Damage Tolerance Analysis of Aero-Engine Fan Blade - Engineering Assignment Help

Assignment Task :

Summary 

This unit is assessed by a report containing two pieces of coursework of equal weighting (50%). 

The coursework draws on experience from industrial consulting work on the application of fracture mechanics and creep-fatigue analysis, and is aimed at providing a realistic opportunity for work experience at engineering consulting in some of the key areas of structural integrity assessment. 

Instructions: 

You are expected to start with a literature review on the background and recent developments of the subject, followed by a search for material data and test standards, which should help you with the quantitative assessments. The report should follow the following format: introduction, literature review, methods, analysis, discussion, conclusions and references; and should be written clearly in technical terms, using figures/tables as necessary. References must be given and cited in the text. The word limit for the report is 3000 words (each up to 1500 words, or approximately 5 pages A4). 

Please refer to the specific requirements and marking criteria in each assignment. 

Although discussion and team work are encouraged, your report must be a piece of independent, individual work. Submissions will be through a Moodle dropbox where Turnitin facility will be used to monitor and detect similarity in all submissions. Students are warned of the risk of failing the unit, or a significant loss of marks, if a high similarity is reported by Turnitin indicating plagiarism. 

Project I: Damage Tolerance Analysis of Aero-Engine Fan Blade 

You have just joined an engineering consulting firm specialising in damage tolerance analysis. Your client, an aero-engine manufacturer, requested a fracture mechanics analysis of fan blade  

Specifically, they requested that the component is to be simplified as a centre-cracked panel and the centrifugal force experienced as uniformly distributed tensile stresses across the ends of the panel. Ti-6Al-4V is used currently, and a conservative estimate of an initial defect size from two independent NDT inspections found 2a=0.5 mm. W=0.5m. The client is interested in the following information: 

1. Would fatigue crack growth occur under an operational cyclic stress range -30 to 220 MPa? 

What if the maximum stress is increased by 50% whilst the stress range stays the same? 2. If the component is sufficiently strong to sustain an overload of 5 times of the maximum nominal stress 220 MPa? 3. When an inspection should be scheduled, if this must be done at 70% of component life predicted for a baseline loading cycle 0 – 220 MPa? 4. What if this major cycle is superimposed with a vibrational minor cycle 200-240 MPa? 

Should the inspection period be revised? 

Although not part of the client’s briefing, your project manager suggested that you should also: 

5. Find the background information on fan blades of aero-engines, and the essential material information about Ti-6Al-4V and its properties from literature. In particular:

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