Containment of blade shedding in gas turbine engines: part II—experimental and numerical investigations
Source abstract
Abstract
In Part I, we purposely designed, developed and commissioned an instrumented functional scaled down test rig to examine blade shedding in gas turbine engine experimentally and numerically using the finite element method. Specifically, in Part II, we examine two cases involving blade shedding incidents. In the first, we study the interaction between a released and a trailing blade and in the second, we study the interaction between a released blade and a fully bladed disk. Three aspects of the work were accordingly examined in these two cases: (1) blade shedding trajectory, its interaction with the trailing blades and the containment ring, (2) the contact stresses in the containment ring as a result of the impingement of the released blade, and (3) the dynamic forces transmitted to the rotor mounting. Remarkably, the experimental results of the scaled down tests confirm the finite element predictions of a typical fan disk. In particular, they clearly show the influence of the trailing blades on the trajectory of the released blades, the large deformation of the trailing blades as a result of the momentum transfer between the trailing blades and the released blade, the final confinement of the released blade near the tip of the trailing blades and the stresses induced in the containment ring as a result of contact impingement. The results of our work should aid in the design of a proper containment ring and enhance the safety of gas turbine engines.
Source: openaire · Quality: candidate unverified · Source record ↗
Research context
OpenAlex topics: Bladed Disk Vibration Dynamics · High Temperature Alloys and Creep · Tribology and Lubrication Engineering
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
References (20)
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