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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
> Journal Vol & Issue
Journal of the Korean Society of Propulsion Engineers
Journal Basic Information
Journal DOI :
The Korean Society of Propulsion Engineers
Editor in Chief :
Volume & Issues
Volume 5, Issue 4 - Dec 2001
Volume 5, Issue 3 - Sep 2001
Volume 5, Issue 2 - Jun 2001
Volume 5, Issue 1 - Mar 2001
Selecting the target year
An experimental study on the liquid rocket combustion chamber cooling
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 2, 2001, Pages 1~7
To protect combustion chamber from high temperature combustion gas, regenerative cooling is used for most liquid rocket engine. Although regenerative cooling is the most effective way to protect the chamber from high heat flux, realization of this system requires detail analysis, manufacturing technique and high cost. To demonstrate the possibility of applying regenerative cooling to a real rocket engine, the hot fire test has been carried out for the sub-scale liquid rocket with the water cooling system. The main purpose of the test is to identify the problem area of design, safety and cost effective manufacturing technique. The coolant passage was 3 mm in width and wall thickness was 1 mm with stainless steel. Maximum combustion time and pressure were 60 seconds and 400 psi, respectively. The flow rate of coolant was reduced gradually from 2 kg/s to 0.12 kg/s throughout firing test, combustion chamber was visually examined and no dwfect was observed.
An Experimental Study of Compressor Section Profile in Transonic Flow
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 2, 2001, Pages 8~15
In the continuing quest for increased turbomachinery efficiency, the part played by blade profile shape remains crucial. The application of a heated thin metallic film with CTA(constant temperature anemometer) to the measurements of the laminar and turbulent boundary layer behavior(shock-boundary layer-interaction) in a transonic wind tunnel. Results of measurements with hot-film sensors on transonic compressor blades are extremely difficult to interpret because of ambiguous probe signals due to the complexity of the local flow pattern. In order to get the explicit information and give the designer to interpret characteristic signals from hot-film probes, a method was developed by comparing the results with other measuring technic results.
Development of Thrust Measurement System for Liquid Rocket Engine
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 2, 2001, Pages 16~23
For liquid rocket engine test, one of most important design parameters to be measured is thrust. However, not like solid rocket motor, a liquid rocket engine is attached to the propellant feed system, control valve and many other safety systems. Without considering these effects, thrust data measured from firing test is not reliable and sometimes almost meaningless. In this research, new thrust measurement system, which includes all these side effects, was designed and fabricated.
A Study on the One-Stage 3-Dimensional Axial Turbine Performance Test with Different Incidence Angle
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 2, 2001, Pages 24~31
An axial-type turbine design technology is developed. In order to design one-stage turbine, the preliminary design method is applied, and then design parameters are chosen after analyzing gas properties within the turbine passage using the streamline curvature method. Stator blade is designed using C4 profile, and rotor blade is designed using shape parameters. Stator is manufactured as an integral type and rotor is manufactured to be disassembled from the disc for changing blade incidence angle. The output power from the rotor is measured with various RPM and input power. Experimental results show that the maximum efficiency of turbine rotor is obtained on the design point, and the output power is proportionally decreased with the negative incidence angle even the test turbine is a reaction turbine. The efficiency of turbine rotor is decreased to 5% by
negative incidence angle from the designed value.
Emission Characteristics for the MTBE Gasoline Engine
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 2, 2001, Pages 32~37
This article is to provide reasonably accurate vehicle emission estimates for the four sampled fuels which are commercially available across the nation. Emission quantities are obtained by testing a vehicle on a chassis dynamometer and capturing a sample of the emissions from the tailpipe in vehicle. The vehicle is driven following a particular pattern of idle, acceleration, cruise, and deceleration. Shown here is the trace of the test cycle known as the CVS-75 Mode which is used to certify the emission performance standards. The mode of CVS-75 consists of a cold start cycle, a hot stabilized cycle, and a hot start cycle. Emissions for the pollutants are measured in vehicle testing. These are carbon monoxide (CO), oxides of nitrogen (NOx), and total hydrocarbon (THC). The test results summarized in this report indicate that the differences for the amount of emission are quantitatively minimal.
