Impact of Bolt-Nut Interface Modeling Assumptions on the Calculated Low Cycle Fatigue Life of Aircraft Engine Turbine Rotor Bolted Joints.
Jensen, Luke.
2012
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Abstract: Finite element analysis is used extensively in the aircraft turbine
engine industry to predict stresses to calculate low cycle fatigue (LCF) life. An accurate
prediction of stresses is especially important to a specific subset of engine hardware that
is defined by the FAA as life-limited parts (LLP's). LLP's include rotor and major
structural parts such as disks, spacers, hubs, shaft... read mores, high pressure casings, and
non-redundant mount components. A failure of an LLP can lead to a potentially catastrophic
event due to non-containment of high energy debris, uncontrolled fire, or a complete
inability to shut the engine down. Under-predicted stress can cause the life limits to be
set too high, which is a safety hazard. Over-predicted stress can cause the life limits to
be set too low, which adds cost due to the need to replace expensive engine hardware more
frequently. High fidelity stress analysis is necessary to appropriately set LCF life
limits. One common engine feature analyzed with 3D stress analysis is a rotor bolted joint.
Geometrical features associated with bolted joints such as holes, fillets, and scallops
cause stress concentrations. Often the life limiting feature in a rotor LLP is a
geometrical feature in close proximity to the joint. Unfortunately, the detailed stress
analysis associated with accurately predicting stress in the joint is costly and time
consuming. Analysis assumptions that can simplify the effort, yet still produce accurate
results, would be valuable to the industry. The focus of this study is on the bolt-nut
interface modeling assumptions associated with a rotor bolted joint stress analysis for LCF
predictions. A 3D finite element model of an actual aircraft engine rotor bolted joint is
created. A series of eleven cases are analyzed and compared to investigate how the thread
modeling assumptions affect the calculated life in the mated rotor LLP hardware.
Walker-adjusted alternating stress, σ0,alt, is used to
measure the life impact. The impact is limited to the edges of the two critical features
closest to the bolt-nut interface. The results demonstrate that factors such as the thread
mesh density, elastic versus elastic-plastic bolt/nut material properties, and the
inclusion of the helical thread shape have only minor impact. The inclusion of contact
elements at the interface instead of couples has a moderate impact of 1.1 to 1.2 ksi. When
couples are used, the placement of the first couple is critical, impacting the results by
1.1 to 2.6 ksi. Also, when couples are used to join the interface, the explicit inclusion
of the thread shape has only 0.5 to 0.6 ksi impact.
Thesis (M.S.)--Tufts University, 2012.
Submitted to the Dept. of Mechanical Engineering.
Advisor: Anil Saigal.
Committee: Thomas James, and David Kelpe.
Keyword: Mechanical engineering.read less - ID:
- 9k41zr66h
- Component ID:
- tufts:21102
- To Cite:
- DCA Citation Guide EndNote
