• Title, Summary, Keyword: Propulsion performance

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Performance Analysis of Turboprop Aircraft Propulsion System by using Gasturb (Gasturb를 이용한 터보프롭 항공기 추진시스템 성능해석)

  • Choi, Won;Jeong, In-Myon;You, Jae-Ho;Kim, Ji-Hong;Lee, Il-Woo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.371-377
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    • 2009
  • The propulsion system of turboprop has been rarely used in the large aircraft due to the limitation of the maximum velocity of the propeller, the power limitation by the reduction gear, etc. Recently, the demand on turboprop aircraft continues to increase because of economical efficiency and environmental factors. In this paper, turboprop propulsion system which is composed of a Pratt & Whitney 127F turboprop engine and a Hamilton Standard 568F propeller was modeled by using the Gasturb11 software. The result of the performance analysis on this propulsion system model showed that the propulsion system model was evaluated to have been successfully builded.

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A Study on Steady-state Performance Simulation of Smart UAV Propulsion System (신개념 비행체 추진시스템의 정상상태 성능모사 기법 연구)

  • 공창덕;강명철;기자영;양수석;이창호
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.177-182
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    • 2003
  • In this study, a performance model of the Smart UAV propulsion system with ducts, tip jets and variable main nozzle, which has flight capability of the rotary wing mode for the take-off/landing and low speed forward flight as welt as the fixed wing mode for high speed forward flight, has been newly developed. With the proposed model, steady-state performance analysis was performed at various flight modes and conditions, such as rotary wing mode, fixed wing mode, compound wing, mode altitude and flight speed. In investigation of performance analysis, it was noted that the operational capability of the propulsion system was limited due to the duct losses depending on each flight mode, and the limitation with the altitude variation case has much greater than that with the flight speed variation case.

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A Study on Performance Analysis of a Helicopter Propulsion System Using SIMULINK (SIMULINK를 이용한 헬리콥터 추진시스템의 성능해석에 관한 연구)

  • Kong, Chang-Duk;Ki, Ja-Young;Kho, Seong-Hee;Kim, Jae-Hwan
    • Journal of the Korean Society of Propulsion Engineers
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    • v.12 no.1
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    • pp.44-50
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    • 2008
  • In this study a turboshaft engine for a helicopter propulsion system was modeled using SIMULINK and the components' maps were generated from the limited performance deck data provided by engine supplier using a hybrid method with the genetic algorithms and the system identification method. In order to verify the SIMULINK performance model and the component maps generated by the hybrid method, the steady-state performance analysis results were compared with the performance data provided by engine manufacturer. In this investigation, it was confirmed that the analysis results by the proposed model are closely met with those by engine manufacturer's data.

Performance Evaluation of C/SiC Composites (C/SiC 복합재료의 내열성능 평가)

  • Kim, Yun-Chul
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.185-188
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    • 2007
  • The main objective of this research effort was to develope the performance of C/SiC composites manufactured by LSI (Liquid Silicon Infiltration) method for solid and liquid rocket propulsion system and ensure the performance analysis technique. The various carbon preform were manufactured by filament winding, tape rolling, involute layup and stack molding process. For the best performance of thermal and mechanical properties, many process conditions were tested and selected by varying preform, the content of SiC, temperature, impregnation resin and chemical vapour reaction. In conclusion, the high performance and reliability of C/SiC composite were proved for solid and liquid rocket propulsion system. And the performance analysis technique related to mathematical ablation model was originated.

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A Study on Installed Performance Analysis Modelling for a Helicopter Propulsion System Considering Intake Loss (흡입구 손실을 고려한 헬리콥터 추진시스템의 장착성능 해석 모델에 관한 연구)

  • Kong, Chang-Duk;Koo, Young-Ju;Kho, Seong-Hee;Ki, Ja-Young;Cha, Bong-Jun;Yu, Hyeok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.263-267
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    • 2008
  • In this work the realistic install performance analysis of a helicopter was performed together with power extraction enabling to operate auxiliary system as well as intake pressure loss, loss due to bleed air, etc. which must be considered in practical propulsion system's performance modelling to be installed to the airframe. The pressure loss occurring in intake was estimated from the intake performance map with relationships of Mach Number and pressure loss. In order to evaluate the proposed installed performance model, the experimental data for comparison must be needed when mounted in propulsion system. However because of lack of accessibility to such real data at the moment, the alternative way was made through comparison that the analysis results by the proposed model were compared with a wellknown commercial program GASTURB's analysis results. The validity of the proposed installed performance model was consequently confirmed because its average deferences from the GASTURB's results were within 0.5%.

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A Study on Installed Performance Analysis Modelling for a Helicopter Propulsion System Considering Intake Loss (흡입구 손실을 고려한 헬리콥터 추진시스템의 장착성능 해석 모델에 관한 연구)

  • Kong, Chang-Duk;Kho, Seong-Hee;Ki, Ja-Young;Jun, Yong-Min;Ahn, Lee-Ki
    • Journal of the Korean Society of Propulsion Engineers
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    • v.12 no.1
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    • pp.51-56
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    • 2008
  • In this work the realistic install performance analysis of a helicopter was performed together with power extraction enabling to operate auxiliary system as well as intake pressure loss, loss due to bleed air, etc. which must be considered in practical propulsion system's performance modelling to be installed to the airframe. The pressure loss occurring in intake was estimated from the intake performance map with relationships of Mach Number and pressure loss. In order to evaluate the proposed installed performance model, the experimental data for comparison must be needed when mounted in propulsion system. However because of lack of accessibility to such real data at the moment, the alternative way was made through comparison that the analysis results by the proposed model were compared with a wellknown commercial program GASTURB's analysis results. The validity of the proposed installed performance model was consequently confirmed because its average deferences from the GASTURB's results were within 0.5%.

