Abstract
Turbo-pump is an essential component in any rocket engine. The airfoil (NGTE 10C4 series) section of a rotor blade in the SSME (Space Shuttle Main Engine) was modelled along with a far-field of suitable shape and dimensions. The model was suitably discretized with proper amount of refinement, etc. A numerical simulation was then carried-out using ANSYS software with several iterations of varying inlet boundary conditions to check for any improvement in the performance of the rotor blade. Inlet velocity for optimum functionality of the blade was identified.
| Original language | English |
|---|---|
| Article number | 012221 |
| Journal | Journal of Physics: Conference Series |
| Volume | 1706 |
| Issue number | 1 |
| DOIs | |
| Publication status | Published - 22-12-2020 |
| Event | 1st International Conference on Advances in Physical Sciences and Materials 2020, ICAPSM 2020 - Coimbatore, Virtual, India Duration: 13-08-2020 → 14-08-2020 |
All Science Journal Classification (ASJC) codes
- General Physics and Astronomy
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