Virginia Grupo de Investigacion
Transcript of Virginia Grupo de Investigacion
-
8/22/2019 Virginia Grupo de Investigacion
1/34
Center for Turbomachinery
and Propulsion Research
Providing Research and Educational Programs in Turbomachinery and
Propulsion Science and Engineering
-
8/22/2019 Virginia Grupo de Investigacion
2/34
-
8/22/2019 Virginia Grupo de Investigacion
3/34
Table of ContentsTable of ContentsTable of ContentsTable of Contents
Table of ContentsTable of ContentsTable of ContentsTable of Contents
CENTER FOR TURBOMACHCENTER FOR TURBOMACHCENTER FOR TURBOMACHCENTER FOR TURBOMACHINERY ANDINERY ANDINERY ANDINERY AND
PROPULSION RESEARCHPROPULSION RESEARCHPROPULSION RESEARCHPROPULSION RESEARCH
1. Introduction 1
2. Recent and On-Going Projects
Acoustics and Active Control 2
Combustion and Active Control 3 - 4
Aerodynamics and Heat Transfer 5 - 11
Rocket Propulsion 12 - 13
Instrumentation and Sensor Development 14 - 16
Rotor Dynamics and Magnetic Bearings 17 - 18
3. Participating Faculty Members 19 - 25
4. Facilities 26
5. Sponsors 27
-
8/22/2019 Virginia Grupo de Investigacion
4/34
1
Introduction
The program of turbomachinery and propulsion research at Vir-
ginia Tech has provided research and educational service to indus-
try and government agencies for more than thirty years. Beginning
with the development of high-response instrumentation for on-
rotor pressure measurements in 1971, the program has expanded
dramatically. Research is conducted on a wide variety of turbo-
machinery fluidmechanics topics including:
Development of computational techniques for calculation of
turbomachinery flows
Research on sensors for flow and heat transfer measurements
Measurement and prediction of rotor dynamics
Blade vibration and seal performance
Large-scale aero and thermal measurements
Ramjet and rocket combustion
Optimization techniques for turbomachinery applications
The Center is organized to support and enhance the research ef-
forts of faculty and to provide increased research and educational
services. The faculty members pursue a comprehensive program
of relevant, fundamental research in the turbomachinery, gas tur-bine, and propulsion fields. In addition to individually sponsored
programs, the Center acts as a focal point for cooperative re-
search efforts between faculty and affiliate sponsors. The Center
promotes effective communica-tion between the two, and seeks to
encourage relevant activities. It works to support quality educa-
tion of graduate students in the turbomachinery and propulsion
areas.
-
8/22/2019 Virginia Grupo de Investigacion
5/34
Control of Inlet Noise from Turbofan Engines Using Herschel-
Qenke Waveguide Resonator,
Ricardo A. Burdisso
An innovative implementation of the Herschel-Quincke waveguides
(or tubes) concept for the reduction of tonal and broadband noise
from a turbofan engine is experimentally investigated. The
Herschel-Quincke tube con-
cept, applied to turbofan en-
gines, consists of installing
circumferential arrays of tubes
around the inlet of the turbo-
fan engine. The experimental
work is carried out on a Pratt
and Whitney JT15D turbofanjet engine. Single and multi-
ple circumferential arrays of
Herschel-Quincke tubes are
mounted around the inlet of the engine, and their effects on the
radiated noise are measured and oompared to the hard-walled
inlet case. The results on the JT15D
turbofan engine show reductions exceeding 8 dB in the blade pas-
sage frequency tone sound power levels. Experimental results also
show that the Herschel-Quincke technique is also very effective at
reducing the turbofan inlet broadband noise with sound power
reduction of up to 3 dB in the 0-3200 Hz frequency range.
JTI5D turbofan for engine experiments
Acoustic and Active Control
2
-
8/22/2019 Virginia Grupo de Investigacion
6/34
Acoustic Characterization and Modeling of Gas TurbineAcoustic Characterization and Modeling of Gas TurbineAcoustic Characterization and Modeling of Gas TurbineAcoustic Characterization and Modeling of Gas TurbineFlowtrainsFlowtrainsFlowtrainsFlowtrains, R.L. West, Uri VandsburgerR.L. West, Uri VandsburgerR.L. West, Uri VandsburgerR.L. West, Uri VandsburgerMethodologies have been developed for characterization of the
acoustic field in flow trains and combustors.These have been applied to lab developmentand industrial model combustors.In parallel acoustic modeling of the flowtrains was undertaken using FEA. TheABAQUS package was utilized since it can
handle complex boundary conditions. Thiscode can and will be coupled with a CFDsolver like FLUENT.
Characterization of ThermoCharacterization of ThermoCharacterization of ThermoCharacterization of Thermo----Acoustic Instabilities in LeanAcoustic Instabilities in LeanAcoustic Instabilities in LeanAcoustic Instabilities in Lean----Premixed Combustion Uri Vandsburger,Premixed Combustion Uri Vandsburger,Premixed Combustion Uri Vandsburger,Premixed Combustion Uri Vandsburger, R.L. WestR.L. WestR.L. WestR.L. WestThe dynamics, thermo acoustic instabilities, of Lean Premixed
Combustion systems are studied experimentally. The diagnos-tic techniques include microphones, hot wire anemometers,chemiluminescence, laser absorption. The data acquired, inthe form of FRF are combined with the acoustic characteriza-tion to obtain the closed loop behavior, and to test models de-veloped.