A study on the performance prediction technique of the dual-thrust rocket motor
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 2, 2001, Pages 38~43
In this study, the technique of the performance prediction on the finocyl-type dual-thrust rocket motor is developed, and the predicted data are compared with those of the static firing tests. The prediction is carried out with the separate calculations of the grain burning area and the performance of the rocket motor. When predicting the performance of the dual-thrust rocket motor, the different correction factors should be used at the boosting and sustaining phases. Otherwise, an error of prediction will follow. Reprediction using the separate correction factors shows good agreement with the test data within 0.5% error.
Performance Simulation of Turboprop Engine using SIMULINK
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 2, 2001, Pages 44~50
After modeling an aircraft turboprop engine using SIMULINK
, performance simulation of PT6A-62 engine, which is main power plant of KT-1, was performed. For validation, performance parameters of the SIMULIINK model were compared with the simulated results by GASTURB program. It was confirm that the results by the SIMULINK model were well agreed with those by GASTURB within 1.07%, It was assumed that installation losses were bleed-air exteraction with a range from 0% to 5%, and power for accessories with a range from 0 to 20hp. In this investigation, it was found that the shafthorsepower was decreased by maxium 0.68%, but specific fuel consumption ratio was not effected nearly by these losses.
The Experimental Study of Supersonic, Dual, Coaxial, Free, Jets (The effects of the assistant jet pressure ratio)
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 2, 2001, Pages 51~58
Supersonic, axisymmetric, jets issuing from several kinds of dual, coaxial, nozzles were experimentally investigated. Four different kinds of coaxial, dual nozzles were employed to characterize the major. features of the supersonic, coaxial, dual jets. Two convergent-divergent supersonic nozzles with different impinging angle on the jet axis of were designed to have the Mach number 2.0 and used to compare the coaxial jet flows with those discharging from two sonic nozzles. The primary pressure ratio was changed in the range from 4.0 to 10.0 and the assistant jet ratio from 1.0 to 4.0. The results obtained show that the assistant jets from the annular. nozzle affect the coaxial jet flows and an increase of both the primary jet pressure ratio and assistant jet pressure ratio lead to a longer supersonic length of the dual, coaxial jet.
A Study on the Static Strength Analysis in Composite Laminate
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 2, 2001, Pages 59~64
The purpose of this work is to investigate the static strength, the stress distribution, and the failure process of quasi-isotropic composite laminates made of two different matrices when loading directions are changed. We carried out static tests of
laminates. Two types of matrices used are AS4/epoxy and AS4/PEEK. The damage mechanisms of the quasi-isotropic laminate,
, strongly depend on the load direction applied to the laminate.
Performance Improvement of Free Power Gas Turbine Type Gas Turbine Engine by Using of a MAT Cycle
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 2, 2001, Pages 65~72
In order to improve the performance of a free power turbine type gas turbine engine by injecting the atomized water into a compressor inlet., a study on Moisture Air Turbine (MAT) cycle was proposed. Compressor work by air-water mixtures in phase change was theoretically considered, and it was found that the water evaporation might reduce the compressor work. Cycle model calculations predicted that power increments of 16.2%, 14.9% and 12.6% by 1.0% water to the air flow rate at the compressor intake with rotational shaft speeds of 1000, 1210, 1350 rps were obtained, and also thermal efficiency due to the reduction of compressor work was improved.
Review on Airbreathing Propulsion Technology for Missile Application
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 2, 2001, Pages 73~82
Technical status and prospect of the subsonic airbreathing propulsion system composed of jet engine for missile application are described herein, including analysis of some present airbreathing missiles. Comprehension on this can be applicable both to know deeply about the same type missiles and to get some basic idea of unmanned air vehicle's and light aircraft's propulsion system.