Fretting Fatigue Experiment and Finite Element Analysis for Dovetail Specimen at High Temperature
Source abstract
Abstract
The dovetail attachment between the turbine blade and disk for an aero-engine operates under varying centrifugal load and vibration at elevated temperatures. The fretting fatigue is prone to occur at the contact surface of the dovetail attachment. This paper investigated the fretting fatigue behavior of the dovetail specimen at 630 °C through experiment and numerical simulation, in which the blade-like dovetail specimen is nickel-based single crystal superalloy DD10 while two fretting pads in contact with the dovetail specimen simulating the mortise of the disk are made of powder metallurgy FGH99. It is revealed from all the tests that the fracture induced by the fretting wear occurs at the upper edge area of the contact surface. The contact surface near the upper edge is more severely worn; hence, the phenomenon of partition on the worn contact surface can be observed, which is consistent with the fretting fatigue mechanism. Moreover, the calculated area of maximum contact pressure gradient through finite element method is in good agreement with the experimental position of the initial fretting fatigue cracks.
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Research context
OpenAlex topics: Mechanical stress and fatigue analysis · Electrical Contact Performance and Analysis · Metal Alloys Wear and Properties
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
Affiliations
School of Energy and Power Engineering, Beihang University, Beijing 102206, China
Beijing Aerospace Propulsion Institute, Beijing 100076, China
Aero Engine Academy of China, Beijing 101304, China
Beijing Key Laboratory of Aero-Engine Structure and Strength, Beijing 102206, China
Research Institute of Aero-Engine, Beihang University, Beijing 102206, China
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