Development of Reduced Order Models (ROM) for TA In-Development of Reduced Order Models (ROM) for TA In-Development of Reduced Order Models (ROM) for TA In-Development of Reduced Order Models (ROM) for TA In-stabilities prediction,stabilities prediction,stabilities prediction,stabilities prediction, Uri Vandsburger, R.L. WestUri Vandsburger, R.L. WestUri Vandsburger, R.L. WestUri Vandsburger, R.L. WestThe effort aims at providing models for design engineers to pre-dict the stability of their, LP, combustion system, with the usageof full reacting CFD.
Combustion chamber
for thermoacoustic
characterization
Combustion and Active Control
3
-
8/22/2019 Virginia Grupo de Investigacion
7/34
-
8/22/2019 Virginia Grupo de Investigacion
8/34
5
Heat Transfer and Flow Characteristics in Can and Annu-Heat Transfer and Flow Characteristics in Can and Annu-Heat Transfer and Flow Characteristics in Can and Annu-Heat Transfer and Flow Characteristics in Can and Annu-
lar Combustorslar Combustorslar Combustorslar Combustors , Srinath V. Ekkad and Danesh TaftiSrinath V. Ekkad and Danesh TaftiSrinath V. Ekkad and Danesh TaftiSrinath V. Ekkad and Danesh Tafti
Research will focus on theinteraction between thehot swirling gases and theliner wall within a gas tur-bine combustor. Improvedunderstanding of the heattransfer process from thegases to the combustorliner is critical with the re-duction of direct film cool-ing of the liner. Thus more accurate local quantification of theheat transfer rates will allow more effective cooling on thebackside of the combustor liner. Modern DLE combustors are
characterized by highly swirling and expanding flows that makeconvective heat load on the gas side very difficult to predict orestimate. Present methodology is based on peak heat load(quantified based on the peak combustion temperature) ratherthan local near wall conditions. This conservative approach re-quires very high cooling rates on the wall, thus requiring compli-cated cooling designs and high coolant flow rates. Annularcombustors are significantly different in design than can com-bustors as there is no boundary in the transverse direction for
flow expansion for these types of combustors.
Combustion and Active Control
-
8/22/2019 Virginia Grupo de Investigacion
9/34
6
Backside Cooling of Gas Turbine Combustor Liners,Backside Cooling of Gas Turbine Combustor Liners,Backside Cooling of Gas Turbine Combustor Liners,Backside Cooling of Gas Turbine Combustor Liners, Sri-Sri-Sri-Sri-nath V. Ekkadnath V. Ekkadnath V. Ekkadnath V. Ekkad
This study, with Solar Turbines, Inc. based in San Diego, focuses on
improved combustion liner cooling. The modern lean premixed low
NOx combustor injectors produce a highly swirling and expanding
flow, so the convective heat load estimate in the gas side becomes a
daunting task. The combustors are so designed to reduce the NOx
emissions but the design produces increased heat load that ad-
versely affects the life of the components.
The life and performance of the combustor
depends on adequate cooling to the liner
walls. In older design, the cooling technique
utilized combustion dilution air and film cool-
ing of various types to achieve reasonable
liner temperatures. In low NOx combustors,
film cooling is not an option. So, there is a
need to design advanced cooling techniques,
which are a combination of traditional tech-
niques as in rib turbulators, impingement,
pin fins, and TBC coatings. In the present
study, we focus on various combined tech-niques to achieve high cooling efficiency that
will help in reducing liner temperatures, re-
sulting in cooled liners without using film
cooling and thus reducing NOx emissions.
Combustion and Active Control
-
8/22/2019 Virginia Grupo de Investigacion
10/34
Advanced Film Cooling Hole Geometry Study,Advanced Film Cooling Hole Geometry Study,Advanced Film Cooling Hole Geometry Study,Advanced Film Cooling Hole Geometry Study, Srinath V.Srinath V.Srinath V.Srinath V.
EkkadEkkadEkkadEkkad
Film cooling is used extensively in gas turbine hot
gas path components to protect the surfaces from
being exposed to high temperature combustion
gases. Typically, bleed air from the compressor is
routed under the hot gas path and injected throughthe surface from discrete holes to form a protective
film of cooler air, hence called film cooling. As
turbine inlet temperatures rise, the amount of avail-
able coolant is limited and cooling efficiency has
become an critical issue. In an attempt to enhance
cooling efficiency, new cooling hole designs have been investigated.
