• 항공우주기술
• /
• 제8권2호
• /
• pp.133-139
• /
• 2009

가스발생기 사이클 액체로켓엔진의 비추력 성능 해석을 수행하였다. 본 해석 방법은 공개된 문헌의 추력 300톤급 엔진에 대한 개념설계와 비교하여 검증을 마쳤다. 막냉각을 증가시킴으로써 연료가 연소에 참여하는 비율이 감소될 수 있지만 재생냉각에 필요한 연료 펌프의 소요동력 감소를 통하여 엔진의 비추력이 증가될 수 있다. 개선된 조건은 막냉각의 도움을 통하여 연료펌프 헤드를 감소시키고 연소 압력을 높일 수 있음을 예시한다.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2010년도 제35회 추계학술대회논문집
• /
• pp.601-604
• /
• 2010

본 연구는 과산화수소와 케로신을 추진제로 하는 액체로켓엔진에 막냉각 링을 장착하여 막냉각 효과에 관한 연구를 수행하였다. 막냉각제의 유량 및 냉각장치 형상에 따른 열유속을 계산하기 위하여 축방향으로 열전대를 장착하여 온도를 측정하였다. 냉각제 유량은 총 추진제 유량의 0~20%의 유량으로 선정하여 실험을 수행하였다.

• 한국항공우주학회지
• /
• 제34권2호
• /
• pp.75-81
• /
• 2006

로켓엔진에서 선형 연소 안정한계에 미치는 유한화학반응의 열적 효과와 막냉각 효과를 조사하였다. 안정한계를 평가하기위해 3차원 연소실에서 유한화학반응을 채택한 반응 유동장 계산으로부터 구한 유동변수들을 사용하였다. 주요 유동변수들의 값은 유한화학반응 모델의 채택으로 인해 상당히 달라졌으며 결과적으로 안정한계도 수정되었다. 유한화학반응은 열적 관점에서 안정성 향상에 기여함을 알았다. 또한 막냉각을 한 경우, 안정성 경향이 향상됨을 알 수 있었다.

• 대한기계학회:학술대회논문집
• /
• 대한기계학회 2007년도 춘계학술대회B
• /
• pp.2291-2296
• /
• 2007

Thermal transport from vertical heated surface to falling liquid film in a channel has been investigated experimentally. Air-flow is introduced into channel to make a counter flow against falling liquid film. This problem is of particular interest in the design of direct contact heat exchange system, such as cooling tower, evaporative cooling system, absorption cooling system, and distillation system. The effects of channel width and air flow rate on the heat transfer to falling liquid film are studied in detail. The results obtained indicate that heat transfer rate is gradually decreased with an increase in the channel width without air flow as well as with air flow in a channel. It is also found that heat transfer rate of air-flow is increased while heat transfer rate of falling liquid film is decreased with an increase in the air flow rate at a given channel width. However, total heat transfer rate form the heated surface is increased as the air flow rate is increased.

• 대한기계학회:학술대회논문집
• /
• 대한기계학회 2001년도 추계학술대회논문집B
• /
• pp.746-751
• /
• 2001

We used a cylindrical model which simulates turbine blade leading edge to investigate the effects of free-stream turbulence intensity and blowing ratio on film cooling of turbine blade leading edge. Tests are carried out in a low-speed wind tunnel on a cylindrical model with three rows of injection holes. Mainstream Reynolds number based on the cylinder diameter was $7.1\times10^4$. Two types of turbulence grid are used to increase a free-stream turbulence intensity. The effect of coolant blowing ratio was studied for various blowing ratios. For each blowing ratios, wall temperatures around the surface of the test model are measured by thermocouples installed inside the model. Results show that blowing ratios have small effect on spanwise-averaged film effectiveness at high free-stream turbulence intensity. However, an increase in free-stream turbulence intensity enhances significantly spanwise-averaged film effectiveness at low blowing ratio.

