
    • Journal of the Korean Society of Propulsion Engineers
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    • v.15 no.1
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    • pp.19-28
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    • 2011
  • As a preview study, present research analysed the performance characteristics of a velocity compound supersonic impulse turbine with the rotor overlaps before adapting the overlap has the best turbine performance. This research was conducted for the turbine with square cross-section nozzles instead of axisymmetric nozzles and wrap around nozzles. Through 3-dimensional flow analysis for the turbine by a commercial flow analysis package, tip overlap case was more effective to improve the turbine performance than case hub overlap, and overlap case applied the hub and tip of the rotor had the largest improvement for the turbine performance in the cases. In case of overlap for the 2nd stage rotor, improvement of the turbine performance was not visibly large. Because, generated power in the 2nd stage is 22~23% of whole generated turbine power.

Numerical Study of the Supersonic Turbine Performance Variation with respect to the Rotor Profile Diameter (터빈 동익의 프로파일 정의 위치에 따른 초음속 터빈 성능변화에 대한 전산해석 연구)

  • Park, Pyun-Goo;Jeong, Eun-Hwan;Kim, Jin-Han
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2007.11a
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    • pp.297-301
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    • 2007
  • The blades of supersonic turbines with low aspect ratio are usually designed to have the same cross sectional shape in radial direction. The profile diameter definition of turbines may lead to produce unintended flow passage area variations resulting performance degradation. In this paper, the effects of profile diameter definition on the supersonic impulse turbine performance have been investigated. Computational results of three different profile diameters are compared. It has been found that flow passage area variation can be achieved according to designer's intention when blade profile is defined at rotor tip diameter. Furthermore, the turbine blade profile defined at rotor tip showed better performance than the others.

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Numerical Analysis for Flow in Two-Stage Supersonic Turbines (2단형 초음속 터빈의 유동에 대한 전산해석)

  • Cho, Jong-Jae;Seo, Jong-Chul;Kim, Sang-Jo;Kim, Kui-Soon;Jeong, Eun-Hwan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.05a
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    • pp.362-366
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    • 2010
  • Numerical Analysis of two-stage supersonic turbines were conducted, and the results were analyzed. $FLUENT^{TM}$ commercial flow analysis package was employed for the calculation of the turbine. Characteristics of the turbine performance were investigated according to the overlap height and existence of the shroud at the second rotor blade through the calculations.

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액체로켓용 터빈시스템 설계

  • Choi, Chang-Ho;Kim, Jin-Han;Yang, Soo-Seok;Lee, Dae-Sung
    • Aerospace Engineering and Technology
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    • v.1 no.1
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    • pp.163-172
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    • 2002
  • The turbine system composed of a nozzle and a rotor is used to drive turbopumps while gas passes through the nozzle, potential energy is converted to kinematic energy, which forces the rotor blades to spin. In this study, an aerodynamic design of a turbine system is investigated using compressible fluid dynamic theories with some pre-determined design requirements (i.e.,pressure ratio, rotational speed, required power etc.) obtained from a liquid rocket engine (L.R.E.) system design. For simplicity of a turbine system, impulse-type rotor blades for open type L.R.E. have been chosen. Usually, the open-type turbine system requires low mass flow rate compared to the close-type system. In this study, a partial admission nozzle is adopted to maximize the efficiency of the close-type turbine system. A design methodology of the a turbine system has been introduced. Especially, a partial admission nozzle has been designed by means of simple empirical correlations between efficiency and configuration of the nozzle. Finally, a turbine system design for a 10 ton thrust level of L.R.E is presented.

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Effects on the Performance of Velocity Compound Supersonic Impulse Turbine with the Rotor Overlaps (속도 복합형 초음속 충동형 터빈의 로터 블레이드 오버랩이 성능특성에 미치는 영향)

  • Cho, Jong-Jae;Kim, Kui-Soon;Jeong, Eun-Hwan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.11a
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    • pp.43-48
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    • 2010
  • Present study was conducted numerical analysis for velocity compound supersonic impulse turbine with the rotor overlaps, and the performance characteristics were analyzed through the numerical results. Tip overlap was more effective than hub overlap through the analysis. a case, overlap applied the hub and tip of the rotor, has the largest improvement for the turbine performance in parametric study cases. In case of overlap for the 2nd stage rotor, however, improvement of the turbine performance was not visibly large. Because, power generated in the 2nd stage was 22~23% of whole generated turbine power.

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A Study of the One-Stage Axial Turbine Performance with Various Axial Gap Distances between the Stator and Rotor (정.동익 축방향 간격에 따른 단단 축류터빈의 성능시험에 관한 연구)

  • Kim, Dong-Sik;Cho, Soo-Yong
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.30 no.4
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    • pp.99-105
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    • 2002
  • The performance test of an axial-type turbine is carried out with various axial gap distances between the stator and rotor. The turbine is operated at the low pressure and speed, and the degree of reaction is 0.373 at the mean radius. The axial-type turbine consists of ons-stage and 3-dimensional blades. The chord length of rotor is 28.2mm and mean diameter of turbine is 257.56mm. The power of turbo-blower for input power is 30kW and mass flow rate is $340m^3$/min at 290mmAq static-pressure. The RPM and output power are controlled by a dynamometer connected directly to the turbine shaft. The axial gap distances are changed from a quarter to three times of stator axial chord length, and performance curves are obtained with 9 different axial gaps. The efficiency varies about 8% of its peak value due to the variation of axial gap on the same non-dimensional mass flow rate and RPM, and experimental results show that the optimum axial gap is 1.6-1.9Cx.

Effect of Blade Angles on a Micro Axial-Type Turbine Operated in a Low Partial Admission Rate (부분분사 마이크로 축류형터빈에서의 익형각 효과에 관한 연구)

  • Cho, Soo-Yong;Cho, Bong-Soo;Cho, Chong-Hyun
    • Journal of the Korean Society of Propulsion Engineers
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    • v.11 no.4
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    • pp.10-18
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    • 2007
  • A tested micro axial-type turbine consists of two stages and its mean radius of rotor flow passage is 8.4 mm. This turbine could be applied to a driver of micro power system, and its rotational speed in the unloaded state reaches to 100,000 RPM. The performance of this system is sensitive depending on the blade angles of the rotor and stator because it is operated in a low partial admission rate, so a performance test is conducted through measuring the specific output power and the net specific output torque with various blade angles on the nozzle, stator and rotor. The experimental results show that the net specific output torque is varied by 15% by changing the rotor blade angle, and the optimal incidence angle is about $10.3^{\circ}$.

Optimal Design for the Rotor Overlap of a Supersonic Impulse Turbine to Improve the Performance (초음속 충동형 터빈 성능개선을 위한 동익 오버랩 최적설계)

  • Cho, Jongjae;Shin, Bong Gun;Kim, Kuisoon;Jeong, Eunhwan
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.1
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    • pp.33-41
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    • 2014
  • In a supersonic turbine, A rotor overlap technique reduced the chance of chocking in the rotor passage, and made the design pressure ratio satisfied. However, the technique also made additional losses, like a pumping loss, expansion loss, etc. Therefore, an approximate optimization technique was appled to find the optimal shape of overlap which maximizes the improvement of the turbine performance. The design variables were shape factors of a rotor overlap. An optimal design for rotor overlap reduces leakage mass flow rate at tip clearance by about 50% and increases about 4% of total-static efficiency compared with the base model. It was found that the most effective design variable is the tip overlap and that the hub overlap size is the lowest.