Three different cooling designs are proposed: Trenched holes where the
cylindrical holes are embedded in 2-dimensional trenches to simulate slot
exits; Cratered holes where the cylindrical holes are embedded in 3-dimensional craters to reduce upward momentum; and lastly the anti-
vortex geometry where the main holes also feed two smaller side holes to
generate anti-vortices that reduces jet lift-off and improve cooling effec-
tiveness. All the above designs have been tested on a flat plate in a low
speed wind tunnel. Geometrical variations such as trench width and
depth, crater depth and crater-to-hole exit location, anti-vortex pair hole
size and location have been investigated.
Manufacturing Effects in Gas Turbine Compressors,Manufacturing Effects in Gas Turbine Compressors,Manufacturing Effects in Gas Turbine Compressors,Manufacturing Effects in Gas Turbine Compressors,WingWingWingWing
F. NgF. NgF. NgF. Ng
The perturbation effects of as manufactured gas turbine compres-
sor blades can have a detrimental effect on engine performance.
Statistical techniques, such as Principal Component Analysis, are
used to determine the most common manufacturing perturbations
and the descriptive parameters that define these perturbations. Nu-
merical and experimental studies are then employed to quantify the
effects of manufacturing perturbations, where experimental and
numerical data is obtained via 2-D cascades.
Aerodynamics and Heat Trans-
fer
7
-
8/22/2019 Virginia Grupo de Investigacion
11/34
Compressor Cascade Testing and Flow Control,Compressor Cascade Testing and Flow Control,Compressor Cascade Testing and Flow Control,Compressor Cascade Testing and Flow Control,
Wing F. Ng
A two dimensional, transonic, linear cascade tunnel is used for compres-
sor aerodynamic research. Freestream turbulence intensity can vary
from 0.5% to 5% by the addition of a turbulence grid upstream. Loss
measurements have been taken for a variety of compressor stator blades.In addition, the use of flow control to reduce losses is also investigated.
Aerodynamics and Heat Trans-
fer
Heat Transfer Studies in Transonic Turbine BladesHeat Transfer Studies in Transonic Turbine BladesHeat Transfer Studies in Transonic Turbine BladesHeat Transfer Studies in Transonic Turbine Blades,
Wing F. NgA two dimensional transonic turbine cascade is used to study the heat
transfer to turbine blades and vanes. Time-resolved surface heat transfer
measurements are made by heating the inlet air and using thin film heat
flux gauges to measure corresponding changes in surface temperature.
The thin film heat flux gauges allow for high frequency response and
high spatial resolution measurements (we can measure heat flux at ap-
proximately 30 locations depending on blade size). Additionally, velocityand pressure measurements are made up and downstream of the cascade,
as well as on the surface of the blades. The effects of film cooling,
freestream turbulence and exit Mach number on the transfer of heat to the
blades and vanes are studied. A turbulence generator, which can vary the
turbulence intensity up to 15%, is used to simulate engine combustor exit
conditions.
8
-
8/22/2019 Virginia Grupo de Investigacion
12/34
Active Flow Control for HighActive Flow Control for HighActive Flow Control for HighActive Flow Control for High----Cycle Fatigue Reduction,Cycle Fatigue Reduction,Cycle Fatigue Reduction,Cycle Fatigue Reduction,
Wing F. Ng and Ricardo A. Burdisso
The high-cycle-fatigue (HCF) of com-
pressor components is due to blade
vibration and the accumulated dam-
age of the fatigue stress cycle. One
major source of such fatigue stress
cycles is the forced response of the
blade from unsteady aerodynamic exci-
tation. In particular, the unsteady ef-
fect on the rotor blade loading due to
the movement of the rotor through disturbances from the stationary
wake of an upstream stator or inlet guide vane (IGV) has been shown
to have a major effect on the HCF of compressor blades and the first
stage fan rotor.
Active Flow Control in a Serpentine Inlet,Active Flow Control in a Serpentine Inlet,Active Flow Control in a Serpentine Inlet,Active Flow Control in a Serpentine Inlet,Wing F. Ng andWing F. Ng andWing F. Ng andWing F. Ng and
Ricardo A. BurdissoRicardo A. BurdissoRicardo A. BurdissoRicardo A. Burdisso
An innovative method to reduce inlet distortion and improve the
performance of propulsion systems in unmanned air vehicles is
investigated. These vehicles (as well as other tactical aircraft) use
serpentine inlets to improve the stealth characteristics of the aircraft.
Unfortunately, these serpentine ducts cause flow separation and in-
crease the distortion at the engine reducing its stability and perform-
ance. In this research program, fluidic actuators will be used for
active flow control to prevent flow separation in serpentine gas tur-
bine inlet ducts. These fluidic actuators operated by bleeding high-
pressure air from the engine, will provide boundary layer suction and
blowing near the separation-prone areas in the inlet. Non-intrusive
microphones mounted on the internal surface of the inlet to detect
separated flow will be used to provide error signals for the controller.
