A Study of the Contact Interface for Compressor Blisks with Ring Dampers Using Nonlinear Modal Analysis

Yekai Sun,Loïc Salles,Jie Yuan,Enora Denimal

doi:10.1088/1757-899x/1081/1/012041

Yekai Sun, Loïc Salles + Show 2 more

Open Access

https://doi.org/10.1088/1757-899x/1081/1/012041

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Abstract

The integrally bladed disks, also known as blisks, have been widely used in industrial turbomachinery because of their benefits in aerodynamic performance and mass reduction. Friction damping is considered as the major damping sources in turbomachinery. However, in blisks, the friction damping is negligible due to the lack of the contact interfaces. The friction ring dampers are one of the emerging external damping sources for blisks. In this paper, a full-scale blisk with a friction ring damper is studied, where a 3D contact element is used to compute the contact frictions. The blisk and ring damper is investigated using their damped nonlinear normal modes. The modal damping can be directly calculated and used to quantify the friction damping generated by the ring damper. The contact behaviour within the contact interface is further analysed. The nodes with initial gap show less damping ability. The separations within the contact interface are expected to be avoided to achieve a better damping performance.

Highlights

The bladed disk is an important structural component in industrial turbomachinery
The large vibrational stress on the bladed disks leads to the high cycle fatigue which is considered as the major reason for most failures of aircraft engines
When the vibration amplitude is greater than 1.5 × 10−2 mm, the contact pairs within the contact interface start to slide leading a softening effect

Summary

Introduction

The bladed disk is an important structural component in industrial turbomachinery. The bladed disks are almost designed to their structural limit due to the higher efficiency required. The bladed disks are usually working under extreme environment, i.e. high thermal stress, centrifugal stress and vibration loading. The large vibrational stress on the bladed disks leads to the high cycle fatigue which is considered as the major reason for most failures of aircraft engines. The material damping and aerodynamic damping are relatively low. The external damping source is required to reduce the vibrational amplitude under resonance. The friction damping is a common and effective damping technique used in industrial turbomachinery. The friction dampers have been well-established in literature [5, 12, 18]

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