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-2007-5152

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

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

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

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

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

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

Profiles

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 http://gtsl.ase.uc.edu/T-AXI

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.

Thank You Questions?