Aerodynamics and Heat Trans-
fer
Blade surface flow visualiza-
9
-
8/22/2019 Virginia Grupo de Investigacion
13/34
Aerodynamics and Heat Trans-
fer
Operating on hydrocarbons, a
plasma torch produces a
bright, luminous combustion
plume in a M=2.4 crossflow
10
AxialAxialAxialAxial----Compressor Response to NonCompressor Response to NonCompressor Response to NonCompressor Response to Non----Uniform Flow,Uniform Flow,Uniform Flow,Uniform Flow,
Walter F. OBrien
An experimentally-derived technique for predicting the behavior of
axial- flow compressors operating with circumferential non-uniform
inlet flow is currently under development. The technique relies on cap-
turing unsteady blade- row flow phenomena with frequency
domain transfer functions. The stage-to-stage transfer of flow distor-
tion and the resulting first stage rotor blade forced response is included.
Ignition, Flameholding and Combustion EnhancementIgnition, Flameholding and Combustion EnhancementIgnition, Flameholding and Combustion EnhancementIgnition, Flameholding and Combustion Enhancement
System for Application in Supersonic Combustion,System for Application in Supersonic Combustion,System for Application in Supersonic Combustion,System for Application in Supersonic Combustion,
Walter F. OBrienWalter F. OBrienWalter F. OBrienWalter F. OBrien
Initiating and sustaining combustion in supersonic flows is a challeng-
ing problem. A new system based on the Aeroramp fuel injector de-
sign combined with a plasma torch is under research. Several fuels and
torch feedstocks including liquids and gasses are being investigated.
Tests in an unheated wind tunnel at a Mach number of 2.4 are promis-
ing.
-
8/22/2019 Virginia Grupo de Investigacion
14/34
Computational Simulations of Internal Turbine BladeComputational Simulations of Internal Turbine BladeComputational Simulations of Internal Turbine BladeComputational Simulations of Internal Turbine Blade
Cooling,Cooling,Cooling,Cooling, Danesh TaftiDanesh TaftiDanesh TaftiDanesh Tafti
The internal cooling of turbine blades
is a critical problem for the gas turbine
industry. Prediction of these flows
have been complicated by the pres-
ence of turbulence generators for heattransfer augmentation, rotational Cori-
olis, and buoyancy forces. Reynolds
number ranges from moderate O(104)
to very high O(105) depending on the
application. Rotation numbers can be
of O(1), and centrifugal buoyancy
driven Rayleigh numbers of O(108).
The turbulent flow is highly anisotropicand all attempts at predicting the flow and heat transfer have fo-
cused on the solution of steady Reynolds Averaged Navier-Stokes
(RANS) and energy equations. The focus of the current research is to
apply alternative time-dependent solution techniques based on large-
eddy and detached-eddy simulations (LES and DES, respectively).
Currently LES is being performed in ribbed channels with the code
GenIDLEST (Generalized Direct and Large Eddy Simulations of Turbu-
lence) at Re=20,000.
Periodic section of a ribbed channel
Aerodynamics and Heat Trans-
fer
11
-
8/22/2019 Virginia Grupo de Investigacion
15/34
12
A General Theory for the Effect of Large Scale
Freestream Turbulence on Surface Heat Transfer, Tom
Diller and Pavlos VlachosThe objective of
this research is to examine
the effects of freestream
turbulence on boundarylayer heat transfer using
state-of-the-art TRDPIV
(Time Resolved Digital
Particle Image Veloci-
metry) and by developing
and employing a new class
of thin film heat flux sen-
sors called the HFA (Heat
Flux Array). TRDPIV is
used to spatiotemporallyresolve the dynamics of the
flow, while the HFA is used
to directly measure heat
flux signals on the surface as well as surface temperature. We were able
to resolve coherent structures as they interacted with the boundary layers,
and directly correlate these motions with heat flux. Coherent structure
identification and tracking algorithms were developed and implemented
to further understand the fundamental mechanism of heat transfer aug-
mentation by freestream turbulence. Our results so far support the notionthat vortices near the plate interact or exchange heat with the plate for a
characteristic time t~d2/G where d is the mean distance of the vortex core
form the surface and G is the mean circulation of the vortex. Correlations
of measured heat flux with coherent structures validate this hypothesis.
Therefore this simplistic phenomenological model is capturing the asso-
ciated physical processes. Additional, more complex models and correla-
tions are currently being examined with promising results.
Aerodynamics and Heat Trans-
fer
Example of TRDPIV images where flow velocity magnitude iscontoured and vectors are added to bring out the structure of the
stagnating flow field.
-
8/22/2019 Virginia Grupo de Investigacion
16/34
Porous flow Modeling and Parallel Implementation ofPorous flow Modeling and Parallel Implementation ofPorous flow Modeling and Parallel Implementation ofPorous flow Modeling and Parallel Implementation of
Aircast,Aircast,Aircast,Aircast, Danesh Tafti
The project involves the enhancement of ARCAST, which predicts the
thermal response of charring materials used in nozzle liners. It involves
the enhanced modeling of the pyrolyzed gas flow in the liner together
with efficient parallelization strategies to increase physical as well as
computational fidelity.
