Damping of high-temperature shape memory alloys

Duffy, Kirsten P.; Padula, Santo; Scheiman, Daniel A.

doi:10.1117/12.776288

Cited by 11 publications

(17 citation statements)

References 9 publications

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“…Since all the piezoelectric material properties necessary for FE modeling were not available from the piezoelectric materials manufacturer for the experimental tests, some approximations were necessary for inputting the piezoelectric material properties for FE modeling. Hence, differences in experimental test and FE model possibly comes from: (1) discrepancy in piezoelectric properties and clamp boundary conditions; (2) imperfections in bonding; (3) modal damping measurements variation; (4) possible experimental wiring signal effects; (5) inconsistent shaker excitations; (6) and imperfection in the connection of piezoelectric patch and electric circuitry in the experimental tests. …”

Section: Non-spinning Resultsmentioning

confidence: 99%

“…Designing damping treatments for rotating blades in an extreme engine environment is a difficult task with various factors such as very high temperatures and centrifugal accelerations. Several damping methods have been investigated by NASA researchers at Glenn Research Center (GRC) for use in aircraft engine blades, including viscoelastic damping [2], impact damping [3,4], plasma sprayed damping coatings [5], and high-damping high-temperature shape memory alloy materials [6]. Piezoelectric dampers have also been explored as a solution for damping treatment [7][8][9].…”

mentioning

confidence: 99%

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Shunted Piezoelectric Vibration Damping Analysis Including Centrifugal Loading Effects

Min

Duffy²,

Provenza³

2010

51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

19
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24
0

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Excessive vibration of turbomachinery blades causes high cycle fatigue problems which require damping treatments to mitigate vibration levels. One method is the use of piezoelectric materials as passive or active dampers. Based on the technical challenges and requirements learned from previous turbomachinery rotor blades research, an effort has been made to investigate the effectiveness of a shunted piezoelectric for the turbomaninery rotor blades vibration control, specifically for a condition with centrifugal rotation. While ample research has been performed on the use of a piezoelectric material with electric circuits to attempt to control the structural vibration damping, very little study has been done regarding rotational effects. The present study attempts to fill this void. Specifically, the objectives of this study are: (a) to create and analyze finite element models for harmonic forced response vibration analysis coupled with shunted piezoelectric circuits for engine blade operational conditions, (b) to validate the experimental test approaches with numerical results and vice versa, and (c) to establish a numerical modeling capability for vibration control using shunted piezoelectric circuits under rotation. Study has focused on a resonant damping control using shunted piezoelectric patches on plate specimens. Tests and analyses were performed for both non-spinning and spinning conditions. The finite element (FE) shunted piezoelectric circuit damping simulations were performed using the ANSYS Multiphysics code for the resistive and inductive circuit piezoelectric simulations of both conditions. The FE results showed a good correlation with experimental test results. Tests and analyses of shunted piezoelectric damping control, demonstrating with plate specimens, show a great potential to reduce blade vibrations under centrifugal loading. INTRODUCTIONThe requirements for advanced aircraft engine components lead to designs which are more lightweight and efficient, yet more susceptible to excessive vibration, complex dynamic behavior, and uncertain durability and reliability. Structural vibrations also lead to thicker blade designs, increased fuel burn, increased noise, fatigue failures, reduced engine life, reduced safety, and increased maintenance costs. Turbomachinery rotating blades such as fan and compressor blades are subject to high cycle fatigue (HCF) failures as a result of high vibratory stresses. HCF accounts for fifty-six percent of major aircraft engine failures and ultimately limits the service life of most critical rotating components. An estimated $400M is expended annually for HCF related inspection and maintenance of military aircraft alone [1]. Excessive vibration of turbomachinery blades requires damping treatments to mitigate excessive vibration levels which cause HCF problems. Designing damping treatments for rotating blades in an extreme engine environment is a difficult task with various factors such as very high temperatures and centrifugal accelerations. Several damping methods ha...

