The effect of different protrusion amounts on various parameters (static pressure
total pressure
sealing efficiency) was experimentally studied by measuring carbon dioxide volume fraction
so as to obtain the change rule of the sealing efficiency and the minimum flow rate of sealing air of different sealing structures. In the experiment
the experimental parameters of different dimensionless sealing flow rates were measured under the condition that the annulus Reynolds number and the rotating Reynolds number changed within a certain range. The results show that the change of the protrusions amount has little effect on the static pressure in the cavity
and the static pressure change near the sealing ring is almost negligible. The total pressure and sealing efficiency will increase with the increasing protrusion amount. However
the degree of change in the different sealing structures is different. As a whole
the efficiency of radial rim seal is most obvious
and the improvement of the axial rim seal and double teeth rim seal is less. For each additional protrusion
the minimum sealing flow rate required for each of the three structures can be reduced by 0.96%
0.30%
0.28%
respectively. In addition
the rotating Reynolds number will have a more significant effect on the sealing efficiency after the protrusions are installed.
Numerical investigation on influence of sealing clearance on sealing performance
Experiment on multitooth rim sealing.
Experiment on gas ingestion on forward disk cavity of 1.5 stage turbine rig
Numerical simulation of rotationally-induced ingress through turbine rim seals
Volume fraction technique for measuring the minimum value of mass flow in turbine rotor-stator disk cavities
Related Author
LUO Qingyang
TAN Xiaoming
ZHANG Qingcai
徐国强
杜发荣
全永凯
康文武
罗翔
Related Institution
北京航空航天大学 能源与动力工程学院航空发动机气动热力国家级重点实验室
National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 1000191
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics