8/8/2019 pre_pro_DSB

http://slidepdf.com/reader/full/preprodsb 1/12

M.S.Ramaiah School of Advanced Studies 1

Pre-Project Presentation

Simulation of Fan Blade Out EventIn a Gas Turbine Engine

Devendra Singh BhatiBSB0909001, FT09

M. Sc. (Engg.) in Rotating Machinery Design

8/8/2019 pre_pro_DSB

http://slidepdf.com/reader/full/preprodsb 2/12

M.S.Ramaiah School of Advanced Studies

Introduction

2

Fan blade is the largest and heaviest

rotating blade of aircraft engine.

Being in front of the engine it is

more prone to FOD too. Failure can

occur in fan blade while operating at

maximum r.p.m. The fan blade outof the turbofan engine can impact on

the casing.

The blade out event cause unbalance mass and nature of the contact is

friction, damage and impact between blade and casing. The fan blade

detach from the fan and it will fly in a radially outward direction to

impact on containment portion.

8/8/2019 pre_pro_DSB

http://slidepdf.com/reader/full/preprodsb 3/12

M.S.Ramaiah School of Advanced Studies 3

Aim of the Project

To excess the structural integrity of fan Blade containment

structures through finite element simulation.

8/8/2019 pre_pro_DSB

http://slidepdf.com/reader/full/preprodsb 4/12

M.S.Ramaiah School of Advanced Studies 4

Project Objectives

To review the literature on fan blade of gas turbine.

To arrive at procedure of finite element simulation for the fan

 blade out event.

To develop the finite element model of the containment structureand fan blade.

To solve the develop finite element model at a particular 

situation.

To excess the structural integrity of the existing blade

containment structure.

8/8/2019 pre_pro_DSB

http://slidepdf.com/reader/full/preprodsb 5/12

M.S.Ramaiah School of Advanced Studies 5

Methods and Methodology

Literature review for structural design and crash/impact analysis

of fan blade will be carried out by referring reviewed journals,

 books, manuals and related documents.

Based on literature survey the problem statement is understood.

The finite element model for fan blade and containment structure

using commercial tool will be develop.

8/8/2019 pre_pro_DSB

http://slidepdf.com/reader/full/preprodsb 6/12

M.S.Ramaiah School of Advanced Studies 6

Methods and Methodology

Geometrical model will be prepared using CATIA and analysis is

carried out using LS-DYNA.

Finite element simulation for fan blade out event.

From the simulation identify the critical area and what would be

the major possibilities near casing.

8/8/2019 pre_pro_DSB

http://slidepdf.com/reader/full/preprodsb 7/12

M.S.Ramaiah School of Advanced Studies 7

Place of work 

M. S. Ramaiah School of Advanced Studies

8/8/2019 pre_pro_DSB

http://slidepdf.com/reader/full/preprodsb 8/12

M.S.Ramaiah School of Advanced Studies 8

Project ScheduleActivity Week 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28

pre-Project Presentation

Literature review

Creation of geometric model

F.E. modelling

Simulation of F.E. model

post processing of results

Interim review

Study to meet design specification

Simulation for modified parameters

Post processing of results for modified parameters

Preparation of draft copy for final dissertation

Final presentation

Submission of tech. paper and final dissertation

8/8/2019 pre_pro_DSB

http://slidepdf.com/reader/full/preprodsb 9/12

M.S.Ramaiah School of Advanced Studies 9

Resources

Computing Resources

PC with 2 GB RAM, Pentium 4 Processor 

Software Resources

CATIA

HYPERMESH

ANSYS

LS-DYNA

LiteratureBooks, Journals

8/8/2019 pre_pro_DSB

http://slidepdf.com/reader/full/preprodsb 10/12

M.S.Ramaiah School of Advanced Studies 10

Literature

Books

Journal Papers

Web refer 

8/8/2019 pre_pro_DSB

http://slidepdf.com/reader/full/preprodsb 11/12

M.S.Ramaiah School of Advanced Studies 11

Literature Journal Papers/ Literature

1. Kulak A.C. (1995), Aircraft fan containment structure.

International patent application no. ± PCT/US95/04963.

2. Rolls Royce PLC (1996) , Containment structure. US patent no.-

5513949.3. GE Company (1985) , Blade containment structure. US patent no.-

4534698.

4. Kelly S.C. , Lawrence C and Carney D.V. (2002), Aircraft engine

fan blade out dynamics, 7th international LS-DYNA user 

conference, held may 19-21 2002 at Dearborn, US. P 14-25.

5. Sinha S. K. and Dorbala S. (2009), Dynamic load in fan

containment structure of turbofan engine, J aerospace energy, vol.

22, issue 3, P 260-269.

8/8/2019 pre_pro_DSB

http://slidepdf.com/reader/full/preprodsb 12/12

M.S.Ramaiah School of Advanced Studies 12

Benefits of the work 

Will it result into a publication? yes

Will it result into a product? no

Will it be a solution to an existing problem

of an industry? yes

Is it pursued for academic interest? Yes