Abstract
Transonic tests in linear cascade wind tunnels can suffer
from significant test section boundary interference effects in pitch. A slotted tailboard has been designed and optimised with an in-house Euler numerical method to reduce such ef- fects. Wind tunnel measurements on an overspeed Mach 1.27 discharge from a Rolls-Royce T2 cascade, featuring strong end-wall shock-induced interference, showed a 77% reduction in the flow pitchwise periodicity error with the optimised tail- board, with respect to the baseline open-jet cascade flow. Two-dimensional Euler predictions were also cross-validated against a three-dimensional Reynolds averaged computation, to explore the three-dimensionality of the discharge
from significant test section boundary interference effects in pitch. A slotted tailboard has been designed and optimised with an in-house Euler numerical method to reduce such ef- fects. Wind tunnel measurements on an overspeed Mach 1.27 discharge from a Rolls-Royce T2 cascade, featuring strong end-wall shock-induced interference, showed a 77% reduction in the flow pitchwise periodicity error with the optimised tail- board, with respect to the baseline open-jet cascade flow. Two-dimensional Euler predictions were also cross-validated against a three-dimensional Reynolds averaged computation, to explore the three-dimensionality of the discharge
| Original language | English |
|---|---|
| Number of pages | 11 |
| DOIs | |
| Publication status | Published - 08 Jan 2004 |
| Event | AIAA 42nd Aerospace Sciences Meeting & Exhibit - Reno, United States Duration: 01 Jan 2004 → 01 Jan 2004 |
Conference
| Conference | AIAA 42nd Aerospace Sciences Meeting & Exhibit |
|---|---|
| Country/Territory | United States |
| City | Reno |
| Period | 01/01/2004 → 01/01/2004 |
Keywords
- CFD
- Transonic wind tunnel
- Turbine cascade