TY - GEN
T1 - 3D numerical simulation of clamshell thrust reverser with flap deployed while landing
AU - Liu, Chunyang
AU - Wang, Zhanxue
AU - Wang, Jiaqi
AU - Yin, Fang
AU - Kong, Deying
PY - 2010
Y1 - 2010
N2 - The flow field distribution characteristic of a clamshell thrust reverser with flap deployed while landing is investigated based on Computational Fluid Dynamics (CFD) technology. The mesh was generated with unstructured tetrahedron and unstructured hexahedron meshes and S-A turbulent model in solving Reynolds averaged N-S equations is adopted. The results show, in the range of landing speed between 136.1m/s and 17.0m/s, the hot reverse exhaust flow from the clamshell thrust reverser is not re-injected into the engine inlet; and it impinges on part of the aerofoil and pylon. As landing speed decreases, the hot reverse exhaust flow spreads forward and laterally deeper, so it may be re-injected by near engine inlet if the aerofoil sweepback is large enough, which will result in inlet distortion. When landing speed decreases down to 34m/s, the hot reverse exhaust flow starts to impinge on the ground, which may wind up some dross to the inlet. At last, the reverse thrust decreases as landing speed decreases.
AB - The flow field distribution characteristic of a clamshell thrust reverser with flap deployed while landing is investigated based on Computational Fluid Dynamics (CFD) technology. The mesh was generated with unstructured tetrahedron and unstructured hexahedron meshes and S-A turbulent model in solving Reynolds averaged N-S equations is adopted. The results show, in the range of landing speed between 136.1m/s and 17.0m/s, the hot reverse exhaust flow from the clamshell thrust reverser is not re-injected into the engine inlet; and it impinges on part of the aerofoil and pylon. As landing speed decreases, the hot reverse exhaust flow spreads forward and laterally deeper, so it may be re-injected by near engine inlet if the aerofoil sweepback is large enough, which will result in inlet distortion. When landing speed decreases down to 34m/s, the hot reverse exhaust flow starts to impinge on the ground, which may wind up some dross to the inlet. At last, the reverse thrust decreases as landing speed decreases.
KW - Clamshell thrust reverser
KW - Flap
KW - Hot reverse exhaust flow
KW - Inlet distortion
KW - Reverse thrust
UR - https://www.scopus.com/pages/publications/79952167561
U2 - 10.1109/ISSCAA.2010.5632562
DO - 10.1109/ISSCAA.2010.5632562
M3 - 会议稿件
AN - SCOPUS:79952167561
SN - 9781424460441
T3 - ISSCAA2010 - 3rd International Symposium on Systems and Control in Aeronautics and Astronautics
SP - 153
EP - 157
BT - ISSCAA2010 - 3rd International Symposium on Systems and Control in Aeronautics and Astronautics
T2 - 3rd International Symposium on Systems and Control in Aeronautics and Astronautics, ISSCAA2010
Y2 - 8 June 2010 through 10 June 2010
ER -