The aerodynamics of a baseline supersonic throughflow fan rotor

335 Pages·2016·8.62 MB·English

by  Daniel Lawrence Tweedt

Iowa State University Capstones, Theses and
Retrospective Theses and Dissertations
Dissertations
1993
The aerodynamics of a baseline supersonic
throughflow fan rotor
Daniel Lawrence Tweedt
Iowa State University
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Recommended Citation
Tweedt, Daniel Lawrence, "The aerodynamics of a baseline supersonic throughflow fan rotor " (1993).Retrospective Theses and
Dissertations. 12194.
https://lib.dr.iastate.edu/rtd/12194
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The aerodynamics of a baseline
supersonic throughflow fan rotor
by
Daniel Lawrence Tweedt
A Dissertation Submitted to the
Graduate Faculty in Partial Fulfillment of the
Requirements for the Degree of
DOCTOR OF PHILOSOPHY
Department: Mechanical Engineering
Major: Mechanical Engineering
Approved:
Signature was redacted for privacy.
In Charge of Major Work
Signature was redacted for privacy.
For the Major Department
Signature was redacted for privacy.
For the Graduate CoUege
Iowa State University
Ames, Iowa
1993
mil Number; 9941784
UMI Microform 9941784
Copyright 1999, by UMI Company. All rights reserved.
This microform edition is protected against unauthorized
copying under Title 17, United States Code.
UMI
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ii
TABLE OF CONTENTS
SYMBOLS AND NOTATION iv
ABSTRACT vii
CHAPTER 1. INTRODUCTION I
The Supersonic Throughflow Fan Engine 2
Historical Considerations of Supersonic Compressor Development 6
NASA Lewis Supersonic Throughflow Fan Program 9
Purpose and Scope of Dissertation 11
CHAPTER 2. BASELINE FAN DESIGN 13
Design Philosophy and Approach 13
Description of Fan Design 15
CHAPTER 3. EXPERIMENTAL FACILITY 21
Description of Facility 21
Facility Instrumentation and Data Acquisition 26
Data Reduction 31
CHAPTER 4. COMPUTATIONAL FLUID DYNAMICS 35
Description of Codes 36
Application of Codes 39
CHAPTER 5. ROTOR OPERATING CHARACTERISTICS
AND PERFORMANCE 56
One-Dimensional Steady-Flow Analysis 58
Subsonic Throughflow Operation 77
Axial-Subsonic Rotor-Inflow Characteristics 82
Rotor Inflow Starting and Unstarting 112
iii
Impulse-Type Operation 149
Supersonic Throughflow Operation 169
Shock-in-Rotor Operation 215
CHAPTER 6. CONCLUDING REMARKS 219
REFERENCES 225
ACKNOWLEDGEMENTS 233
APPENDIX A. SUPERSONIC NOZZLE PERFORMANCE
AND EXIT FLOW QUALITY 235
APPENDIX B. PROBLEMS IN COMPARING COMPUTATIONAL
AND EXPERIMENTAL RESULTS 250
APPENDIX C. AVERAGING METHODS FOR
COMPUTED FLOW FIELDS 263
APPENDIX D. APPROXIMATE TWO-DIMENSIONAL
CALCULATION METHODS 275
APPENDIX E. A TOTAL-PRESSURE LOSS MODEL FOR
SUPERSONIC THROUGHFLOW FAN
BLADE ROWS 290
iv
SYMBOLS AND NOTATION
A cross-sectional area of stream-tube or duct
a sonic speed; half-thickness of blade leading edge
c aerodynamic chord
h specific enthalpy; streamtube height
M. Mach number
m meridional location
m mass flow rate
N rotational speed in revolutions per unit-time
Pr Prandtl number
p static pressure
r —
R gas constant; annulus height fraction =
^tip ^hub
Re Reynolds number
r radial location; radius
s circumferential blade spacing; specific entropy
T absolute static temperature
U circumferential blade speed
V velocity magnitude
X axial location
a absolute circumferential flow angle with respect to meridional flow direction; flow
"yaw" angle measured by a cone probe or rake element
p relative circumferential flow angle with respect to meridional flow direction
Y ratio of specific heats
5 deviation angle; flow deflection angle through an oblique shock wave
e ellipse eccentricity parameter
V
fan adiabatic efficiency
rotor adiabatic efficiency
0 circumferential location; oblique shock wave angle; fan inlet total-temperature
correction parameter = /518.7 (temperature in °R)
1 incidence angle
K blade metal angle
X area blockage factor = 1 — /A)
|i Mach angle = sin~V1 /M)
J —
V Prandtl-Meyer angle = ^—j^tan ~ 1) ~ ^ 1
p static density
cj blade element solidity = c/s
-(Y+1)/(2Y-2)
V — 1 1
{]) dimensionless mass-flux parameter = M
Q rotational speed in radians per unit-time
\\f meridional flow angle with respect to axial direction; flow "pitch" angle measured
by a cone probe or rake element
.
Par Pa
CO total-pressure loss coefficient = —=—
Pti-Pi
Subscripts
ax component in axial or meridional direction
cb nozzle centerbody
d design condition
e free-stream or boundary-layer-edge condition
ejf condition which effectively exists
eq equivalent condition
hub annulus hub condition or quantity
vi
i condition reached through an isentropic process
le leading edge condition or quantity
m component in meridional direction
N nozzle condition or quantity
p Pitot condition, which for supersonic flow is the total condition downstream of a
steady normal shock introduced actually or hypothetically into the flow field
ps blade pressure-surface quantity
R rotor quantity
r component in radial direction
ss blade suction-surface quantity
t total condition
tip annulus tip condition or quantity
X component in axial direction
0 component in circumferential direction
* critical (sonic flow) condition
0 plenum condition; station within nozzle; aircraft flight condition
1 upstream condition; station at rotor inlet (nozzle exit)
2 downstream condition; station at rotor exit
Superscripts and Diacritics
q ' condition or quantity relative to blade
q average quantity
q energy-average quantity from a circumferential integration (see Appendix C)
q momentum-average quantity from a circumferential integration (see Appendix C)
q entropy-average quantity from a circumferential integration (see Appendix C)
^q entropy-average quantity from a spanwise integration in an axisymmetric flow
field (see Appendix C for general notation)
q overall entropy-average quantity from a circumferential and spanwise integration
in a three-dimensional flow field (see Appendix C for general notation)