• Title/Summary/Keyword: Supersonic Impulse Turbine

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Experimental Study of the Velocity Compound Turbine in Turbopump (터보펌프의 속도복식 터빈에 대한 성능 연구)

  • Lee, Hang-Gi;Jung, Eun-Hwan;Park, Pyun-Gu;Kim, Jin-Han
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.38-44
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    • 2011
  • The performance experiment was tested for the velocity compound turbine of turbopump which was the main part of 75 ton class liquid rocket engine. The seal is installed between the 1st rotor and the reversing vane to reduce the leakage flow. The turbine outlet pressure of the velocity compound turbine by changing the rotating speed was compared with that of baseline turbine with single rotor including the effect on the total performance.

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An Investigation into the Three-dimensional Design of Turbine Rotor Blade for Turbopump (터보펌프용 터빈 로터 블레이드의 3차원 설계 연구)

  • Jeong, Sooin;Choi, Byoungik;Lee, Hanggi;Kim, Kuisoon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.1038-1044
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    • 2017
  • We are working on improving the performance by applying the three-dimensional design element to the rotor blades of high pressure supersonic impulse turbine that drives turbo pump of liquid rocket engine. In this paper, based on the shape of a rotor blade of a turbopump turbine designed in the past, a three-dimensional shape is applied to a rotor blade through a stacking line change such as sweep and dihedral. After performing the flow analysis, the changes in the turbine performance characteristics for each design element were carefully examined and the results were summarized.

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A Study on the Blade Load Measurement of Partial-admission Turbine Cascade (충동형 터빈 캐스케이드의 깃 하중 측정에 관한 연구)

  • Lim, Dong-Hwa;Jang, Jin-Man;Lee, Eun-Seok;Kim, Jin-Han;Choi, Jong-Soo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.35 no.2
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    • pp.143-148
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    • 2007
  • An impulse turbine, which is a main component of a liquid rocket engine, needs to be a small size with light weight and generate large power. Since the impulse turbine is being operated under complicated supersonic conditions, flow analysis and performance prediction largely depend on CFD technique. In order to increase the reliability of the prediction code, however, it often requires an experimental data to compare. In this research a rotating turbine rotor with multiple blades is simulated with a two-dimensional stationary cascade to check the effect of major flow parameters. Mach number is measured at nozzle exit by using a pitot tube and the blade thrust was also measured with a load cell. The measured thrust coefficient and the power are compared well with the designed conditions, which proves the design procedures are properly taken.

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.

Experimental Investigation of Turbopump Turbine : Turbine Performance and Effect of Nozzle-Rotor Clearance (터보펌프 터빈의 성능 및 노즐-로터 간극의 영향에 대한 실험적 고찰)

  • Jeong Eun-Hwan;Kang Sang-Hun;Shin Dong-Yoon;Park Pyu-Goo;Kim Jin-Han
    • Journal of the Korean Society of Propulsion Engineers
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    • v.10 no.2
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    • pp.78-86
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    • 2006
  • This paper presents the performance test result of the 30-ton class turbopump turbine. Test has been conducted using high pressure cold air, The turbine overall performance has been measured for various pressure ratio and rotational speed settings. The nozzle-rotor clearance effect on turbine performance also has been tested for the four kinds of the nozzle-rotor clearance values. We found that turbine efficiency rated 51.1% at its design velocity ratio and pressure ratio of 13.5. We also found that turbine efficiency can be increased by 3.5% for approximately 1mm decrement of the nozzle-rotor clearance from its nominal value.

Design of Velocity and Pressure Compounded Impulse Turbine (속도 및 압력 복합형 충동 터빈 설계)

  • Jeong, Eun-Hwan;Park, Pyun-Goo;Kim, Jin-Han
    • Aerospace Engineering and Technology
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    • v.9 no.2
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    • pp.185-192
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    • 2010
  • Design of velocity-compounded turbine for 75ton class LRE turbopump application and pressure compounded turbine for 30ton class LRE turbopump has been performed. 1D calculation and CFD analysis were conducted in determining blade and flow passage shape of velocity compounded turbine iteratively. Finally, 23.1% improved specific power and 5% reduced weight turbine to the original design was developed. In case of pressure-compounded supersonic turbine design, rotational speed was increased by 50% and the effect of carryover ratio, 2nd nozzle installation angle, leakage flow of 2nd nozzle, and work sharing factor was studied. Final 1D design resulted 36% increased specific power and 51% reduced weight comparing to the original single-row impulse turbine. It is anticipated that nozzle flow path design will be very important for the accomplishment of expected performance of pressure-compounded turbine and nozzle shape optimization will be conducted through the CFD analysis.

