REDESIGN OF AN AIRCRAFT ENGINE EQUIPMENT USING 3D DYNAMIC WHOLE ENGINE MODEL - PowerPoint PPT Presentation

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REDESIGN OF AN AIRCRAFT ENGINE EQUIPMENT USING 3D DYNAMIC WHOLE ENGINE MODEL

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Title: REDESIGN OF AN AIRCRAFT ENGINE EQUIPMENT USING 3D DYNAMIC WHOLE ENGINE MODEL


1
REDESIGN OF AN AIRCRAFT ENGINE EQUIPMENT USING 3D
DYNAMIC WHOLE ENGINE MODEL
  • Company SNECMA MOTEUR
  • Engineering System Integration Division
  • Author Alain Mazelet

2
Background of the study
  • Baseline engine in service
  • New application implies modification of one or
    more equipments
  • Impact of these modifications on engine carcass
    integrity is not a concern
  • Main concern is local impact around equipment
  • Need to assess if local redesign is required to
    comply with blade out regulation
  • WEM model is used to redesign equipment without
    blade out test

3
Calculation process for the base line equipment

SNECMA Test division
Forced response test data
Correlation
Bladeout test data
Correlation
Correlation
Forced response calculation
Bladeout calculation
Interface acceleration
SNECMA Integration division
WEM
Simplified equipment model
Detailed equipment model
Stress analysis
Equipment designer
4
Calculation process for the modified equipment
SNECMA Test division
Vib. survey test data
Correlation
SNECMA Integration division
Vib. survey calculation
WEM
Simplified equipment model
Equipment designer
5
Equipment models
  • Simplified model enables general loads and
    displacement calculation beam / shell / masses /
    springs / rigid bodies
  • Detailed model enables stress analysis volume
    elements model
  • Equipment

6
Forced response test
  • Equipment is mounted on fan frame and fan case to
    get adequate boundary conditions
  • White noise excitation is produced with a dash
    pot (0-300 Hz)
  • 83 dofs are measured on the structure with
    accelerometers
  • 57 modes are detected, we focus on 17 which were
    more representative of equipment displacement

F
7
Forced response test / model correlation
  • Correlation parameters mount stiffness , flange
    stiffness, masses and inertia
  • Correlation method MAC / FDAC for deform shape
    correlation, FRF comparison for each
    accelerometer.
  • Good correlation was achieved between 30 and 150
    Hz

8
Whole engine blade out model
  • Whole engine and test rig model (shell, beam,
    masses, rigid bodies )
  • NASTRAN V69.1 (SOL109) DMAP alter for
    gyroscopic effect
  • Non linear element between fan and fan case
  • 330 000 dofs (11000 after condensation)
  • Loads unbalance load (one blade), impact of the
    blade on the fan case, decrease of thrust load,
    and deceleration moment.

9
Blade out test / model correlation
bearing load
Equipment link load
calculation test
Equipment acceleration
10
Equipment design
  • PROCESS
  • Run blade out transient calculation
  • Extract engine / equipment interface acceleration
  • Run detailed equipment transient response under
    enforced interface motion (Lagrange multiplier
    method or big mass method)
  • Conduct stress analysis

Interface acceleration
Bladeout calculation with simplified equipment
model
Detailed equipment model
Stress analysis
  • SNECMA Moteur does not need to export WEM, DMAP
    etc
  • Equipment designer does not need to export
    detailed model
  • SNECMA and equipment designer do not need to have
    the same FEM code, no translation is needed

11
CONCLUSION
  • WEM gives a satisfactory representation of the
    engine behaviour
  • Engine equipment design can be achieved with
    dynamic transient criteria, static equivalent
    criteria are not used anymore.
  • Data exchanges between SNECMA and equipment
    designers are limited to interface acceleration
  • MSC/NASTRAN DMAP solutions give us the capacity
    to run the whole process including condensation,
    non linear elements, stress analysis ...
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