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.
Highlights
IntroductionPublisher’s Note: MDPI stays neutral with regard to jurisdictional claims in published maps and institutional affiliations
Academic Editor: Filippo BertoReceived: 26 September 2021Accepted: 21 October 2021Published: 23 October 2021Publisher’s Note: MDPI stays neutral with regard to jurisdictional claims in published maps and institutional affiliations.Licensee MDPI, Basel, Switzerland.Fretting fatigue is prevalent in the contact structure for an aero-engine, especially in the blade-disk connecting structure, such as the dovetail attachment [1]
Due to the vibration caused by the impact of high-temperature airflow and the varying centrifugal load, the contact surfaces of the dovetail attachment are prone to fretting fatigue [2]
Summary
Publisher’s Note: MDPI stays neutral with regard to jurisdictional claims in published maps and institutional affiliations. Fretting fatigue is prevalent in the contact structure for an aero-engine, especially in the blade-disk connecting structure, such as the dovetail attachment [1]. Due to the vibration caused by the impact of high-temperature airflow and the varying centrifugal load, the contact surfaces of the dovetail attachment are prone to fretting fatigue [2]. Typical characteristics of fretting fatigue are fretting wear debris and pitting corrosion on the dovetail contact surfaces. Fretting wear will lead to the crack initiation and crack propagation, which causes a severe non-containment accident of the aero-engine [3]
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