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Application of Tomo-PIV in a large-scale supersonic jet flow facility

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Abstract

Particle imaging velocimetry (PIV) has been used extensively at NASA GRC over the last 15 years to build a benchmark data set of hot and cold jet flow measurements in an effort to understand acoustic noise sources in high-speed jets. Identifying the noise sources in high-speed jets is critical for ultimately modifying the nozzle hardware design/operation and therefore reducing the jet noise. Tomographic PIV (Tomo-PIV) is an innovative approach for acquiring and extracting velocity information across extended volumes of a flow field, enabling the computation of additional fluid mechanical properties not typically available using traditional PIV techniques. The objective of this work was to develop and implement the Tomo-PIV measurement capability and apply it in a large-scale outdoor test facility, where seeding multiple flow streams and operating in the presence of daylight presents formidable challenges. The newly developed Tomo-PIV measurement capability was applied in both a subsonic M 0.9 flow and an under-expanded M 1.4 heated jet flow field. Measurements were also obtained using traditional two-component (2C) PIV and stereo PIV in the M 0.9 flow field for comparison and validation of the Tomo-PIV results. In the case of the M 1.4 flow, only the 2C PIV was applied to allow a comparison with the Tomo-PIV measurement. The Tomo-PIV fields-of-view covered 180 × 180 × 10 mm, and the reconstruction domains were 3500 × 3500 × 200 voxels. These Tomo-PIV measurements yielded all three components of vorticity across entire planes for the first time in heated supersonic jet flows and provided the first full 3D reconstruction of the Mach disk and oblique shock intersections inside of the barrel shocks. Measuring all three components of vorticity across multiple planes in the flow, potentially reduces the number of measurement configurations (streamwise and cross-stream PIV) required to fully characterize the mixing-enhanced nozzle flows routinely studied in aeroacoustics research.

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Abbreviations

ω x , ω z :

x- and z-components of vorticity (1/s)

D j :

Nozzle jet inside diameter (mm)

M :

Mach number

ppp :

Seed particle concentration (particles/pixel)

r :

Radial coordinate from the jet centerline

P 0 :

Stagnation pressure in the jet

P ∞ :

Ambient pressure

u′ :

rms variation in the u-component of the jet velocity (m/s)

U :

Axial component of the jet velocity (m/s)

U ideal :

Isentropic jet exit velocity (m/s)

U j :

Centerline jet velocity at the exit plane (m/s)

x M :

Distance from nozzle exit to Mach disk (mm)

AAPL:

Aero-Acoustic Propulsion Lab

ART:

Algebraic reconstruction technique

LES:

Large eddy simulation

MART:

Multiplicative algebraic reconstruction technique

NPR:

Ratio of the stagnation pressure of the jet to the ambient pressure

NTR:

Ratio of the stagnation temperature of the jet to the ambient temperature

RANS:

Reynolds averaged Navier–Stokes solution

rms:

Root mean square

SART:

Simultaneous algebraic reconstruction technique

SHJAR:

Small hot jet acoustic rig

SMC:

Simple metal chevron

SNR:

Signal-to-noise ratio

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Acknowledgements

The author would like to thank NASA’s Fundamental Aeronautics’ Transformational Tools and Technologies Program for their support of this effort. The author also thanks Dr. Randy Locke, Dr. Adam Wroblewski and Garrett Clayo for their efforts in the setting up and implementation of the 2C PIV, SPIV and Tomo-PIV systems. The author thanks Dr. James Bridges for helpful discussions and for the use of the SHJAR facility. Lastly, the author thanks the staff at the AAPL for their dedication and support in making these tests possible.

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  1. NASA Glenn Research Center, Cleveland, OH, 44135, USA

    Mark P. Wernet

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Correspondence to Mark P. Wernet.

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Wernet, M.P. Application of Tomo-PIV in a large-scale supersonic jet flow facility. Exp Fluids 57, 144 (2016). https://doi.org/10.1007/s00348-016-2228-3

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  • DOI: https://doi.org/10.1007/s00348-016-2228-3

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