发明名称 |
GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE |
摘要 |
A gas turbine engine includes a core nacelle defined about an engine axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A gear train is defined along an engine axis. The gear train defines a gear reduction ratio of greater than or equal to about 2.3. A fan drive turbine along the engine axis which drives the gear train. The fan drive turbine includes three to six (3-6) stages. A fan is configured for rotation within the fan nacelle for operation at a fan pressure ratio less than about 1.45. A fan variable area nozzle is axially movable relative to said fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. A high bypass gas turbine engine is also disclosed. |
申请公布号 |
US2015315977(A1) |
申请公布日期 |
2015.11.05 |
申请号 |
US201514755366 |
申请日期 |
2015.06.30 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Suciu Gabriel L.;Merry Brian D.;Dye Christopher M.;Johnson Steven B.;Schwarz Frederick M. |
分类号 |
F02C9/20;F01D25/24;F02K3/06;F02C7/36;F02C9/18 |
主分类号 |
F02C9/20 |
代理机构 |
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代理人 |
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主权项 |
1. A gas turbine engine comprising:
a core nacelle defined about an engine axis; a fan nacelle mounted at least partially around said core nacelle to define a fan bypass airflow path for a fan bypass airflow; a gear train defined along an engine axis, said gear train defines a gear reduction ratio of greater than or equal to about 2.3; a fan drive turbine along said engine axis which drives said gear train, said fan drive turbine including three to six (3-6) stages; and a fan configured for rotation within the fan nacelle for operation at a fan pressure ratio less than about 1.45, a fan variable area nozzle axially movable relative to said fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. |
地址 |
Hartford CT US |