Rocket Propulsion
13
-
8/22/2019 Virginia Grupo de Investigacion
17/34
14
Skin Friction Measurements in Scramjet Combustors,Skin Friction Measurements in Scramjet Combustors,Skin Friction Measurements in Scramjet Combustors,Skin Friction Measurements in Scramjet Combustors,
Joseph A. Schetz
A direct-measuring skin friction gage was developed for the high-
speed, high-temperature environment of the turbulent boundary layer in
a supersonic combustor. The design is that of a non-nulling
cantilevered beam, the head of which is flush with the model wall and
surrounded by a small (0.0127 cm) gap. Finite element software alongwith simple beam theory were used to analyze the response of the
beam to an applied shear load. Semiconductor (piezo-resistive) strain
gages were used to detect this strain at the base of the beam. Cooling
water was routed both inside the beam and around the external housing
in order to control the temperature of the strain gages. The gage was
statically calibrated using a direct force method and verified by testing
in a well-documented Mach 2.4 cold-flow. Results of the cold-flow
tests were repeatable and within 15% of the value of Cfestimated fromsimple theory. The gage was then installed and tested in a rocket-
based-combined-cycle engine model operating in the scramjet mode.
Instrumentation and Sensor
Development
VT Skin Friction Gage Qualified for Hypersonic Flight Test
on X-43
-
8/22/2019 Virginia Grupo de Investigacion
18/34
15
Photonic Sensors for Harsh Environments,Photonic Sensors for Harsh Environments,Photonic Sensors for Harsh Environments,Photonic Sensors for Harsh Environments,
Anbo Wang
The Center for Photonics Technology
(CPT) in the Department of Electrical
and Computer Engineering at Virginia
Tech is a recognized leader in the
area of photonic sensors for harsh
environments. The Center currently
maintains 8,000 square feet of labo-
ratory and office space specifically to
support research and development
programs in the areas of photonic
sensor instrumentation for physical,
chemical, medical and biological measurements. Their research
covers all major aspects concerning sensors, ranging from novel sens-
ing mechanisms, sensor materials, nanofilms, optoelectronic signal
processing to instrumentation systems. Some of the major sensors
they have investigated or developed include: pressure sensors for
static and dynamic measurements up to 20,000psi; temperature sen-
sors from up to 1700oC; strain sensors for high temperatures up to
1500oC; acoustic sensors for frequencies from 0.01Hz to 1MHz; self-
calibrating flow sensors; magnetic field sensors from 1-40,000nT;
laser spectroscopy for cancer diagnosis; chemical gas measurement
at high temperatures up to 800oC; biological agent detection; simulta-
neous measurement of multi-quantities by a single fiber; sensor
multiplexing.
Single-crystal sapphire fiber fiber-based
strain sensor capable of operation above
1000oC
Instrumentation and Sensor
Development
-
8/22/2019 Virginia Grupo de Investigacion
19/34
16
Heat Flux SensorsHeat Flux SensorsHeat Flux SensorsHeat Flux Sensors, T. E. Diller
Several new heat flux sensors are being built and tested in sup-
port of gas turbine research. These include insert type gages and thin
surface mounted gages, both single point and sensor arrays. The High
Temperature Heat Flux Sensor (HTHFS) is capable of long term opera-
tion at temperatures and heat flux levels in excess of 1000C and 10 W/
cm2 respectively. The current sensor configuration utilizes type-K ther-
mocouple materials in a durable welded thermopile arrangement. The
steady-state thermoelectric sensitivity of the design is predicted using aone-dimensional thermal resistance model and the Seebeck coefficient of
the thermocouple materials. Average experimental values of the sensitiv-
ity are about 1 mV/W/cm2 with no apparent effect of thermal cycling.
Calibration facilities include methods for testing sensors in pre-
dominantly convective, radiative, or conductive heat transfer modes. A
high-temperature calibration facility is currently being designed for im-
plementation in the near future. Based on experimental results previously
obtained, a model has been developed and tested that shows the effect of
convection relative toradiation on the re-
sponse of heat flux
gages. The effect of
convection can be quite
significant over some
ranges.
Instrumentation and Sensor
Development
Original version of the VT/EPFL heat flux gage
-
8/22/2019 Virginia Grupo de Investigacion
20/34
17
A MagneticallyA MagneticallyA MagneticallyA Magnetically----LevitatedLevitatedLevitatedLevitated Rocket Thrust MeasurementRocket Thrust MeasurementRocket Thrust MeasurementRocket Thrust Measurement
Test Rig,Test Rig,Test Rig,Test Rig,Mary E. F. Kasarda
A Magnetically-Levitated Rocket Thrust Measurement System (TMS)
is a novel approach allowing for increased flexibility to meet changing
test requirements for rockets and gas turbines, while providing high-
accuracy thrust measurements. This project develops such a system
by utilizing Active Magnetic Bearings (AMBs) to simultaneously sup-
port the test article and measure the generated thrust and side loads.
By selectively utilizing multiple AMBs in parallel, test articles with a
wider range of performance can be tested in the same fixture, elimi-
nating the need for multiple test stands in some scenarios, resulting
in a reduction of hardware and facility expenditures. A laboratory
scale prototype TMS system sponsored by NASA Stennis and Imlach
Consulting Engineering was recently delivered to NASA Stennis after
initial testing at Virginia Tech.
