PIV applications

SLIDE 1 | Kim D. Jensen| USP March 2013A Nova Instruments company

PIV applicationsPresentation of a select range of PIV applications.Historic review of measurements then and now.


Aerospace

• Aircraft model aerodynamics• Wing design (drag & lift) • Trailing vortices • Helicopter rotor design•Super sonic flows•Gas turbine fuel injection & cooling• Flight cabin ventilation• Validation of CFD models

# 33356


Automotive

• Car body aerodynamics• Air flows in passenger compartments

• Engine compartment flows

• Engine combustion


Bio-medical and bio-technology

Artificial hearts

Hart-valve function

Blood flows

Medicine inhalers

Micro fluidics Flow in biological valve, Prof. Roberto Zenit UNAM, Mexico City


Combustion Diagnostics

• Fuel injection• Air/fuel mixing• Combustion efficiency• Cooling efficiency• Rocket engineering• Flame research


• Sedimentation & particle transport• Wave dynamics• Mass transport

Earth science & environmental protection


Fundamental fluid dynamics research

Turbulence research

Boundary layers

Fluid-structure interactions

Vortex evolution

Heat transfer studies

Super sonic flows

CFD code validation


Hydraulics & hydrodynamics

• Ship hull design (hydrodynamics)• Propulsion efficiency• Pipe & channel flows• Flows in pumps• Cavitation prevention (propellers)• Cooling performance


Mixing processes

Research in mixing processes

Flow in industrial mixers

Micro mixers


Process and chemical engineering

• Cyclone separators• Heat exchangers• Liquid metal flows (moulds)


Data presentation from select applications


Stimulated air jet

• Ø30 air jet stimulated by a loud speaker

• Velocity: ~2.7 m/s• Lens: 60mm/#F2.8• S=500mm

(Distance between light sheet and lens)

• 2-3µm oil droplet seeding• Field of view:

82x103 mm at 1024x1280 pixel

Fan

Loud speaker

Grid

Jet


Jet flow without stimulation

• RMS of the v- velocity component

• Vorticity based on 250 Hz PIV

Strongreflection


Flow with 45 Hz stimulation


RMS V - velocity component

• RMS v - flow with45 Hz stimulation

• RMS v - flow without stimulation


PIV testing at HSVA Towing tank, Germany

Rudder

PIV system Camera Laser


HSVA Towing tank measurementTracking the vortex from a rudder


Travelling of the tip vortex


PIV in towing tank moving with carriage


The professional presentation makes it look simple


PIV under a microscope

Pump

Microscope Lens, High NA

Microfluidic device

Inlet Outlet

Ocular

12 bit InterlineCooled CCD Camera

Max ~5 mJ

Lamp

Filter cubeEpi-fluorescent Prism

Flow + Tracing Particles

= 532 nm

= 560 nm

Waste

Relay lens

Beam splitter

Optics for lamp / fiber

Nd: YAG Laser

Optical fiber


Micro channel Experiments

30 m

xz

x

y

300 m

Top View

Side View

MeasurementArea


Micro channel Flow (x - z plane)

Courtesy: Meinhart et. Al.


Results at X63 measurement

Measurement area


Results at X63 measurement

• Magnification X63 (X0.5) = X31.5

• Time between laser pulses 200 µs

• Measurement volume 14 x 14 x 8 µm

• Vectors spaced 3.4 µm


Micro PIV mixing Time resolved


Rotating disk experiment


Some times a Cartesian grid does not suffice


Some experiments makes you wonder


Shadow Sizing

Spatial distribution, cumulative histogram and table for data analysis

Spray analysis


Shadow Sizing of bubbly flow


Flow-Structure interaction

• Flow-Structure solid interaction has been research topic for many years.

• Areas of application include:- Aero-elasticity- Bridge design- Building design- Micro air vehicle

• Measurement of deformation of and flow behind a flexible winglet.- Flow Measured with TR-PIV- Deformation measured with Digital Image Correlation (DIC)- DIC is a optical technique for Time Resolved (TR-DIC)

measurement of 3-D deformation and strain


Flexible wing and it’s influence on flow

• Optical measurements of real time Deformation of a Flexible Wing and the associated Flow behind a flexible wing.