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Section: Non-spinning Resultsmentioning
confidence: 99%

mentioning
confidence: 99%

Shunted Piezoelectric Vibration Damping Analysis Including Centrifugal Loading Effects
Min
¹
,
Duffy²,
Provenza³
2010
51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
19
0
24
0
View full text Add to dashboard Cite

show abstract

“…Modeling has afforded the ability to understand the fundamental nature of these systems [8,9]. Amplitude control methods have also been achieved through electromagnetic actuators [10] Damping can be used to mitigate the excessive stresses in engine components that lead to high cycle fatigue [11]. The design of advanced, high performance turbomachinery blades, such as bladed disks, has led to higher stresses and decreased damping.…”

Section: Introductionmentioning
confidence: 99%

“…The composition of the NiTi alloy and the thermo-mechanical processing influence the damping characteristics of the material [11]. In addition, the transformation temperature can be tailored through formulation, especially for high temperature applications [14,15]; Ni 19.5 Ti 50.5 Pd 25 Pt 5 has a transformation temperature near 300°C, which is conducive for turbomachinery applications [16].…”

Section: Introductionmentioning
confidence: 99%

Active Stiffness Method for High Cycle Fatigue Mitigation using Topical Thin Foil Shape Memory Alloy
Garafolo¹,
Collard²
2017
JMDV
6
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5
0
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The strong need for high cycle fatigue mitigation has resulted in numerous techniques resulting in added weight, increased operational costs, and lower performance. The experimental investigation presented was a foundational effort towards mitigating HCF through the use of shape memory alloy in a composite system. The research objective was to quantify changes in eigenvalue, eigenvector, and amplitude of a vibrating cantilever beam with a thin SMA topical treatment; as quantified during SMA phase transformations and through comparison with a control. A composite beam consisting of a nitinol thin SMA foil adhered to an Aluminum Alloy 6061 substrate was designed and fabricated. The three configurations were utilized: (1) a full-span SMA treatment designed for maximum eigenvalue shift and maximum amplitude reduction, (2) a half-span SMA treatment designed for eigenvector shift, and (3) a full-span aluminum treatment for a control. Through a complete modal analysis, results illustrated that thin foil SMA treatments led to a significant shift in eigenvalue, up to 6.53%. Highlighting the reduction in amplitude was a 92% reduction in amplitude at second bending with constant excitation frequency with the full-span sample. Spanwise scans on the half-span sample with and without SMA actuation illustrated a 0.77% shift in node location.

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“…6), and high-damping high-temperature shape memory alloy materials (Ref. 7) are typically investigated in this facility. Recent experiments explore the possibility of using piezoelectric materials in the form of patches to dampen problematic blade vibration modes (Refs.…”

Section: Introductionmentioning
confidence: 99%

Control of Fan Blade Vibrations Using Piezoelectrics and Bi-Directional Telemetry
Provenza
¹
,
Morrison
²

2011
Volume 6: Structures and Dynamics, Parts a and B
4
0
3
0
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A novel wireless device which transfers supply power through induction to rotating operational amplifiers and transmits low voltage AC signals to and from a rotating body by way of radio telemetry has been successfully demonstrated in the NASA Glenn Research Center (GRC) Dynamic Spin Test Facility. In the demonstration described herein, a rotating operational amplifier provides controllable AC power to a piezoelectric patch epoxied to the surface of a rotating Ti plate. The amplitude and phase of the sinusoidal voltage command signal, transmitted wirelessly to the amplifier, was tuned to completely suppress the 3rd bending resonant vibration of the plate. The plate’s 3rd bending resonance was excited using rotating magnetic bearing excitation while it spun at slow speed in a vacuum chamber. A second patch on the opposite side of the plate was used as a sensor. This paper discusses the characteristics of this novel device, the details of a spin test, results from a preliminary demonstration, and future plans.

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Damping of high-temperature shape memory alloys

Cited by 11 publications

References 9 publications

Shunted Piezoelectric Vibration Damping Analysis Including Centrifugal Loading Effects

Shunted Piezoelectric Vibration Damping Analysis Including Centrifugal Loading Effects

Active Stiffness Method for High Cycle Fatigue Mitigation using Topical Thin Foil Shape Memory Alloy

Control of Fan Blade Vibrations Using Piezoelectrics and Bi-Directional Telemetry

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