Magnetic Dampers for Improved Rotor Stability,Magnetic Dampers for Improved Rotor Stability,Magnetic Dampers for Improved Rotor Stability,Magnetic Dampers for Improved Rotor Stability,
Mary E. F. Kasarda
The main body of this work involved examin-ing the effect of a magnetic damper on reduc-
ing subsynchronous and supersynchronous
vibrations on a small high-speed test rotor.
Tests were run on two different rotor configu-
rations with the damper located at various
locations along the rotor and with various
settings of stiffness and damping.
(continued on next page)
Investigation of active magnetic
bearings for reduction of gear
noise
Rotor Dynamics and
Magnetic Bearings
-
8/22/2019 Virginia Grupo de Investigacion
21/34
Results showed as much as a 98% reduction in subsynchronous vibra-
tions and in some cases showed an increase in synchronous vibrations.
The tests demonstrated the potential for a magnetic damper to improve
rotor stability and that a thorough rotor dynamic investigation is neces-
sary to fully examine the effect of the magnetic damper on overall sys-
tem dynamics.
CFD Analysis of Bearings, Viscous Dampers and Seals,CFD Analysis of Bearings, Viscous Dampers and Seals,CFD Analysis of Bearings, Viscous Dampers and Seals,CFD Analysis of Bearings, Viscous Dampers and Seals,
R. Gordon Kirk
A major research effort is CFD analysis for fluid film bearings and seals.
CFX-TASCflow with CFX-Build and CFX-TurboGrid have been used
to simulate fluid-film bearing and seal geometries.
Some desired geometries for bearing simulation
have been successfully conducted including the
cylindrical hydrodynamic bearing, the hydrostatic
bearing and the hybrid bearing with laminar or
turbulent flow conditions. A users program will
be developed and connected to the software
through a new interface. This will permit auto-
matic perturbation analysis for computation of bearing and seal dy-namic stiffness and damping characteristics. Bearing, seal and viscous
damper evaluation of internal flows and leakage rates are compared to
current analysis and design methods.
Evaluating CFD results of
bearing analyses
Rotor Dynamics and
Magnetic Bearings
18
-
8/22/2019 Virginia Grupo de Investigacion
22/34
William T. BaumannWilliam T. BaumannWilliam T. BaumannWilliam T. Baumann
Education: B.S.E.E., Lehigh University, 1978,
M.S.E.E., M.I.T., 1980 , Ph.D., Johns Hopkins
University, 1985
Research Interests: Active Combustion Control and
Modeling of Combustion Systems: Theoretical and
experimental investigation of the control of ther-
moacoustic instabilities in gas turbines and aero engines. Development of
modular models that describe combustion instabilities such as ther-
moacoustic limit cycles and lean blow out. Active Noise and Vibration
Control: Design of feedback-based hearing protection systems and struc-
tural vibration control systems. Approaches include adaptive control and
direct optimization.
Ricardo A. BurdissoRicardo A. BurdissoRicardo A. BurdissoRicardo A. Burdisso
Dr. Burdisso received his engineering degree from the
National University of Cordoba, Argentina in 1981. He
obtained his Ph.D. at Virginia Tech in 1986 with
research in stochastic analysis of systems under
multiple correlated seismic input. He joined the
Mechanical Engineering Department at Virginia Tech in
1989 as a Research Scientist working in the area of ac-
tive control of structurally radiated sound. In the Fall of
1992, Dr. Burdisso accepted the assistant professor position in the same
department.
Research Interests: Passive and active control of structural vibrations
and their sound radiation, development of adaptive control algorithms
Participating Faculty Members
19
-
8/22/2019 Virginia Grupo de Investigacion
23/34
William J. DevenportWilliam J. DevenportWilliam J. DevenportWilliam J. Devenport
Dr. Devenport received his B. Sc. degree in Engineering
Science from the University of Exeter, England, and his
Ph.D. in experimental and computational fluid dynamics
from the University of Cambridge, England. He came to
Virginia Tech in 1985 as a research associate and then
joined the faculty of the Department of Aerospace and
Engineering in 1989.
Research Interests: Experimental studies of turbulence structure of tip
vortices, tip-vortex blade interactions and tip-leakage vortex wakes
Thomas E. DillerThomas E. DillerThomas E. DillerThomas E. Diller
Dr. Diller received degrees in Mechanical Engineering from Carnegie-Mellon University (B.S., 1972) and the Massachusetts Institute of Technol-
ogy (M.S., 1974; Sc.D., 1977). Prior to joining the Mechanical Engineer-
ing faculty in 1979, he spent three years at the Polaroid Cor-
poration doing research in the process engineering area.
