• 제목/요약/키워드: Variable nozzle

검색결과 119건 처리시간 0.024초

램제트/스크램제트의 기술동향과 소요기술 분석 I. 램제트 엔진(액체램제트, 덕티드로켓) (Technical Review and Analysis of Ramjet/Scramjet Technology I. Ramjet Engine (Liquid Ramjet, Ducted Rocket))

  • 성홍계;윤현걸
    • 한국추진공학회지
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    • 제10권1호
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    • pp.72-86
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    • 2006
  • 램제트 추진기술에 대한 최근 개발동향과 필요 주요기술을 분석하였다. 통합 부스터의 장점을 극대화하면서 부스터의 총역적을 다양하게 조정하는 기술, 램제트 연소실의 길이는 최소화하면서 화염을 안정시키는 기술, 비행 운용범위를 다양하도록 하는 가변노즐 기술, 장시간 작동을 가능하게 하는 열차폐 기술 등이 소개/분석되었다. 여러 나라에서 다양한 램제트 추진기술을 개발해왔으며, 원초적 기술은 어느 정도 성숙되었으며, 군사적 응용과 복합사이클을 사용하는 민수용으로의 적용이 확대되고 있는 추세이다. 보다 효과적으로 다양한 발사 프랫폼에 공통으로 적용 가능한 다용도 램제트 기술 개발을 위하여 최근에 여러 유도탄(미국의 JSSAM, 러시아의 Yakhont)들이 연구되었으며, 이는 기술 신뢰도 향상 및 개발경비 절감을 높일 수 있다는 기대로 도전적 연구가 진행되고 있다.

배플이 장착된 로켓 연소기의 선형 안정성 해석 (Linear Stability Analysis of a Baffled Rocket Combustor)

  • 이수용
    • 한국추진공학회지
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    • 제22권3호
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    • pp.46-52
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    • 2018
  • 액체산소 및 탄화수소를 사용하는 연소기의 고주파 연소불안정을 해석하기 위해 단순모델로서 Crocco의 $n-{\tau}$ 시간지연 연소모델을 적용하고, 음향과 커플된 연소기 내 유동에 대해 선형해석을 수행하였다. 변수분리를 통해 편미분 포텐셜함수 식을 원통좌표계 미분방정식으로 만들고, 연소기의 접선방향 공진모드에 대한 고유 값을 계산하였다. 분사면 및 노즐입구를 경계조건으로 적용하여 미분식의 해를 구했다. 시스템의 안정성 판정을 위해 전달함수를 주파수 해석 하였으며, 관심 영역 주파수인 1T 모드 주변 주파수에서 시스템 게인 및 위상각으로 안정성 여유를 평가하였다. 또한 1T 모드 안정성 향상을 위해 배플 길이 및 형상에 대한 영향을 평가하였다.

Steady-State/Transient Performance Simulation of the Propulsion System for the Canard Rotor Wing UAV during Flight Mode Transition

  • Kong, Changduk;Kang, Myoungcheol;Ki, Jayoung
    • 한국추진공학회:학술대회논문집
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    • 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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    • pp.513-520
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    • 2004
  • A steady-state/transient performance simulation model was newly developed for the propulsion system of the CRW (Canard Rotor Wing) type UAV (Unmanned Aerial Vehicle) during flight mode transition. The CRW type UAV has a new concept RPV (Remotely Piloted Vehicle) which can fly at two flight modes such as the take-off/landing and low speed forward flight mode using the rotary wing driven by engine bypass exhaust gas and the high speed forward flight mode using the stopped wing and main engine thrust. The propulsion system of the CRW type UAV consists of the main engine system and the duct system. The flight vehicle may generally select a proper type and specific engine with acceptable thrust level to meet the flight mission in the propulsion system design phase. In this study, a turbojet engine with one spool was selected by decision of the vehicle system designer, and the duct system is composed of main duct, rotor duct, master valve, rotor tip-jet nozzles, and variable area main nozzle. In order to establish the safe flight mode transition region of the propulsion system, steady-state and transient performance simulation should be needed. Using this simulation model, the optimal fuel flow schedules were obtained to keep the proper surge margin and the turbine inlet temperature limitation through steady-state and transient performance estimation. Furthermore, these analysis results will be used to the control optimization of the propulsion system, later. In the transient performance model, ICV (Inter-Component Volume) model was used. The performance analysis using the developed models was performed at various flight conditions and fuel flow schedules, and these results could set the safe flight mode transition region to satisfy the turbine inlet temperature overshoot limitation as well as the compressor surge margin. Because the engine performance simulation results without the duct system were well agreed with the engine manufacturer's data and the analysis results using a commercial program, it was confirmed that the validity of the proposed performance model was verified. However, the propulsion system performance model including the duct system will be compared with experimental measuring data, later.

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하이브리드 로켓용 파라핀 연료의 후연소실 L/D비 변화에 따른 연소 특성 연구 (A Study on the Combustion Characteristic of Paraffin Fuel Based Hybrid Rocket with the Post Chamber L/D Ratio)

  • 고수한;이동희;권세진;문희장
    • 한국추진공학회지
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    • 제23권5호
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    • pp.19-26
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    • 2019
  • 파라핀 연료는 일반적으로 상당량의 미연 액적들이 노즐로 배출되는 관계로 연소효율을 낮아 연소효율과 직결된 후연소실의 최적화는 중요한 성능인자로 대두되고 있다. 따라서 본 연구에서는 하이브리드 로켓용 후연소실 길이 및 직경 변화에 따른 연소 특성을 파악하기 위한 연소 시험을 수행하였다. 연소 시험 결과, 후연소실 길이가 증가할수록 특성속도효율이 상승함을 확인하였으며 이는 후연소실 길이가 증가할수록 연소가스의 잔류시간 증가와 연소실 압력에 기인되는 것으로 판단되었다. 반면, 후연소실 직경 변화에 따른 특성속도효율 및 압력의 차이는 길이 변화 대비 크지 않음을 확인하였다. 따라서 하이브리드 로켓 시스템의 연소효율에 영향을 미치는 후연소실의 기하학적 요인은 직경보다는 길이의 영향에 크게 지배되는 것으로 사료된다.

Development Study of A Precooled Turbojet Engine for Flight Demonstration

  • Sato, Tetsuya;Taguchi, Hideyuki;Kobayashi, Hiroaiki;Kojima, Takayuki;Fukiba, Katsuyoshi;Masaki, Daisaku;Okai, Keiichi;Fujita, Kazuhisa;Hongoh, Motoyuki;Sawai, Shujiro
    • 한국추진공학회:학술대회논문집
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    • 한국추진공학회 2008년 영문 학술대회
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    • pp.109-114
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    • 2008
  • This paper presents the development status of a subscale precooled turbojet engine "S-engine" for the hypersonic cruiser and space place. S-engine employs the precooled-cycle using liquid hydrogen as fuel and coolant. It has $23cm{\times}23cm$ of rectangular cross section, 2.6 m of the overall length and about 100 kg of the target weight employing composite materials for a variable-geometry rectangular air-intake and nozzle. The design thrust and specific impulse at sea-level-static(SLS) are 1.2 kN and 2,000 sec respectively. After the system design and component tests, a prototype engine made of metal was manufactured and provided for the system firing test using gaseous hydrogen in March 2007. The core engine performance could be verified in this test. The second firing test using liquid hydrogen was conducted in October 2007. The engine, fuel supplying system and control system for the next flight test were used in this test. We verified the engine start-up sequence, compressor-turbine matching and performance of system and components. A flight test of S-engine is to be conducted by the Balloon-based Operation Vehicle(BOV) at Taiki town in Hokkaido in October 2008. The vehicle is about 5 m in length, 0.55 m in diameter and 500 kg in weight. The vehicle is dropped from an altitude of 40 km by a high-altitude observation balloon. After 40 second free-fall, the vehicle pulls up and S-engine operates for 60 seconds up to Mach 2. High altitude tests of the engine components corresponding to the BOV flight condition are also conducted.

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Firing Test of Core Engine for Pre-cooled Turbojet Engine

