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Performance Mathematic Model and Operation Characteristic Analysis for Turbine Based Combined Cycle Engine

Author: LiLong
Tutor: LiangDeWang；HuangGuoPing
School: Nanjing University of Aeronautics and Astronautics
Course: Aerospace Propulsion Theory and Engineering
Keywords: Hypersonic vehicle Turbine -based combined cycle Aero Engine Modeling Performance Analysis Numerical Simulation
CLC: V231.3
Type: Master's thesis
Year: 2008
Downloads: 327
Quote: 0
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Abstract


Turbine based combined cycle (Turbine-Based-Combined-Cycle, TBCC) engine with superior ballistic performance, power air-breathing hypersonic vehicle, which can be applied with a wide range of application prospects in the civil and military aerospace field . To establish the the TBCC engine overall performance of the model in a hypersonic vehicle program selection, have a very important role in promoting the study of the overall system design, engine operating characteristics of the machine and related components analysis. In this paper, the proposed one-dimensional flow path analysis method, preliminary building the the TBCC overall performance analysis framework and establish the TBCC overall performance computational model based on the engine component characteristics, the use of C language development of calculation software. Complete the calculation of the steady-state performance of the combination of the engine under the typical operating mode, analysis of the combination of engine performance parameters of the line along the flight path variation. Through this work, the characteristic curve of the turbine engine work, concluded with the aero-engine matches the classical theory. Match inlet and engine nozzle and aircraft after the body work together in the analysis, this paper established a mathematical model of a parallel combination of engine intake and exhaust systems. Inlet and nozzle performance and its variation in the different modal analysis, a preliminary discussion of the interaction in the intake and exhaust components work together. Aerodynamic parameters as compared to the inlet export target, calculate the inlet and CFD results compared, the calculated results are consistent with the physical laws of the inlet work presented in this paper, in addition to the design point total pressure recovery coefficient indicators, and other parameters error substantially does not exceed 10%. According to the calculation results, the influence of the ramjet combustor operating pressure changes on the overall performance of the engine, a preliminary discussion of the hazards of the pressure pulsation of the combustion chamber of the engine work, and the allowable range of the design of the combustion chamber pressure pulsation. Finally, the overall performance of the transition states of the combined engine exploratory study. Flow distribution ratio change to the engine conditions, analysis of the variation of the performance parameters of the combination of an engine transition segment, determining Off vehicle position of the turbine engine. The main reason for the attenuation of the relay operating point of the engine performance, the initial program to improve the stability of the engine work.

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CLC: > Aviation, aerospace > Aviation > Aero-engine ( propulsion system ) > Engine theory > Aero-engine gas mechanics
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