Research Interests: Development and use of new instru-mentation for measuring heat transfer, particularly in high
temperature unsteady flows
Participating Faculty Members
20
-
8/22/2019 Virginia Grupo de Investigacion
24/34
Srinath V. EkkadSrinath V. EkkadSrinath V. EkkadSrinath V. Ekkad
Dr. Ekkad joined Virginia Tech in August 2007. He
spent 9 years at LSU and 2 years at Rolls-Royce, Indi-
anapolis before that. Dr. Ekkad is an expert in the area
of gas turbine heat transfer and cooling. He has devel-
oped experimental techniques for heat transfer meas-
urement for film cooling and has written a book on
gas turbine heat transfer and cooling technology. He
received his Ph.D. in 1995 from Texas A&M University.
Research Interests:Research Interests:Research Interests:Research Interests: Gas turbine cooling and heat transfer, film cool-
ing, design of high temperature components, combustor design, ex-
perimental heat transfer, micro-channel flow and heat transfer, nan-
ofluids
Steve KampeSteve KampeSteve KampeSteve Kampe
Dr. Kampe received a B.S. in 1981, an M.S. in 1983, and a
Ph.D. in 1987 from Michigan Technological University.
He is currently an associate professor in the Materials Sci-ence and Engineering department at Virgina Tech.
Research interests: Mechanical behavior, composite mate-
rials, intermetallics, titanium alloys, and alloy development
and processing
Participating Faculty Members
21
-
8/22/2019 Virginia Grupo de Investigacion
25/34
Mary E. F. KasardaMary E. F. KasardaMary E. F. KasardaMary E. F. Kasarda
Dr. Kasarda joined Virginia Tech as an assistant
professor in January of 1997. She has six years of
professional engineering experience and is a former em-
ployee of Ingersoll-Rand, Rotor Bearing Dynamics, Inc.,
and Du Pont. Her background is in various aspects of tur-
bomachinery engineering including rotor dynamics and
the repair and overhaul of rotating equipment. She com-
pleted her Ph.D. in 1996 at the University of Virginia.
Research Interests: Effects of base motion on performance of
magnetic bearing systems, investigation of magnetic bearings for meas-
urement of forces in a rocket thrust measurement system and the charac-
terization of power losses in magnetic bearings
R. Gordon KirkR. Gordon KirkR. Gordon KirkR. Gordon Kirk
Dr. Kirk studied at the University of Virginia where he received a B.S.
degree in 1967, an M.S. in 1969, and a Ph.D. in 1972.
His industrial experience includes three years with Pratt &
Whitney Aircraft in East Hartford, Conn., and ten years
with the Ingersoll-Rand Turbo Machinery Division in
Phillipsburg, NJ. He joined the Mechanical Engineering
Department at Virginia Tech in 1985.
Research Interests: Liquid and gas seal influence on rotor
response and stability, dynamics stability of active magnetic bearings,
active control of rotor response, thermal instability of rotors, and balanc-
ing of rotating machinery
Participating Faculty Members
22
-
8/22/2019 Virginia Grupo de Investigacion
26/34
Wing F. NgWing F. NgWing F. NgWing F. Ng
Dr. Ng is the Chris Kraft Professor of Engineering at
Virginia Tech. He received his B.Sc. (M.E.) degree
from Northeastern University, and his S.M. and Ph.D.
from the Massachusetts Institute of Technology. Before
beginning his S.M. work, he worked for the Aircraft
Engine Group of the General Electric Company.
Research Interests: Flow control for aeropropulsion, calculations of
turbo-machinery flowfields, experimental studies of turbomachinery cas-
cades, and aeroacoustics
Walter F. OBrienWalter F. OBrienWalter F. OBrienWalter F. OBrien
Dr. OBrien received degrees from Virginia Polytechnic Institute & State
University and Purdue University. He has conducted
research and development projects in several propul-
sion-related areas including gas generators and rockets,
gas turbines, and SCRAMJETS.
Research Interests: Modeling the transfer of non-
uniform flow in transonic compressors, the use of gas
turbine engine performance models for improving gas turbine manufac-
turing and maintenance practices, ignition and flame holding in super-
sonic flame combustion
Participating Faculty Members
23
-
8/22/2019 Virginia Grupo de Investigacion
27/34
Danesh K. TaftiDanesh K. TaftiDanesh K. TaftiDanesh K. Tafti
Dr. Danesh K. Tafti obtained his Ph.D. from Penn State University in
1989. He served as a visiting professor at West Virginia Institute of
Technology from 1988-1989, a post doctoral research associate from
1989-1991 and then as a research scientist at the national Center for Su-
percomputing Applications at the University of Illinois,
Urbana Champaign from 1991-2001. Currently he is an
Associate Professor in the Department of Mechanical Engi-
neering at Virginia Tech, where he directs the High Per-formance Computational Fluid-Thermal Science and Engi-
neering Lab.
