Active Control of Low-Speed Fan Tonal Noise Using Actuators Mounted in Stator Vanes: Part 1 Control System Design and Implementation

Remington, Paul J.; Sutliff, Daniel L.; Sommerfeldt, Scott D.

doi:10.2514/6.2003-3190

Cited by 9 publications

(6 citation statements)

References 3 publications

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“…A mass element (MASS21) which has six degrees of freedom (three translations and three rotations in the x, y, and z directions) was attached to the "ground" (rotor part) to define a large mass element [M] with concentrated mass matrix components and rotary inertias as shown in Equation (13). The harmonic-forced excitation was then applied as a force of magnitude of the combined mass, m and M, times the desired acceleration, a, on the master node.…”

Section: Approach Of Rotating Blade Vibration Excitation Through Largmentioning

confidence: 99%

“…Researchers at GRC also carried out the design and implementation of an experimental system that utilized stator vane mounted piezoelectric actuators to control fan-stator interaction noise in a simulated turbo-fan engine (Ref. 13). More recently, a resonant damping study using shunted piezoelectric patches on plate specimens was conducted (Refs.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Piezoelectric Vibration Damping Study for Rotating Composite Fan Blades

Min

Duffy

Choi³

et al. 2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

4
0
1
0

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Section: Approach Of Rotating Blade Vibration Excitation Through Largmentioning
confidence: 99%

Section: Introductionmentioning
confidence: 99%

Piezoelectric Vibration Damping Study for Rotating Composite Fan Blades
Min
¹
,
Duffy
²
,
Choi³
et al. 2012
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
4
0
1
0
View full text Add to dashboard Cite

“…The technology works to reduce noise, but the accompanying system (measurement devices, acoustics sources, and controllers) makes it difficult to package the device in a real system (Ref. 7).…”

Section: Active Inlet Flow and Noise Controlmentioning
confidence: 99%

Sensor and Actuator Needs for More Intelligent Gas Turbine Engines
Garg
¹
,
Schadow²,
Horn
³

et al. 2010
Volume 3: Controls, Diagnostics and Instrumentation; Cycle Innovations; Marine
29
0
11
0
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This paper provides an overview of the controls and diagnostics technologies, that are seen as critical for more intelligent gas turbine engines (GTE), with an emphasis on the sensor and actuator technologies that need to be developed for the controls and diagnostics implementation. The objective of the paper is to help the “Customers” of advanced technologies, defense acquisition and aerospace research agencies, understand the state-of-the-art of intelligent GTE technologies, and help the “Researchers” and “Technology Developers” for GTE sensors and actuators identify what technologies need to be developed to enable the “Intelligent GTE” concepts and focus their research efforts on closing the technology gap. To keep the effort manageable, the focus of the paper is on “On-Board Intelligence” to enable safe and efficient operation of the engine over its life time, with an emphasis on gas path performance.

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“…Piezoelectric networks have also been studied for reduction of mistuned blade vibration levels through blade coupling [16]. Researchers at NASA GRC also carried out the design and implementation of an experimental system that utilized stator vane mounted piezoelectric actuators to control fan-stator interaction noise in a simulated turbo fan engine [17]. These efforts have been non-spinning application tests only, and typically used a powered shunt circuit utilizing synthetic inductors or negative capacitance.…”

Section: Introductionmentioning
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
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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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Active Control of Low-Speed Fan Tonal Noise Using Actuators Mounted in Stator Vanes: Part 1 Control System Design and Implementation

Cited by 9 publications

References 3 publications

Piezoelectric Vibration Damping Study for Rotating Composite Fan Blades

Piezoelectric Vibration Damping Study for Rotating Composite Fan Blades

Sensor and Actuator Needs for More Intelligent Gas Turbine Engines

Shunted Piezoelectric Vibration Damping Analysis Including Centrifugal Loading Effects

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