High cycle fatigue of turbomachinery components - Industry perspective

El-Aini, Yehia M.; deLaneuville, Robert E.; Stoner, Alan; Capece, Vincent R.

doi:10.2514/6.1997-3365

Cited by 31 publications

(19 citation statements)

References 8 publications

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“…Clearly the airflow over the blades adds significant damping to the resonance mode crossings. Generally, aerodynamic damping ranges from on the order of 0.1% for higher order modes to on the order of 1% for lower modes such as mode 1 [11]. Fortunately, the 2EO/M1 crossing had very high damping at 1.9% for M = 0.42, which was a typical Mach number for that crossing during start up and shutdown.…”

Section: Fan Blade Vibration Modesmentioning

confidence: 99%

Laser Displacement Measurements of Fan Blades in Resonance and Flutter During the Boundary Layer Ingesting Inlet and Distortion-Tolerant Fan Test

Duffy

Provenza

Bakhle

et al. 2018

2018 AIAA Aerospace Sciences Meeting

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NASA's Advanced Air Transport Technology Project is investigating boundary layer ingesting propulsors for future subsonic commercial aircraft to improve aircraft efficiency, thereby reducing fuel burn. To that end, a boundary layer ingesting inlet and distortiontolerant fan stage were designed, fabricated, and tested within the 8'x6' Supersonic Wind Tunnel at NASA Glenn Research Center. Because of the distortion in the air flow ingested by the fan, the blades were designed to withstand a much higher aerodynamic forcing than for a typical clean flow. The blade response for several resonance modes was measured during start-up and shutdown, as well as at near 85% design speed. Flutter in the first bending mode was also observed in the fan at the design speed, at an off-design condition, although instabilities were difficult to instigate with this fan in general. Blade vibrations were monitored through twelve laser displacement probes that were placed around the inner circumference of the casing, at the blade leading and trailing edges. These probes captured the movement of all the blades during the entire test. In addition to blade vibration results, benefits and disadvantages of laser displacement probe measurements versus strain gage measurements are discussed.

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Section: Fan Blade Vibration Modesmentioning

confidence: 99%

Laser Displacement Measurements of Fan Blades in Resonance and Flutter During the Boundary Layer Ingesting Inlet and Distortion-Tolerant Fan Test

Duffy

Provenza

Bakhle

et al. 2018

2018 AIAA Aerospace Sciences Meeting

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Section: Hcf Problemmentioning

confidence: 99%

“…It results from blade cracking or fracture due to a large number of cycles at stresses well below the yield strength of the material [1]. Although more than 90% of potential HCF problems are discovered during engine developmental testing, the remaining 10% account for nearly 30% of the total development cost [1]. HCF research is focused on the need for increased durability and reliability of turbomachinery components, since those characteristics impact operational and maintenance costs and flying safety.…”

Section: Hcf Problemmentioning

confidence: 99%

Computational investigation of aeromechanical HCF effects in a compressor rotor

White

2001

37th Joint Propulsion Conference and Exhibit

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“…Newer high-performance turbomachinery blade designs have led to decreased blade damping and higher vibratory stresses 1 . This increases design and maintenance costs, but also can cause component failure.…”

Section: Turbomachinery Blade Dampingmentioning

confidence: 99%

Damping of high-temperature shape memory alloys

Duffy¹,

Padula²,

Scheiman³

2008

Behavior and Mechanics of Multifunctional and Composite Materials 2008

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Researchers at NASA Glenn Research Center have been investigating high temperature shape memory alloys as potential damping materials for turbomachinery rotor blades. Analysis shows that a thin layer of SMA with a loss factor of 0.04 or more would be effective at reducing the resonant response of a titanium alloy beam. Two NiTiHf shape memory alloy compositions were tested to determine their loss factors at frequencies from 0.1 to 100 Hz, at temperatures from room temperature to 300 o C, and at alternating strain levels of 34-35x10 -6 . Elevated damping was demonstrated between the M s and M f phase transformation temperatures and between the A s and A f temperatures. The highest damping occurred at the lowest frequencies, with a loss factor of 0.2-0.26 at 0.1 Hz. However, the peak damping decreased with increasing frequency, and showed significant temperature hysteresis in heating and cooling.

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High cycle fatigue of turbomachinery components - Industry perspective

Cited by 31 publications

References 8 publications

Laser Displacement Measurements of Fan Blades in Resonance and Flutter During the Boundary Layer Ingesting Inlet and Distortion-Tolerant Fan Test

Laser Displacement Measurements of Fan Blades in Resonance and Flutter During the Boundary Layer Ingesting Inlet and Distortion-Tolerant Fan Test

Computational investigation of aeromechanical HCF effects in a compressor rotor

Damping of high-temperature shape memory alloys

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