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A two-dimensional temperature correction method for pressure-sensitive paint measurement on helicopter rotor blades

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Abstract

Pressure-sensitive paint (PSP) has become an important technique for global pressure measurement on rotating surfaces such as helicopter rotor blades. Due to the temperature sensitivity of PSP, it is essential to apply accurate temperature correction method in PSP measurements. In previous studies, one-dimensional (1D) correction methods were generally adopted which only considered the radial temperature gradient on the blade. However, in the current study, it was found that the systematic error of this 1D assumption was non-negligible in large-scale experiments due to the growing chordwise temperature gradient. Accordingly, a two-dimensional (2D) temperature correction method considering both radial and chordwise temperature gradients was developed to improve the accuracy of PSP. In this method, a 2D temperature map was firstly generated based on the TSP results. Calibrations were then conducted under a series of temperature and pressure values to generate a calibration surface. According to the calibration results, the pressure and temperature fields on the rotor blade were solved directly. The proposed 2D method was validated through PSP measurements on a 2 m diameter BO-105 helicopter rotor in hover. Compared with 1D temperature correction, the results from the current method showed clearly improved agreement with the CFD results and reduced overall measurement error.

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Abbreviations

A(T):

Stern–Volmer coefficient

B(T):

Stern–Volmer coefficient

C :

Rotor blade chord

C p :

Pressure coefficient

E R :

Random error

E s :

Systematic error

E T :

Total error

F c :

Modified-convective flux

F v :

Viscous flux

I :

Intensity

I ref :

Intensity at reference condition

I 1 :

Intensity in Gate 1

I 2 :

Intensity in Gate 2

M l :

Local Mach number

M ∞ :

Freestream Mach number

P :

Pressure

P ref :

Pressure at reference condition

P 0 :

Total pressure

P ∞ :

Freestream pressure

R :

Rotating radius

T :

Temperature

T aw :

Adiabatic wall temperature

T 0 :

Total temperature

T ∞ :

Freestream temperature

W :

Conservation variable

k :

Specific heat ratio

n :

Normal direction

r :

Recovery factor

t :

Time

x :

Space coordinate

y :

Space coordinate

θ :

Collective pitch

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Acknowledgements

This work is supported by funding from National Natural Science Foundation of China (NSFC Nos. 11725209 and 11872038).

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Authors and Affiliations

  1. Key Lab of Education Ministry for Power Machinery and Engineering, School of Mechanical Engineering, Shanghai Jiao Tong University, Shanghai, 200240, China

    Lingrui Jiao, Xu Liu, Di Peng & Yingzheng Liu

  2. Gas Turbine Research Institute, Shanghai Jiao Tong University, Shanghai, 200240, China

    Lingrui Jiao, Xu Liu, Di Peng & Yingzheng Liu

  3. China Aerodynamics Research and Development Center, Mianyang, 621000, China

    Zheyu Shi, Weiguo Zhang & Lei Liang

  4. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, 210016, China

    Xi Chen & Qijun Zhao

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  1. Lingrui Jiao
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  2. Xu Liu
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  3. Zheyu Shi
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  4. Weiguo Zhang
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  8. Di Peng
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  9. Yingzheng Liu
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Correspondence to Zheyu Shi or Di Peng.

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Jiao, L., Liu, X., Shi, Z. et al. A two-dimensional temperature correction method for pressure-sensitive paint measurement on helicopter rotor blades. Exp Fluids 61, 104 (2020). https://doi.org/10.1007/s00348-020-2929-5

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  • DOI: https://doi.org/10.1007/s00348-020-2929-5

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