Gas Turbine Engine with Third Stream
AssigneeGeneral Electric Company
InventorsJoseph George ROSE, Thomas Ory MONIZ, Tsuguji NAKANO, Brandon Wayne MILLER, Randy M. VONDRELL, David Marion OSTDIEK, Craig William HIGGINS, Alexander Kimberley SIMPSON
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Abstract
A gas turbine engine includes a turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining a fan duct inlet to a fan duct, and a core inlet to a core duct, a fan driven by the turbomachine, and a booster downstream of the fan, the booster comprising a booster rotor blade and a booster cowl.
Claims20
A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:
- a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the 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 fan driven by the turbomachine;
- and
- a booster located downstream of the fan,
- the gas turbine engine defining a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10,
- wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.
A method of operating a gas turbine engine, the method comprising:
- operating the gas turbine engine at a rated speed, wherein operating the gas turbine engine at the rated speed comprises operating the gas turbine engine to define a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 5, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over a turbomachine of the gas turbine engine plus an airflow through a fan duct to an airflow through a core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct;
- separating a stream of air into an outer stream directed toward the bypass passage and an inner stream directed toward the fan duct;
- boosting the inner stream with a booster rotor blade of a booster;
- and
- separating the inner stream into a fan stream directed into the fan duct and a core stream directed into the core duct.
A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:
- a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining a fan duct inlet to a fan duct, and a core inlet to a core duct;
- a fan driven by the turbomachine;
- and
- a booster downstream of the fan, the booster comprising a booster rotor blade and a booster cowl.
Dependencies are inferred from the claim text.