A study on structural integrity and dynamic characteristic of inertial load test equipment for performance test of railway vehicle propulsion control system (철도차량 추진제어장치 성능시험을 위한 관성부하 시험설비의 구조안전성 및 동특성 평가 연구)

  • Jang, Hyung-Jin;Shin, Kwang-Bok;Lee, Sang-Hoon;Lee, Dae-Bong
    • Proceedings of the KSR Conference
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    • pp.1389-1394
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    • 2010
  • This paper describes the evaluation of structural integrity and dynamic characteristic of inertial load test equipments for performance test of railway vehicle propulsion control system. The propulsion control system of railway vehicle has to be confirmed of safety and reliability prior to it's application. Therefore, inertial load test equipments were designed through theoretical equation for performance test of propulsion control system. The structural analysis of inertial load test equipments was conducted using Ansys v11.0 and it's dynamic characteristic was evaluated the designed using Adams. The results showed that the structural integrity of inertial load test equipment was satisfied with a safety factor of 10.2. Also, the structural stability was proved by maximum dynamic displacement of 0.82mm.

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On the Model Tests for POD Propulsion Ships

  • Go Seokcheon;Seo Heungwon;Chang Bong Jun
    • Journal of Ship and Ocean Technology
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    • v.9 no.1
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    • pp.1-10
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    • 2005
  • The procedures of model test and performance prediction for the CRP-POD propulsion ships, are studied. At the CRP-POD system, which are highly applicable to ultra large container carriers, RPM ratio of two propellers is not fixed, unlike conventional CRP system, and hence the power of each propeller must be predicted respectively. In this paper, a CRP-POD system is designed for 10,000 TEU class ultra large container carriers, and the characteristics of the CRP-POD system are experimentally studied. Finally, based on this study, the procedure of powering performance evaluation for CRP-POD propulsion ships is suggested. However, further studies on quantitative correction of the present procedure are required.

Conceptual Design Trade Offs between Solid and Liquid Propulsion for Optimal Stage Configuration of Satellite Launch Vehicle

  • Qasim, Zeeshan;Dong, Yunfeng
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.283-292
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    • 2008
  • The foremost criterion in the design of a Satellite Launch Vehicle(SLV) is its performance capability to boost the designated payload to the desired mission orbit; it starts from focusing on the SLV configuration to achieve the velocity requirements($}\Delta}V$) for the mission. In this paper we review an analytical approach which is suitable enough for preliminary conceptual design and is used previously to optimize stage configurations for Two Stage to Orbit SLV for Low Earth Orbit(LEO) Missions; we have extended this approach to Three Stage to Orbit SLV and compared different propellant options for the mission. The objective is to minimize the Gross Lift off Weight(GLOW). The primary performance figures of merit were the total inert weight of the SLV and the payload weight that the SLV could lift into LEO, given candidate propulsion systems. The optimization is achieved by configuring the $}\Delta}V$ between stages. A comparison of configurations of single-stage and multi-stage SLVs is made for different propellants. Based upon the optimized stage configurations a comparative performance analysis is made between Liquid and Solid fueled SLV. A 3 degree of freedom trajectory-analysis program is modeled in SIMULINK and used to conduct the performance analysis. Furthermore, a cost analysis is performed on our stage optimized SLVs. The cost estimation relationships(CER) used give us a comparison of development and fabrication costs for the Liquid vs. Solid fueled SLV in man years. The pros and cons of the production, operation ability, performance, responsiveness, logistics, price, shelf life, storage etc of both Solid and Liquid fueled SLVs are discussed. The statistics and data are used from existing or historical(real) SLV stages.

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CFD Analysis of Performance of KRISO Devices (K-DUCT) for Propulsion Efficiency Improvement (CFD를 이용한 KRISO 추진효율 향상 장치(K-duct)의 성능 해석)

  • Suh, Sung-Bu
    • Journal of Ocean Engineering and Technology
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    • v.31 no.3
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    • pp.183-188
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    • 2017
  • This paper provides numerical results for the estimation of the efficiency of KRISO energy saving devices in the design stage. A finite volume method is used to solve Reynolds averaged Navier-Stokes (RANS) equations, where the SST k-$\omega$ model is selected for turbulence closure. The propeller rotating motion is determined using a rigid body motion (RBM) scheme, which is called a sliding mesh technique. The numerical analysis focuses on predicting the power reduction by the designed KRISO devices (K-DUCT) under a self-propulsion condition. The present numerical results show good agreement with the available experimental data. Finally, it is concluded that CFD can be a useful method, along with model tests, for assessing the performance of energy saving devices for propulsion efficiency improvement.