CPC B64D 27/40 (2024.01) [F02C 7/20 (2013.01); B64D 27/402 (2024.01); B64D 27/404 (2024.01); B64D 27/406 (2024.01); F01D 25/28 (2013.01); F02K 3/06 (2013.01); F05D 2220/323 (2013.01); F05D 2240/90 (2013.01); F05D 2260/20 (2013.01)] | 19 Claims |
1. A gas turbine engine, the gas turbine engine comprising, in axial flow sequence, a fan assembly, a compressor module, a turbine module, and an exhaust module, the gas turbine engine comprising a first engine mount plane and a second engine mount plane, each of the first engine mount plane and second engine mount plane being defined by a respective set of a first side engine mount point, a second side engine mount point, and a centre engine mount point, the first and second engine mount planes being configured to support the gas turbine engine in a machine body, the gas turbine engine having an axial length L, the axial length extending from an inlet face of the engine to an exhaust face of the engine, and
wherein the first engine mount plane is positioned axially along the gas turbine engine at a first engine mount plane position, the first engine mount plane position being within a range of between 0.24*L to 0.32*L from the inlet face of the engine, and the second engine mount plane is positioned axially along the gas turbine engine at a second engine mount plane position, the second engine mount plane position being within a range of between 0.73*L to 0.79*L from the inlet face of the engine.
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