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Mechanical loads on a turbofan engine structure at blade-off
2009 (English)Independent thesis Advanced level (professional degree), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

Aircraft engine development is an expensive and time consuming business. The engines have to be designed to withstand loads well above those encountered during normal operating conditions. To meet the certification requirements manufacturers conduct tests where the engines are subjected to extreme conditions and loads. One such extreme condition is fan blade-off (FBO). Using finite element methods (FEM) computational software one can simulate FBO conditions and predict what loads it will inflict on the engine structure. These simulations involve large models that contain many degrees of freedom. As such they are time consuming to create and evaluate. Also they demand a detailed knowledge of the engine geometry to create. In preliminary design studies of engines there exists a need for knowing the loads an engine is subjected to. This provides the design team with valuable information that is used in decisions regarding engine architecture. The aim of this thesis is to create a scaled-down, simpler model of a turbofan engine, that can be used to predict bearing and engine mount loads, for a fan blade-off event. In addition the model can be used to estimate or check other parameters like weight and to compare different engine architectures. The turbofan model created was based on rotor dynamics, this model was created in MATLAB and DyRoBeS rotor dynamic simulation software. The simulations were done on three turbofan engines: a reference engine to validate the turbofan model and later applied on two proposal turbofan engines for the coming Next generation Single Aisle (NSA) aircraft. The results for the simulations show that the turbofan model can be used in the conceptual design stage. It can provide the design team with an initial estimate for bearing and engine mount loads. Taking into account the simplicity of the turbofan model, a conclusion on the accuracy of the results is that they are within acceptable limits.

Place, publisher, year, edition, pages
Keyword [en]
Technology, rotor dynamics, turbofan model, FBO, fan blade-off, mechanical, loads, aircraft engine
Keyword [sv]
URN: urn:nbn:se:ltu:diva-56753ISRN: LTU-EX--09/101--SELocal ID: d80a30f4-e6c0-403a-8cf6-f68bce9afe22OAI: diva2:1030140
Subject / course
Student thesis, at least 30 credits
Educational program
Space Engineering, master's level
Validerat; 20101217 (root)Available from: 2016-10-04 Created: 2016-10-04Bibliographically approved

Open Access in DiVA

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