Engine mount system for a gas turbine engine

A gas turbine engine comprising:

• propulsor means for providing propulsion;
• reduction means for reducing a rotational speed of an output that drives the propulsor means relative to an input;
• first compression means for compressing airflow from the propulsor means, wherein the first compression means includes a plurality of stages;
• second compression means for compressing airflow from the first compression means;
• first expansion means for driving the second compression means in response to expanding airflow from the second compression means;
• second expansion means for driving the input of the reduction means in response to expanding airflow from the first expansion means to establish a pressure ratio of greater than 5:1, wherein the pressure ratio is a ratio of a pressure measured prior to an inlet of the second expansion means as related to a pressure at an outlet of the second expansion means prior to any exhaust nozzle, and the second expansion means includes a greater number of stages than the first expansion means but includes a lesser number of stages than the second compression means;
• and
• static support means for supporting a bearing system that rotatably supports the second expansion means and the propulsor means, the support means for supporting a forward engine mount at a first engine mount location axially near the reduction means relative to an engine axis when the engine is mounted, and the support means for supporting an aft engine mount at a second engine mount location axially aft of the first expansion means relative to the engine axis when the engine is mounted.