GAS TURBINE ENGINE

Abstract: a gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; a nacelle surrounding the primary fan; and a secondary fan located downstream of the primary fan within the inlet duct. the gas turbine engine is characterized by a thrust to power airflow ratio, a core bypass ratio, a blade effective acoustic length, an acoustic spacing length, and an inlet-to-nacelle ratio.

Inventor(s): Brandon W. Miller, Randy M. Vondrell, David M. Ostdiek, Craig W. Higgins, Alexander Simpson, Arthur W. Sibbach

CPC Classification: F02K3/065 (JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants , ))

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