at Lewis FieldGlenn Research Center

Flow Control Actuation

Workshop at Ohio Aerospace Institute, Cleveland OHNov. 6-7, 2007

Dennis CulleyPh: (216) 433-3797

email: dennis.e.culley@nasa.govhttp://www.lerc.nasa.gov/WWW/cdtb

at Lewis Field2Glenn Research Center

• Team Members• Compressor Flow Control Overview• Flow Control Actuation Systems & Experimental Results• Fluidic Actuators• High Temperature Shape Memory Alloy Actuators

Outline

at Lewis Field3Glenn Research Center

Team Members

Dennis Culley Controls & Dynamics BranchRandy Thomas Controls & Dynamics BranchJon DeCastro Arctic Slope Regional Corp (ASRC)Doug Feikema Combustion & Reacting Systems Branch Suleyman Gokoglu Combustion & Reacting Systems Branch

at Lewis Field4Glenn Research Center

Circ

umfe

rent

ial l

ocat

ion

Total PressureCoefficient

Circ

umfe

rent

ial l

ocat

ion

Total PressureCoefficient

Circ

umfe

rent

ial l

ocat

ion

Total PressureCoefficient

80% span 50% span 20% span

NominalHighly Loaded

Compressor Separation

• Induce separation via blade stagger change and reduced flow coefficient• Quantify separation by surveying total pressure ( Pt ) downstream of blades

Suction surface separationis inferred from changes in wake width and depth

at Lewis Field5Glenn Research Center

Solenoid Actuation System

HUB

Massflow

Controller / Meter

External Air Supply

Valve

Controller

1U

ju ju ju 1jetu

TIP

Accumulator

time

Interleaved valve signal

2Tτ

Solenoidswith rapid prototype stator vane

at Lewis Field6Glenn Research Center

1.75Steady vs. Unsteady Injection

Vane Pitch ( % )

Tota

l Pre

ssur

e C

oeffi

cien

t, C

pt

0.21%

0.25%

0.29%

0.17%core mass flow

1.35

1.70

1.65

1.60

1.55

1.50

1.45

1.40

0.06%

0.07%

0.08%

0.09%

0.05%core mass flow

BaselineUnsteady

Steady

at Lewis Field7Glenn Research Center

50% Duty CycleImpulsive Injection Effectiveness

% Core Mass Flow

Cha

nge

in B

asel

ine

Loss

-35%

-30%

-25%

-20%

-15%

-10%

-5%

0%

5%

0.00% 0.04% 0.08% 0.12%

1.95 800

1.71 700

1.34 550

1.22 500

0.98 400

0.67 275

F+ f

Impulsive Injection in Compressor Stator

at Lewis Field8Glenn Research Center

Flow Control ReferencesA Study of Stall Control over an Airfoil Using 'Synthetic Jets‘, K. Zaman and D. Culley, NASA Glenn Research Center, Cleveland, OH, AIAA-2006-98, 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, Jan. 9-12, 2006Separation Control in a Multistage Compressor Using Impulsive Surface Injection, D.W. Wundrow, Ohio Aerospace Institute, E.P. Braunscheidel, D.E. Culley, M.M. Bright, NASA Glenn Research Center, NASA TM- 214361, 2006Impulsive Injection for Compressor Stator Separation Control, D. Culley, E. Braunscheidel and M. Bright, NASA Glenn Research Center, Cleveland, OH AIAA-2005-3633, 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Tucson, Arizona, July 10-13, 2005Active Flow Separation Control of a Stator Vane Using Embedded Injection in a Multistage Compressor Experiment, Culley, Dennis E. (NASA Glenn Research Center); Bright, Michelle M.; Prahst, Patricia S.; Strazisar, Anthony J. Source: Journal of Turbomachinery, v 126, n 1, January, 2004, p 24-34

at Lewis Field9Glenn Research Center

Actively Controlled Fluidic Actuators

Control Point B

Control Surface A

Splitter

Outlet A

Control Port A

Nozzle

Control Port B

Outlet B

Rapid prototyped fluidic actuators with solenoid operators

at Lewis Field10Glenn Research Center

Current Efforts

SFW Turbomachinery Flow Control task experiments and analytical & computational models

Modeling of the transient switching performance of the fluidic actuator

Plasma controlled fluidic actuator

at Lewis Field11Glenn Research Center

High Temperature Shape Memory Alloy Actuators

Dynamic response of SMA actuators

SBIR success story

Miga Motors

HTSMA actuator developed for T700 engine

HTSMA actuator installed in T700 engine

at Lewis Field12Glenn Research Center

Active Flow Control Actuation Research & Development

Component Rig & Wind Tunnel Test

-- Separation ControlSeparation Control-- Stability ControlStability Control

Variable FrequencyPlasma-Fluidic

High TemperatureShape Memory Alloy

Passive Fluidic

Solenoid

Rotary

Voice Coil

Rapid Prototyping

InnovationInnovationDesign Design

TestTest

at Lewis Field13Glenn Research Center

Actuator References

Development of a HTSMA-Actuated Surge Control Rod for High- Temperature Turbomachinery Applications, Padula, S, Noebe, R, Bigelow, G., Culley, D., et al, 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Honolulu, Hawaii, Apr. 23-26, 2007Variable Frequency Diverter Actuation for Flow Control, D. Culley, NASA Glenn Research Center, Cleveland, OH, AIAA-2006-3034, 3rd AIAA Flow Control Conference, San Francisco, California, June 5-8, 2006

at Lewis Field14Glenn Research Center

Opportunities for Collaboration

Collaborative Opportunities

Fabrication and micro-machining

Materials development

Electronic circuit development and miniaturization

Electric and magnetic field analysis

Computational fluid dynamics (CFD) model development

Experimental applications and testing

SFW Funded Opportunities

Currently there are no funded opportunities within SFW

at Lewis Field15Glenn Research Center

Future Plans

Continue the effort to develop, expand, and refine techniques for active flow control in aero-engine applications through multi-disciplinary collaboration.

Goals

• Through improved understanding, develop the design tools which will enable the practicable use of flow control in a wider breadth of aero-engine applications.

• Deliver realistic and reliable actuation technologies for embedded, point-of-use flow control in the aero-engine environment.