A gas turbine engine , comprising: a fan including: a first plurality of fan blades supported on a first fan support that is rotatable about a fan axis (A), and a second plurality of fan blades supported on a second fan support that is rotatable about the fan axis (A) independent of the first plurality of fan blades ; a compressor section comprising a first compressor and a second compressor , wherein the first compressor experiences a lower pressure than the second compressor and there is a spacing between the first compressor and the second compressor in a direction parallel to the fan axis (A); a combustor in fluid communication with the compressor section ; and a turbine section in fluid communication with the combustor ; wherein the engine includes a bypass ratio greater than 10:1; characterised in that : the engine includes a geared architecture including at least one gear configured to be driven by the turbine section for rotating about a gear axis (G) that is transverse to the fan axis (A), the at least one gear being configured for driving the first fan support for rotating the first plurality of fan blades in a first direction, the at least one gear being configured for driving the second fan support for rotating the second plurality of fan blades in a second direction that is opposite to the first direction, wherein the geared architecture is at least partially positioned in the spacing. a fan including: a first plurality of fan blades supported on a first fan support that is rotatable about a fan axis (A), and a second plurality of fan blades supported on a second fan support that is rotatable about the fan axis (A) independent of the first plurality of fan blades ; a first plurality of fan blades supported on a first fan support that is rotatable about a fan axis (A), and a second plurality of fan blades supported on a second fan support that is rotatable about the fan axis (A) independent of the first plurality of fan blades ; a compressor section comprising a first compressor and a second compressor , wherein the first compressor experiences a lower pressure than the second compressor and there is a spacing between the first compressor and the second compressor in a direction parallel to the fan axis (A); a combustor in fluid communication with the compressor section ; and a turbine section in fluid communication with the combustor ; wherein the engine includes a bypass ratio greater than 10:1; characterised in that : the engine includes a geared architecture including at least one gear configured to be driven by the turbine section for rotating about a gear axis (G) that is transverse to the fan axis (A), the at least one gear being configured for driving the first fan support for rotating the first plurality of fan blades in a first direction, the at least one gear being configured for driving the second fan support for rotating the second plurality of fan blades in a second direction that is opposite to the first direction, wherein the geared architecture is at least partially positioned in the spacing. the engine includes a geared architecture including at least one gear configured to be driven by the turbine section for rotating about a gear axis (G) that is transverse to the fan axis (A), the at least one gear being configured for driving the first fan support for rotating the first plurality of fan blades in a first direction, the at least one gear being configured for driving the second fan support for rotating the second plurality of fan blades in a second direction that is opposite to the first direction, wherein the geared architecture is at least partially positioned in the spacing. <EOS>