1. Mark G. Turner, University of Cincinnati Ali Merchant, MIT
Applications of a Turbomachinery Design Tool for Compressors and Turbines
Mark G. Turner, University of Cincinnati
Ali Merchant, MIT
Dario Bruna, University of Genoa, Italy
2007 Joint Propulsion Conference, July 9, 2007
Cincinnati, Ohio
AIAA

2. Observatory Dedication
Wednesday at 7:30
Viewing when dark
Saturn and Venus will set soon after viewing
Really cool
Graeter’s Ice Cream

3. Outline T-AXI system Demonstration Cases Conclusions
2 stage compressor
3 stage low pressure turbine
Conclusions

4. T-AXI System T-AXI T-T_DES T-C_DES bladedata-xxx.dat stack.xxx
blade3d.brx
stack.xxx
walls.xxx
Blade Viewer
Blade Volume
Mises files
Mises
T-C_DES
init.xxx
igv.xxx
stage.xxx
tcdes-results.xxx
Compressor design code
3D mesh +
Solution
Compressor or Turbine 3D RANS
Blade Design
Feedback To T-AXI
T-T_DES
ogv.xxx
ttdes-results.xxx
Turbine design code

5. T-C_DES & T-T_DES
T-C_DES is similar to COMPR that Mattingly distributes in textbook
Added blockage, bleed and gaps
Free vortex, first power and exponential swirl distributions
SI and English Units
Run from command prompt and files
Writes input for T-AXI
Default is to run with coupled boundary layer
Good documentation
T-T_DES is similar to TURBN that Mattingly distributes in textbook
Specify mean radius for each blade row, not whole machine
Free vortex
Default is to run without coupled boundary layer
Documentation not yet written

6. T-AXI
Axisymmetric Solver based on the multiple interacting streamtube Euler equation formulation created by Mark Drela, Mike Giles and Hal Youngren: Mises & mtsol
Capability presented at IGTI in 2006 & 2007 with good agreement with several test cases
Versions have been used in actual designs by Ali Merchant
Coupled Boundary Layers
Stack and Walls files have nondimensional input
Uses a Newton-Raphson solver for frozen entropy for fast solution
Loss models for compressors and turbines: profile, shock, clearance, endwall, secondary flow
Loss is “mixed out” after each blade row
Design mode: Angular momentum is specified-angles come out
Output Table lists profiles of velocity triangles, loss and performance at leading and trailing edges
Blade shapes based on meanline-thickness output for Mises and to visualize

7. HPC and LPT Demo
This talk is have another opportunity to demonstrate T-Axi by starting from an existing design
Demo
Started from GE EEE test cases
Used 10 stage compressor to create a 2 stage design
Design goal was to test a time accurate solver with few passages with periodicity
Used 5 stage lpt to create a 3 stage design
Need to run through quickly
Want to demonstrate process

8. Profiles

9. Conclusions
An axial compressor and turbine design system has been presented
Made available to be used as a teaching tool
Relatively simple demonstrations presented
Documentation is a work in progress
Future capabilities will be based on interest and author’s priorities
Web site

10. Testimonial
“I can't tell you how much we appreciate your help. Naiara and I have made more progress in one week with T-Axi than we made in 6 months with UDO300.”
- Christopher L Cassano, Embry-Riddle Aeronautical University graduate student working on an advanced counter-rotating compressor. Using Excel to drive T-Axi.

11. Thank You Questions?