Stress Analysis On Compressor Blades

1. STRESS ANALYSIS ON
COMPRESSOR BLADES DURING
BIRD STRIKE
21955A2107 & 21955A2109

2. OVERVIEW
EXCEED
2
INTRODUCTION
PROBLEM
STATEMENT/OBJECTIVE
PROPOSED SOLUTION
TECHNOLOGY USED
METHODOLOGY

3. MEET OUR TEAM
EXCEED
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SAINATH REDDY
GANGIDI
21955A2109
NISHANTH
GADAPA
21955A2107

4. INTRODUCTION
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• Bird strikes on aircraft mostly occur during take-off or landing
stages and during the cruising phase as the large open fields
surrounding the airports provide perfect feeding, nesting, and
resting areas for large species of birds.
• US Airways Flight 1549, Airbus A320 in January 2009, is one of
the major incidents of bird strike in the USA. After the impact
both the engines on the aircraft lost power and the aircraft
ditched into the Hudson river. A number of the passengers were
treated for hypothermia, but only five people suffered more

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FIG 1: US Airways flight
1549
FIG 2: US Airways flight
1549

6. PROBLEM
STATEMENT/OBJECTIVE
• The main aim of this analysis is to make airliners understand the process after a bird
strike and take precautions to avoid bird strikes.
• Bird strikes are a major risk to an aircraft, especially during the take-off and landing
stages. It may result in significant loss of human life and property damages worth
millions annually in the US alone. This analysis is done to understand the losses
caused by bird strikes.
• Mostly occurs at a low altitude or on the ground i.e. runways during take-offs and
landings. With the increase in the number of annual flights, Bird strike incidents
have also increased.
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7. PROPOSED SOLUTION
• The goal of this work was to develop a methodology to examine the damages and
failure of an aircraft engine (fan assembly) subjected to bird impact. The work is
focused on scenarios where a bird directly impacts the rotating fan assembly since
this presents the most destructive impact scenario.
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8. TECHNOLOGY USED
• The Computer Aided Three-Dimensional Interactive Application (CATIA) is a
geometric modelling software developed by Dassault Systems. It is the leading
commercial computer program used in product development solutions for various
industries, such as aerospace, automotive, electrical, electronic etc., which provides
greater flexibility in modelling irregular contours.
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9. TECHNOLOGY USED
• ANSYS is a general-purpose, finite-element modelling package for numerically
solving a wide variety of mechanical problems. These problems include
static/dynamic, structural analysis, heat transfer, fluid problems, and acoustic and
electromagnetic problems.
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PRESENTATION
TITLE

10. METHODOLOGY/PROOF OF
CONCEPT
• The fan blade shape was inspired by a general commercial aviation fan blade
geometry used in smaller turbofan engines Blades were modelled with their bases
fixed using rigid connections constraining both translational and rotational motion
relative to the central hub.
• A uniform thickness of 3 mm was allotted to the blades, this is in accordance with
the average blade thickness in smaller turbofan engines. The diameter of the
assembled model (blades and hub) was 1.75m.
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11. METHODOLOGY/PROOF OF
CONCEPT
• Material assumed (TITANIUM
ALLOY)
• Density, ρ (kg/m3) 4420
• Elastic Modulus, E (GPa) 112.5
• Poisson’s Ratio υ 0.31
• Post-Yield Modulus Ey (GPa) 1.59
• Yield Strength Sy (MPa) 980
• Ultimate Strain εf 0.1
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Fig 4. stress analysis on
compressor blades

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PRESENTATION
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Fig 5. Bird strike analysis on
compressor blades

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PRESENTATION
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15. CONCLUSION
• The objective of the study was to develop a computational methodology to certify an
aircraft engine for bird strike. It was validated by impacting it on Titanium blades of
varying thicknesses at various speeds. The results obtained were then compared
with the experimental results from the real scenarios.
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16. THANK YOU
21955A2109 | 21955A2107