Research Interests: Large-scale unsteady simulations of complex turbu-
lent flow and heat transfer using Direct Numerical Simulations (DNS),
Large-Eddy Simulations (LES), and hybrid methods (RANS-LES), paral-
lel computing and programming paradigms. Current projects are in com-
pact heat exchangers, turbomachinery, microfluidics for integrated micro
-total-analysis systems, and the development of computational tools for
high performance computing
Joseph A. SchetzJoseph A. SchetzJoseph A. SchetzJoseph A. Schetz
Dr. Schetz received his bachelors degree in 1958 from
Webb Institute of Naval Architecture and went on to pursue
three graduate degrees at Princeton University. He obtained
his M.S. in 1960, his M.A. in 1961, and his doctorate the
following year. While writing his dissertation for Prince-
ton, Dr. Schetz joined the General Applied Science Labora-
tory. In 1964, he joined the faculty of the University of
Maryland as an associate professor of Aerospace Engineering, and five
years, later, he joined Virginia Tech in the Department of Aerospace and
Ocean Engineering.
Research Interests: Turbulent flow injection and mixing problems, from
supersonic cases to thermal pollution in rivers
Participating Faculty Members
24
-
8/22/2019 Virginia Grupo de Investigacion
28/34
25
Uri VandsburgerUri VandsburgerUri VandsburgerUri Vandsburger
Dr. Vandsburger received his B.Sc. in Mechanical Engi-
neering from the Technion (IIT). His postgraduate
work was performed at Princeton University where he
earned a M.A. and Ph.D. in Mechanical and Aerospace
Engineering. Before returning to graduate school, he
worked in Israel as a mechanical design engineer in the
area of airborne structures, and in West Germany as a
thermal systems design engineer. He worked as a re-
search associate for five years at SU-HTGL.
Research Interests: Flow and combustion control for the purpose of
missing and combustion enhancement, fundamental studies on pollutant
formation, synthesis of nanosize powders, CO formation and transport in
building fires
Pavlos VlachosPavlos VlachosPavlos VlachosPavlos VlachosDr. Vlachos received his BS in Mechanical Engineer-
ing from the National Technical University of Athens
(1995) and his MS (1998) and PhD (2000) in Engineer-
ing Mechanics from Virginia Tech. On August 2003
he joined the Department of Mechanical Engineering at
Virginia Tech as assistant professor and he was pro-
moted to associate with tenure in 2007. Dr Vlachos is
the recipient of the 2007 ASME Fluids Engineering
Moody award and a 2007 College of Engineering Fac-ulty Fellow. In the same year, he delivered the keynote paper in the
ASME Fluids Measurement and Instrumentation Forum. He was
awarded the 2005 Deans Award of Excellence for Outstanding Assis-
tant Professor and the 11th Annual T.F. Ogilvie Lectureship Award for
Young Investigator in Ocean Engineering and Fluid Mechanics by the
MIT Department of Mechanical Engineering. In 2006 he became a re-
cipient of the NSF CAREER award .Research Interests:Research Interests:Research Interests:Research Interests: Experimental fluid mechanics addressing a variety
of flows such as biofluid/cardiovascular mechanics, multi-phase flowsclassical aerothermodynamics, sensors and instrumentation
Participating Faculty Members
-
8/22/2019 Virginia Grupo de Investigacion
29/34
26
Facilities
Compressor Cascade with Moving Wall
JT15D Research Gas Turbine
F109 Turbofan Engine
Supersonic/Transonic Wind Tunnel
Laminar and Turbulent
Combustors
Anechoic Chamber Two Linked Reverberation Chambers
Schlieren and Shadowgraph
Laser Doppler Anemometers
Chemiluminecense Analyzers (CLA)
Heat Flux Sensors
Infared Thermolgrapy
Liquid Crystal Thermography
Hot-Wire Anemometry
Fast-Response Pressure and Heat Flux Gages
High-Speed Fluid-Film Bearing Test Rig
-
8/22/2019 Virginia Grupo de Investigacion
30/34
27
-
8/22/2019 Virginia Grupo de Investigacion
31/34
28
Sponsors
-
8/22/2019 Virginia Grupo de Investigacion
32/34
29
-
8/22/2019 Virginia Grupo de Investigacion
33/34
30
Virginia Techs College of EngineeringVirginia Techs College of EngineeringVirginia Techs College of EngineeringVirginia Techs College of Engineering
Virginia Tech is home to the
Commonwealth's leading Col-lege of Engineering, known in
Virginia and throughout the
nation for its excellent pro-
grams in engineering educa-
tion, research, and public
service. Overall, the college
ranked 24th in the 2002 U.S.
News and World Report graduate survey of engineering schools.
Techs College of Engineering, specifically the Mechanical Engi-
neering Department, is one of the few institutions with a strong back-
ground in propulsion and turbomachinery research.
For more information about Virginia Techs Center forTurbomachinery and Propulsion Research, feel free tocontact:
Dr. Srinath EkkadMechanical Engineering101 Randolph HallMail Code 0238Blacksburg VA 24061
Center for Turbomachinery andCenter for Turbomachinery andCenter for Turbomachinery andCenter for Turbomachinery andPropulsion ResearchPropulsion ResearchPropulsion ResearchPropulsion Research
2004 Center for Turbomachinery and Propulsion Research - Virginia Tech- All Rights Reserved.
Phone: 540-231-7192Fax: 540-231-9100E-mail: [email protected]
-
8/22/2019 Virginia Grupo de Investigacion
34/34
31