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바이오 가스터빈 연소기의 비반응장과 반응장의 3차원 유동해석
안윤호(Yunho An),남삼식(Samsik Nam),최진훈(Jinhoon Choe),임지혁(Jihyuk Im),김호근(Hokeun Kim),전재철(Jaechul Chun) 한국추진공학회 2011 한국추진공학회 학술대회논문집 Vol.2011 No.5
최근 두산중공업은 바이오가스를 연료로 사용하는 가스터빈엔진을 개발하고 있다. 본 논문은 바이오 가스터빈엔진의 주요 구성품 중 하나인 연소기의 비반응장과 반응장 해석에 대한 것이다. 해석을 통해 연소기 설계 결과를 검증하고 다양한 Fuel Distribution Ratio에서의 연소기 작동 거동을 예측하였다. 해석 결과는 두산에서 자체 수행한 리그 시험 결과와 비교하였다. 해석 결과 연소기 압력 손실, 공기 분배비, 재순환 유동의 예측은 신뢰할 만한 수준이며, 낮은 Fuel Distribution Ratio 영역에서의 NOx 생성 추세는 다소 불일치하였다. Doosan Heavy Industries & Construction Co., Ltd. has been recently developing the gas turbine engine using the biogas as fuel. This paper describes the non-reacting and reacting flow analysis of the combustor which is one of the main components in gas turbine engine. Through CFD analysis, investigation has been performed to evaluate the primary factors for aerodynamic design and to predict combustor behaviors during operation with various fuel distribution ratios. The calculation results are compared with rig test data, which reveals that CFD predictions such as pressure loss, air distribution ratio, and recirculation flow are quite reliable. The trend of NO formation was similar with the test, except the low fuel distribution ratio.
안윤호(Yunho An),김중석(Joungseok Kim) 대한기계학회 2016 대한기계학회 춘추학술대회 Vol.2016 No.12
This paper introduces and explains axial turbine aerodynamic design of the developing highly-efficiency industrial gas turbine engine by Doosan heavy industries and constructions. Turbine aerodynamic design should be started with proper boundary conditions and constraints from relevant design disciplines such as cycle, combustor, turbine heat transfer and structure. In order to meet the performance target, it is very essential to carry out 1-/2-dimensional through-flow calculations. Airfoil design phase can be performed by the boundary conditions from through-flow calculation results. After airfoil design, turbine performance should be confirmed by numerical calculations or experimental tests. In terms of numerical calculation, engineers apply combustion gas compositions, exact inlet and outlet boundary conditions to its numerical domains. In case of cooled turbine, they should consider secondary air and cooling air.
덕트 형상 변화가 축류 가스터빈 배기 디퓨져 성능에 미치는 영향
이익상(Iksang Lee),안윤호(Yunho An),김중석(Joung Seok Kim) 대한기계학회 2016 대한기계학회 춘추학술대회 Vol.2016 No.12
In this paper, the aerodynamic performance of an axial gas turbine exhaust diffuser is investigated as duct angle is changed. This diffuser consists of an annular diffuser and duct. Steady 3D CFD simulations with SST turbulence model using ANSYS CFX have been carried out to analyze effect of duct angle. The performance of the diffuser was assessed in terms of static pressure coefficient and total pressure loss along the diffuser. Duct angle depended on total length of duct. Performance of exhaust diffuser was significantly improved as duct angles were changed. Also, increasing duct angle and length reduced a range of recirculation zone at duct outlet. It effects on increasing static pressure within whole diffuser system.
김인겸(Inkyom Kim),안윤호(Yunho An),김중석(Joung Seok Kim) 대한기계학회 2016 대한기계학회 춘추학술대회 Vol.2016 No.12
Squealer tip is a well-known design method to reduce the tip leakage flow and increase the turbine efficiency. Various studies have been conducted to find the optimum squealer tip design or to analyze the flow phenomena. In the present study, a numerical analysis using ANSYS CFX was conducted to find an optimum squealer tip design. Various combination of tip gap heights from 0.5% to 2.0% span and squealer tip heights from 0.5% to 5.8% span were analyzed and the results were compared to the wind tunnel test results of the same squealer tip geometry. All of the numerical results over predicted the total pressure loss coefficient but showed similar trends. The squealer tip design of tip gap 1.0% span and squealer tip 1.9% span was selected as the optimum design, excluding those with tip gap 0.5% span which could cause rubbing, and a loss reduction of 8.6% was shown compared to the plane tip design with same tip gap.