slide1
Download
Skip this Video
Download Presentation
Figure 1 – NSTX Upper Umbrella Assembly Baseline Upgrade Design

Loading in 2 Seconds...

play fullscreen
1 / 35

Figure 1 – NSTX Upper Umbrella Assembly Baseline Upgrade Design - PowerPoint PPT Presentation


  • 98 Views
  • Uploaded on

Figure 1 – NSTX Upper Umbrella Assembly Baseline Upgrade Design. G10 Support. G10 Support. Figure 2 – Single Segment Strap Assembly with Baseline Design G10 Supports. Figure 3 – Single Segment Strap Assembly w/o G10 Supports. Figure 4 – Single Segment Strap Assembly: Center Strap Only.

loader
I am the owner, or an agent authorized to act on behalf of the owner, of the copyrighted work described.
capcha
Download Presentation

PowerPoint Slideshow about ' Figure 1 – NSTX Upper Umbrella Assembly Baseline Upgrade Design' - palma


An Image/Link below is provided (as is) to download presentation

Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author.While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server.


- - - - - - - - - - - - - - - - - - - - - - - - - - E N D - - - - - - - - - - - - - - - - - - - - - - - - - -
Presentation Transcript
slide2

G10 Support

G10 Support

Figure 2 – Single Segment Strap Assembly with Baseline Design G10 Supports

slide5

Rout = 5.688”

38 Laminations:

- .060” thk; .005” gap

Mat’l: Copper

Wtfull = 37.4 lb

(Wtarch = 20.4 lb)

Rin = 3.160”

7.5”

Bpol= .3 T

5”

I = 130 kA

Uvertthermal = .3 in

Btor = 1 T

Uradthermal = .018 in

2.523”

2”

Figure 5 – Single Laminated Strap Assembly with Applied Fields and Current

slide6

Calculated EMAG Loads

Fop

Out-of-Plane Load (z-direction)

I+

R

Fop = 2*I*Bpol*R

Fop = 2 x 130,000 A/ 38 x .3 T x 5.688/39.37 m

Fop = 296.4 N = 66.6 lbf [per lamination]

Bpol

In-Plane Load (y-direction)

pressip

Fip/ L = I*Btor

Fip/ L = 130,000 A/ 38 x 1 T [per lamination]

Fip/ L = 3,421 N/ m x .2248 lbf/ N x 1 m/ 39.37 in

Fip/ L = 19.53 lbf/ in

pressip = (Fip/ L)/ w

pressip = 19.53 lbf/in / 2 in

pressip = 9.77 lbf/ in2 (applied to inside cylindrical faces)

x x x x x

x x x x x x

x x x x x x x

I+

w

Btor

slide7

Force = 66.6 lbf

Ux = .018 in

Uy = .3 in

Uz = 0

Press = 9.7 psi

Fixed

3 Elements thru Thickness

Figure 6A – Single Lamination FEA Model: Mesh

slide8

Figure 6B – Single Lamination Linear Results: von Mises Stress

Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

slide9

Figure 6C – Single Lamination Linear Results: von Mises Stress

Loads: Thermal Displacements Only

slide10

Figure 6D – Single Lamination Linear Results: von Mises Stress

Loads: In-Plane (Pressure) Load Only

slide11

Figure 6E – Single Lamination Linear Results: von Mises Stress

Loads: Out-of-Plane (Force) Load Only

slide12

Large deflection = On

Figure 6F – Single Lamination Nonlinear Results: von Mises Stress

Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

slide13

Large deflection = On

Figure 6G – Single Lamination Nonlinear Results: Z-Deformations

Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

slide14

Large deflection = On

Figure 6H – Single Lamination Nonlinear Results: Z-Deformations_Front

Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

slide15

σhoop = P*R/ t

= 9.77 psi x 5.688 in/ .060 in

= 924 psi

Large deflection = On

Figure 6J – Single Lamination Nonlinear Results: von Mises Stress

Loads: Emag Pressure (In Plane) Only

slide16

1st Mode

Load Multiplier = 58.4

1st Mode

Load Multiplier = 58.4

3rd Mode

Load Multiplier = 117.6

(Nonlinear 1st Mode

Load Multiplier = 50)

Large deflection = Off

2nd Mode

Load Multiplier = 73.0

Figure 6K – Single Lamination Pre-Stressed Linear Buckling Results

Load multiplier LMF applies to all Emag loads and thermal displacements

slide17

Y

LMF = 14

0

80

Large deflection = On

Figure 6L – Single Lamination Nonlinear Buckling: Y-Deformation at Onset (1)

Load multiplier factor LMF applies only Out-of-Plane Emag load

slide18

Y

LMF = 26

0

80

Large deflection = On

Figure 6M – Single Lamination Nonlinear Buckling: Y-Deformation at Onset (2)

Load multiplier factor LMF applies only to Out-of-Plane Emag load

conclusions
Conclusions
  • Buckling due mostly to out-of-plane load. In-plane load (pressure outward) reduces buckling; thermal displacements slightly increase buckling.
  • Good agreement between linear and nonlinear buckling results with load multiplier factor applied to both Emag loads and to thermal displacements.
  • Load multiplier factor over 14 for nonlinear analysis with constant in-plane load and increasing out-of-plane load (conservative).
slide20

3 Elements / Lamination

Figure 7A – 3 Lamination FEA Model: Mesh

slide21

Large deflection = On

Frictional contact (COF = .4)

Figure 7B – 3 Lamination Nonlinear Results: von Mises Stress

Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

slide22

Large deflection = On

Frictional contact (COF = .4)

Figure 7C – 3 Lamination Nonlinear Results: Z-Deformations

Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

slide23

Large deflection = On

Frictional contact (COF = .4)

Figure 7D – 3 Lamination Nonlinear Results: Z-Deformations_Front

Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

slide24

Large deflection = On

Frictional contact (COF = .4)

Figure 7E – 3 Lamination Nonlinear Results: Contact Status

Loads: Combined Thermal Displacements, Emag Press. (In Plane) and Forces (OOP)

slide25

3rd Mode

Load Multiplier = 61.8

1st Mode

Load Multiplier = 58.2

Large deflection = Off

Frictional contact (COF = .4)

2nd Mode

Load Multiplier = 60.7

Figure 7F – 3 Lamination Results: Linear Buckling Mode Multiplier

Load Multiplier factor LMF applies to all Emag loads and thermal displacements

slide26

Figure 8A – Single Laminated Strap Assembly FEA Model: Bonded and Frictionless Contact Areas

slide27

3 elements/ lamination

# Nodes = 850423

# Elements = 152895

Figure 8B – Single Laminated Strap Assembly FEA Model: Mesh

slide28

Large deflection = Off

Frictional contact (COF = 0)

Fig. 8C –Laminated Strap Assembly FEA Results - Thermal Displacements Only: von Mises Stress

slide29

Large deflection = Off

Frictional contact (COF = 0)

Fig. 8D –Laminated Strap Assembly FEA Results – Thermal Displacements Only: Total Deformation

slide30

0 V

130,000 A

Fig. 9A – Single Segment_Center Strap Electric Model: Boundary Conditions

slide31

By = .3T

Bz = 1 T

ux = .018”

uy = .30”

I = 130 kA

JS

FLorentz

Non-Linear

Large Deflection

Non-Linear

Large Deflection

Heat Gen

Tnodes

Fig. 9B – Upper Flex Strap ANSYS Multiphysics Analysis Work Flow Diagram

ad