• 대한기계학회논문집B
• /
• 제32권5호
• /
• pp.335-341
• /
• 2008

Thermal transport from vertical heated surface to falling liquid film in a channel has been investigated experimentally. Air-flow is introduced into channel to make a counter flow against falling liquid film. This problem is of particular interest in the design of direct contact heat exchange system, such as cooling tower, evaporative cooling system, absorption cooling system, and distillation system. The effects of channel width and air flow rate on the heat transfer to falling liquid film are studied in detail. The results obtained indicate that heat transfer rate is gradually decreased with an increase in the channel width without air flow as well as with air flow in a channel. It is also found that heat transfer rate of air-flow is increased while heat transfer rate of falling liquid film is decreased with an increase in the air flow rate at a given channel width. However, total heat transfer rate from the heated surface is increased as the air flow rate is increased.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2007년도 제29회 추계학술대회논문집
• /
• pp.170-173
• /
• 2007

본 연구에서는 액체로켓엔진 내부에 라이너를 설치하고 기체 질소를 이용한 막냉각 방법을 사용하여, 라이너의 막냉각 특성을 살펴보았다. 고온 가스는 액체로켓 연소가스와 액체질소를 혼합하여 사용하였다. 기존의 액체로켓엔진 시험 설비에 추가적으로 라이너 냉각 기체를 공급 설비를 구축하였으며, 라이너 및 냉각 기체 공급부를 제작하였다. 10초 연소 실험을 통해 라이너 내부 고온 가스의 온도와 라이너 외부 벽면 온도를 측정하였으며, 기체 질소에 의한 라이너 냉각 특성을 확인하였다.

• Journal of Advanced Marine Engineering and Technology
• /
• 제11권1호
• /
• pp.72-79
• /
• 1987

When the wall temperature is very high, a stable vapor film covers the heat transfer surface. The vapor film creates a strong thermal resistance when heat is transferred to the liquid though it. This phenomenon, called "film boiling" is very important in the heat treatment of metals, the design of cryogenic heat exchangers, and the emergency cooling of nuclear reactors. In the practical engineering problems of the transient cooling process of a high temperature wall, the wall temperature history, the variation of the heat transfer coefficients, and the wall superheat at the rewetting points, are the main areas of concern. These three areas are influenced in a complex fashion such factors as the initial wall temperature, the physical properties of both the wall and the coolant, the fluid temperature, and the flow state. Therefore many kinds of specialized experiments are necessary in the creation of precise thermal design. The object of this study is to investigate the heat transfer characteristics in the transient cooling process of a high temperature wall. The slow transient cooling experiment was carried out with a copper block of high thermal capacity. The block was 240 mm high and 79 mm O.D.. The coolant flowed throuogh the center of a 10 mm diameter channel in the copper block. In the copper block, three sheathed thermocouples were placed in a line perpendicular to the flow. These thermocouples were used to take measurements of the temperature histories of the copper block.

• 한국유체기계학회 논문집
• /
• 제17권6호
• /
• pp.52-58
• /
• 2014

In the present work, design optimization of film-cooling hole array on the pressure side of high pressure turbine nozzle was conducted. There are four rows of fan-shaped film cooling holes on the nozzle pressure side surface and each row has a straight array of holes in the spanwise direction for baseline model. For design optimization, hole distributions in streamwise and spanwise directions for three rows of holes except first row are parameterized as a 2nd-order shape function. Three-dimensional compressible RANS equations are used for flow and thermal analysis around the nozzle surface and optimization technique using Design of Experiment, Kriging surrogate model and Genetic Algorithm is used. The results shows that averaged adiabatic wall temperature at the whole nozzle surface decreases about 2.7% and averaged film cooling effectiveness at the pressure side of nozzle increased about 8.2%.

• 한국분말야금학회:학술대회논문집
• /
• 한국분말야금학회 2006년도 Extended Abstracts of 2006 POWDER METALLURGY World Congress Part 1
• /
• pp.430-431
• /
• 2006

Thermoelectric thick film was fabricated by screen printing process with using p-type Bi-Te-Sb powders. The powder was synthesized by melting, milling and sintering process and hydrogen reduced to enhance the thermoelectric property. The thick film of Bi-Te-Sb powder was fabricated by screen printing method and baked at the optimized conditions. The thermal conductivity, the electrical resistivity and Seeback coefficient of thick film were measured and the thermoelectric performance was analyzed in terms of film characteristics and its microstructure. Finally, the feasibility of thermoelectric thick film into micro cooling device on CPU chip was discussed in this study.