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Investigation of Effects of the Characteristic Parameters on the Rotor-stator Cavity System with Pre-swirl Flow

Author: MengXiangHai
Tutor: WangSuoFang
School: Nanjing University of Aeronautics and Astronautics
Course: Thermal Power Engineering
Keywords: Turn - static pelvic Prewhirl Flow ratio The prewhirl temperature drop Total pressure coefficient Numerical Simulation
CLC: V233.5
Type: Master's thesis
Year: 2009
Downloads: 35
Quote: 0
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Abstract


Aero-engine pre-swirl cooling technology can effectively improve the cooling efficiency of the air-conditioning on high temperature turbine components , in order to ensure the reliability of the engine and extend its life. However, due to the complexity of the structure of the actual engine turbine disk cavity , through the conclusion of the rules Pelvic Institute of Research on the Structure of certain limitations , In complex structure prewhirl into the cavity of the gas disk has important theoretical significance and practical engineering . value. Research background and current status of the pre-swirl cooling carried out a systematic study of the complex with three outlet turbine rotor - stator cavity close to the actual structure of the pre - spin system . First, the FLUENT software pelvic system of pre-swirl flow in proportion to the allocation of pre- spin temperature drop and the total pressure coefficient of the characteristic parameters change . The characteristic parameters including plate spacing, pre-swirl angle , rotation Reynolds number , dimensionless mass flow rate , the intake of total temperature . And according to the existing conditions of the laboratory , the preliminary design of the the complex the pelvic prewhirl system test system , and to prepare for subsequent trials research . The numerical simulation results show that : 1 ) disk spacing has little effect on the flow distribution ratio ; 2) pre-swirl angle of the flow distribution ratio of less impact ; 3) rotation Reynolds number flow distribution ; 4 ) geometry changes in flow distribution the larger ; 5 ) when the rotation Reynolds number increases , the dimensionless total temperature and total pressure coefficient decreases ; 6) With the increase in the total temperature of the intake , the the dimensionless total temperature and total pressure coefficients are gradually increasing ; 7) , dimensionless total temperature gradually decreases with increasing mass flow , the total pressure coefficient is gradually increasing ; 8) With the plate spacing increases the dimensionless total temperature and total pressure coefficient are first decreases and then increases ; 9 ) with the pre-swirl angle increases , the the dimensionless total temperature gradually decreases , total pressure coefficient increases gradually . The results of this research provides a theoretical basis for guiding the design of the actual pre - precessing gas turbine disc cavity structure .

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CLC: > Aviation, aerospace > Aviation > Aero-engine ( propulsion system ) > Engine attachment system > Cooling system
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