Journal of Jilin University(Engineering and Technology Edition) ›› 2022, Vol. 52 ›› Issue (7): 1561-1573.doi: 10.13229/j.cnki.jdxbgxb20210114

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Numerical simulation and experiment on ultrasonic deicing system of airfoil structure

Zhong-hua SHI(),Quan-wei SONG,Zhen-hang KANG,Qiang XIE,Ji-feng ZHANG()   

  1. College of Aerospace and Civil Engineering,Harbin Engineering University,Harbin 150001,China
  • Received:2021-02-05 Online:2022-07-01 Published:2022-08-08
  • Contact: Ji-feng ZHANG E-mail:szhongh@hrbeu.edu.cn;jfzhang@hrbeu.edu.cn

Abstract:

Numerical and experimental methods were used to study the NACA 0015 airfoil structure ultrasonic deicing system. For the ice-coated double-layer plate model, the effects of the thickness and Young's modulus of ice layer on the interface shear stress concentration coefficient (ISCC) and deicing frequency were explored by the global matrix method (GMM). At the same time, specific piezoelectric actuators were designed based on the theoretical research results and the accuracy of the finite element simulation was verified by the impedance curve. Finally, according to the geometric characteristics of the airfoil, the location of piezoelectric actuators and deicing efficiency were studied. Related deicing experiments were conducted to verify the feasibility of the ultrasonic deicing system. The experimental results showed that the deicing power of this airfoil structure is only around 16% of the traditional electro-thermal deicing.

Key words: solid mechanics, airfoil structure, ultrasonic deicing, global matrix method, interface shear stress concentration coefficient, deicing efficiency, deicing experiments

CLC Number: 

  • V244.1

Table 1

Material proprieties"

材 料

密度/

(kg·m-3

杨氏模量/

GPa

泊松比
2700700.27
9209.10.28

Fig.1

Dispersion curve and ISCC value of 1 mm airfoil with 1 mm ice"

Fig.2

Effect of ice thickness on deicing frequency and high ISCC value range"

Fig.3

Effect Young's module of ice on deicing frequency and high ISCC value range"

Fig.4

NACA 0015 airfoil scaled-down wing model wing leading edge"

Fig.5

Finite element diagram of verification model and physical diagram of verification model"

Fig.6

Comparison of experimental and finite element impedance curves"

Fig.7

Calculation model of iced airfoil with piezoelectric wafer placed at 10% of wing chord length"

Table 2

Maximum adhesive layer thickness when piezoelectric wafer at different installation locations"

压电片直径/mm弦长位置/mm
6090120150
501.1090.6820.4860.369
601.6180.9990.7030.535

Fig.8

Transformation relationship between global and local coordinates of airfoil"

Fig.9

Mapped coordinate system of ice interface"

Fig.10

Displacement of airfoil and shear stresses at interface of ice layer when 50 mm piezoelectric wafers installed at different locations of airfoil"

Fig.11

Displacement of airfoil and shear stresses at interface of ice layer when 60 mm piezoelectric wafers installed at different locations of airfoil"

Fig.12

DEF values of 50 mm piezoelectric wafers at different locations"

Fig.13

DEF values of the 60 mm piezoelectric wafers at different locations"

Fig.14

Total shear stress of the piezoelectric wafers at different locations"

Fig.15

Location of piezoelectric wafers inside airfoil"

Fig.16

Deicing experimental setup"

Fig.17

Deicing process of 50 mm piezoelectric wafer ultrasonic deicing system and comparison of experimental and simulation results"

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