  • Taguchi, Hideyuki;Sato, Tetsuya;Kobayashi, Hiroaiki;Kojima, Takayuki;Fukiba, Katsuyoshi;Masaki, Daisaku;Okai, Keiichi;Fujita, Kazuhisa;Hongoh, Motoyuki;Sawai, Shujiro
    • 한국추진공학회:학술대회논문집
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    • 한국추진공학회 2008년 영문 학술대회
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    • pp.115-121
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    • 2008
  • A core engine for pre-cooled turbojet engines is designed and its component performances are examined both by CFD analyses and experiments. The engine is designed for a flight demonstration of precooled turbojet engine cycle. The engine uses gas hydrogen as fuel. The external boundary including measurement devices is set within $23cm{\times}23cm$ of rectangular cross section, in order to install the engine downstream of the air intake. The rotation speed is 80000 rpm at design point. Mixed flow compressor is selected to attain high pressure ratio and small diameter by single stage. Reverse type main combustor is selected to reduce the engine diameter and the rotating shaft length. The temperature at main combustor is determined by the temperature limit of non-cooled turbine. High loading turbine is designed to attain high pressure ratio by single stage. The firing test of the core engine is conducted using components of small pre-cooled turbojet engine. Gas hydrogen is injected into the main burner and hot gas is generated to drive the turbine. Air flow rate of the compressor can be modulated by a variable geometry exhaust nozzle, which is connected downstream of the core engine. As a result, 75% rotation speed is attained without hazardous vibration and heat damage. Aerodynamic performances of both compressor and turbine are obtained and evaluated independently.

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준 일차원 다상 반응유동 기법을 이용한 케로신/과산화수소 액체 핀틀 추력기 성능해석 연구: Part II 추력기 성능 특성 (Performance Analysis of Liquid Pintle Thruster Using Quasi-one-dimensional Multi-phase Reaction Flow: Part II. Thruster Performance Characteristics)

  • 강정석;복장한;성홍계;권민찬;허준영
    • 한국추진공학회지
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    • 제24권6호
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    • pp.78-84
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    • 2020
  • 본 논문에서는 Part I에 소개된 요소모델들을 통합하여 핀틀 추력기 성능 특성을 분석하였다. 성능해석 모델 검증을 위하여 케로신/과산화수소 액체 핀틀 추력기의 실험결과와 비교 분석하였다. 검증한 결과를 바탕으로 핀틀 추력기 내부의 비정상 열유동장의 물리적 특성을 분석하였으며 필름효과를 확인하였다. 또한 추력기의 형상인자와 작동인자가 성능특성에 미치는 영향을 파악하기 위하여 OAT 방법과 scatter plot 방법을 이용해 민감도 분석을 수행하였다. 액적직경, 필름유량, O/F비, 노즐목 직경의 4가지 인자를 이용해 특성속도, 연소실 압력, 비추력의 변화에 대한 영향을 관찰하였다.

125 MW급 우드펠릿 발전소에서 탈질설비 운전조건이 질소산화물 발생량에 미치는 영향 (Effect of the De-NOx Facility Operating Condition on NOx Emission in a 125 MW Wood Pellet Power Plant)

  • 전문수;이재헌
    • 플랜트 저널
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    • 제18권3호
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    • pp.52-61
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    • 2022
  • 본 연구는 실제 운영중인 영동에코발전본부 1호기 125 MW 우드펠릿 발전소를 대상으로 탈질설비 운전조건이 NOx 발생량에 미치는 영향을 시험하였다. SNCR 요소 유량 증가에 따라 NOx 농도는 점차 감소하였으나 SCR 후단 암모니아 슬립은 상승하였다. 시험대상 보일러는 고온의 내부온도로 인해 SNCR 운영에 불리한 구조이며 노즐의 최적위치 검토가 필요할 것이다. SCR 희석공기 온도변화는 NOx 발생량에 영향을 미치지 않았다. SCR 암모니아 유량 증가는 SCR 후단 NOx 농도를 감소시켰고 NOx 제거효율도 증가시켰다. 다만 암모니아 슬립 자체 기준치를 초과하지 않는 암모니아 유량 111 kg/h가 최대 운전기준으로 추정된다. SCR 믹서 압력 상승은 NOx 농도를 감소시키고 제거효율도 최대로 측정되어 NOx 생성을 가장 효과적으로 억제하는 변수로 파악되었다.

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불량환경하(不良環境下)에서의 제초제(除草劑) 약해(藥害)와 경감기술(輕減技術) (Herbicidal Phytotoxicity under Adverse Environments and Countermeasures)

  • 권용웅;황형식;강병화
    • 한국잡초학회지
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    • 제13권4호
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    • pp.210-233
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    • 1993
  • The herbicide has become indispensable as much as nitrogen fertilizer in Korean agriculture from 1970 onwards. It is estimated that in 1991 more than 40 herbicides were registered for rice crop and treated to an area 1.41 times the rice acreage ; more than 30 herbicides were registered for field crops and treated to 89% of the crop area ; the treatment acreage of 3 non-selective foliar-applied herbicides reached 2,555 thousand hectares. During the last 25 years herbicides have benefited the Korean farmers substantially in labor, cost and time of farming. Any herbicide which causes crop injury in ordinary uses is not allowed to register in most country. Herbicides, however, can cause crop injury more or less when they are misused, abused or used under adverse environments. The herbicide use more than 100% of crop acreage means an increased probability of which herbicides are used wrong or under adverse situation. This is true as evidenced by that about 25% of farmers have experienced the herbicide caused crop injury more than once during last 10 years on authors' nationwide surveys in 1992 and 1993 ; one-half of the injury incidences were with crop yield loss greater than 10%. Crop injury caused by herbicide had not occurred to a serious extent in the 1960s when the herbicides fewer than 5 were used by farmers to the field less than 12% of total acreage. Farmers ascribed about 53% of the herbicidal injury incidences at their fields to their misuses such as overdose, careless or improper application, off-time application or wrong choice of the herbicide, etc. While 47% of the incidences were mainly due to adverse natural conditions. Such misuses can be reduced to a minimum through enhanced education/extension services for right uses and, although undesirable, increased farmers' experiences of phytotoxicity. The most difficult primary problem arises from lack of countermeasures for farmers to cope with various adverse environmental conditions. At present almost all the herbicides have"Do not use!" instructions on label to avoid crop injury under adverse environments. These "Do not use!" situations Include sandy, highly percolating, or infertile soils, cool water gushing paddy, poorly draining paddy, terraced paddy, too wet or dry soils, days of abnormally cool or high air temperature, etc. Meanwhile, the cultivated lands are under poor conditions : the average organic matter content ranges 2.5 to 2.8% in paddy soil and 2.0 to 2.6% in upland soil ; the canon exchange capacity ranges 8 to 12 m.e. ; approximately 43% of paddy and 56% of upland are of sandy to sandy gravel soil ; only 42% of paddy and 16% of upland fields are on flat land. The present situation would mean that about 40 to 50% of soil applied herbicides are used on the field where the label instructs "Do not use!". Yet no positive effort has been made for 25 years long by government or companies to develop countermeasures. It is a really sophisticated social problem. In the 1960s and 1970s a subside program to incoporate hillside red clayish soil into sandy paddy as well as campaign for increased application of compost to the field had been operating. Yet majority of the sandy soils remains sandy and the program and campaign had been stopped. With regard to this sandy soil problem the authors have developed a method of "split application of a herbicide onto sandy soil field". A model case study has been carried out with success and is introduced with key procedure in this paper. Climate is variable in its nature. Among the climatic components sudden fall or rise in temperature is hardly avoidable for a crop plant. Our spring air temperature fluctuates so much ; for example, the daily mean air temperature of Inchon city varied from 6.31 to $16.81^{\circ}C$ on April 20, early seeding time of crops, within${\times}$2Sd range of 30 year records. Seeding early in season means an increased liability to phytotoxicity, and this will be more evident in direct water-seeding of rice. About 20% of farmers depend on the cold underground-water pumped for rice irrigation. If the well is deep over 70m, the fresh water may be about $10^{\circ}C$ cold. The water should be warmed to about $20^{\circ}C$ before irrigation. This is not so practiced well by farmers. In addition to the forementioned adverse conditions there exist many other aspects to be amended. Among them the worst for liquid spray type herbicides is almost total lacking in proper knowledge of nozzle types and concern with even spray by the administrative, rural extension officers, company and farmers. Even not available in the market are the nozzles and sprayers appropriate for herbicides spray. Most people perceive all the pesticide sprayers same and concern much with the speed and easiness of spray, not with correct spray. There exist many points to be improved to minimize herbicidal phytotoxicity in Korea and many ways to achieve the goal. First of all it is suggested that 1) the present evaluation of a new herbicide at standard and double doses in registration trials is to be an evaluation for standard, double and triple doses to exploit the response slope in making decision for approval and recommendation of different dose for different situation on label, 2) the government is to recognize the facts and nature of the present problem to correct the present misperceptions and to develop an appropriate national program for improvement of soil conditions, spray equipment, extention manpower and services, 3) the researchers are to enhance researches on the countermeasures and 4) the herbicide makers/dealers are to correct their misperceptions and policy for sales, to develop database on the detailed use conditions of consumer one by one and to serve the consumers with direct counsel based on the database.

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