• The wing has one spare and 4 ribs over which is latex membrane is mounted with adhesive (5.7x3)

• Curtsey Mr. Ryan Wallace and Prof. Mark Glauser of Syracuse University


Wing layout and area of investigation

Image of full wing, placed in wind tunnel.Flow 14 m/s angle of attack 4 deg

Flow field measured by TR-PIV

Temporal resolution on TR-DIC and TR-PIV measurements: 1 ms (1kHz)


TR-DIC measurements on wing

Z displacement

-2

-1

0

1

2

3

4

5

1 51 101 151 201 251 301 351 401 451

ms

mm

Z displacement

-1

0

1

2

3

4

5

0 5 10 15 20 25 30 35 40 45 50

ms

mm


Point spectral information

• Z-displacement spectral in formation from a point

Spectrum

-0.2

0

0.2

0.4

0.6

0.8

1

1.2

1.4

1.6

1.8

2

0.0 55.6 111.1 166.7 222.2 277.8 333.3 388.9 444.4 500.0

Hz

Dis

pla

cem

ent

Spectrum (zoom)

0

0.2

0.4

0.6

0.8

1

1.2

1.4

1.6

1.8

2

60.0 66.7 73.3 80.0 86.7 93.3 100.0 106.7 113.3 120.0 126.7 133.3 140.0

Hz

Dis

pla

cem

ent


TR-PIV Flow measurements behind wing

Flow field behind wing and associated spectrum

Frequency contents of Flow after wing

-0.05

0

0.05

0.1

0.15

0.2

0.25

0.3

70 75 80 85 90 95 100 104 109 114 119 124 129 134

FrequencyU

@ 9

,15


Comparison of frequency contents between Structure and Flow

Spectrum mean over surface

-0.05

0

0.05

0.1

0.15

0.2

0.25

0.3

0.35

0.4

0.0 55.6 111.1 166.7 222.2 277.8 333.3 388.9 444.4 500.0

Hz

Dis

pla

cem

ent

Frequency contents of flow after wing

-0.01

0

0.01

0.02

0.03

0.04

0.05

0.06

0.07

0.08

70 75 80 85 90 95 100 104 109 114 119 124 129 134

Frequency

U @

9,1

5


A closer look at the PIV data from behind the flexible wing


Flow measurements then and now

• Today we take many things for granted• How have we advanced?• Let’s have a quick review


1981 LDA underwater measurements

PIV underwater measurements

Maritime research, Propellers in towing tanks


Airborne studies

1977 Hotwire in-flight measurements at high altitude and speed

Airborne LDA measurements

Combustion in Micro-gravity with a PIV system onboard


Understanding tip vortices in detailswith PIV measurements in water

Wingtip vortices, then and now

x/b=6.80.2 nm

K. & C. Huenecke, Airbus

x/b=30.00.9 nm

x/b=63.02.0 nm

1962 CTA measurements in open air,waiting for the fly-by of the aircraft


On the way to micro applications

1965 CTA in a “microfluidic” bi-stable fluid amplifier

Flow Discharge Vectoring using a Miniature Fluidic Actuator mapped with PIV


When it gets bloody !

1970 CTA built into a hypodermic needle, used in patients to verify results after operation

Microscopic PIV in a 30 x 100 µm wide channel with real human blood

wall

100

µm

wid

e

30 µm deep


Thermodynamics in combustion

1956 The PV indicator revolutionized combustion understanding. Now, the thermodynamic work was online !

LIF measurement in an engineat different crank angles

Result: PV diagram for all crank angles

Modern day developments requires much more detail and advanced imaging


We can see it - quantification of bubbles with advanced image processing

1967 Investigation of a hot film and bubble interaction

Quantification of bubbles with shadow sizing techniques


Jet flow still the same 30 years later ?

1971 First commercial LDAinvestigated by F. Durst and J. Whitelaw

2001 First commercialTime Resolved PIV system based on fast powerful Nd:Yag lasers

1971: 5 mWatt laser2001: 50 Watt laser & more information

Documents

PIV applications