Numerical Flow Analysis of a Supersonic Impulse Turbine with Nozzles and Rotor Blades (노즐과 로터가 장착된 초음속 충동형 터빈의 전산유동해석)

  • Park, Pyun-Goo;Lee, Eun-Seok;Jeong, Eun-Hwan;Kim, Jin-Han
    • The KSFM Journal of Fluid Machinery
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    • v.10 no.1 s.40
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    • pp.26-33
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    • 2007
  • Four design candidates for a partial admission turbine have been chosen from a preliminary design process. Their performance were estimated through the 3-D numerical analyses using a frozen rotor method. In order to select the optimum design, each flow analysis result was compared with others. Flow characteristics in the passages and some types of losses induced by shocks and wakes were found from calculation results. Based on these calculations, a new rotor blade was redesigned and compared with previous one through flow analysis.

Numerical Flow Analysis of a Supersonic Impulse Turbine with Nozzles and Rotor blades (노즐과 로터가 장착된 초음속 충동형 터빈의 전산유동해석)

  • Park, Pyun Goo;Lee, En Seok;Jeong, Eun Hwan;Kim, Jinhan
    • 유체기계공업학회:학술대회논문집
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    • 2004.12a
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    • pp.445-451
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    • 2004
  • Four design candidates for a 1.4MW class partial admission turbine have been chosen from a Preliminary design process. Their performance were estimated through the 3-D numerical analyses using a frozen rotor method. In order to select the optimum design, each flow analysis result was compared with others. Flow characteristics in the passages and some types of losses induced by shocks and wakes were found from calculation results. Based on these calculations, a new rotor blade was redesigned and compared with previous one through flow analysis.

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The performance effect of shroud split for turbopump turbine rotor (터보펌프 터빈 로터의 슈라우드 스플릿이 성능에 미치는 영향)

  • Lee, Hang-Gi;Jung, Eun-Hwan;Yoon, Suk-Hwan;Park, Pyun-Gu;Kim, Jin-Han
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2012.05a
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    • pp.117-122
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    • 2012
  • A blisk with rotor shroud is usually adopted in LRE turbine to maximize its performance. However it experiences severe thermal load and resulting damage during engine stating and stop. Shroud splitting is devised to relieve thermal stress on the turbine rotor. Structural analysis confirmed the reduction of plastic strain at the blade hub and tip. However, split gap at the rotor shroud entails additional tip leakage and results performance degradation. In order to assess the effect of shroud split on the turbine performance, tests have been performed for various settings of shroud split. For the maximum number of shroud splitting, measured efficiency reduction ratio was 2.65% to the value of original shape rotor.

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Effect of Shroud Split on the Performance of a Turbopump Turbine Rotor (터보펌프 터빈 로터의 슈라우드 스플릿이 성능에 미치는 영향)

  • Lee, Hanggi;Jeong, Eunhwan;Park, Pyungoo;Yoon, Sukhwan;Kim, Jinhan
    • Journal of the Korean Society of Propulsion Engineers
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    • v.17 no.4
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    • pp.25-31
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    • 2013
  • A blisk with rotor shroud is usually adopted in LRE turbine to maximize its performance. However it experiences the severe thermal load and resulting damage during engine stating and stop. Shroud splitting is devised to relieve the thermal stress on the turbine rotor. Structural analysis confirmed the reduction of plastic strain at the blade hub and tip. However, split gap at the rotor shroud entails additional tip leakage and results performance degradation. In order to assess the effect of shroud split on the turbine performance, tests have been performed for various settings of shroud split. For the maximum number of shroud splitting, measured efficiency reduction ratio was 2.65% to the value of original shape rotor.