Translating inlet for adjusting airflow distortion in gas turbine engine

A method for adjusting airflow distortion in a gas turbine engine on an aircraft, the gas turbine engine comprising a compressor section, a combustion section, and a turbine section in series flow, the compressor section, combustion section, and turbine section defining at least in part an engine airflow path, the gas turbine engine further comprising an inner flow path surface positioned at least partially within the compressor section and defining at least in part the engine airflow path, the gas turbine engine further comprising a core casing at least partially enclosing the compressor section and defining a forward end, the method comprising:

• determining, by one or more control devices, an airflow distortion condition associated with the engine airflow path, the airflow distortion condition determined at least in part from one or more measurements obtained by an instrumented guide vane;
• and
• controlling, by the one or more control devices, a moving inlet assembly to adjust the airflow distortion condition of the gas turbine engine having been determined at least in part from the one or more measurements obtained by the instrumented guide vane, wherein the core casing comprises the moving inlet assembly at the forward end, the moving inlet assembly and inner flow path surface together defining an inlet to the compressor section, the moving inlet assembly moveable between a first position defining a first inlet area and a second position defining a second inlet area, the first inlet area being greater than the second inlet area,
• wherein the core engine defines a centerline axis,
• wherein the moving inlet assembly is movable between the first position and the second position in a substantially uniform manner about the centerline axis of the core engine,
• wherein the moving inlet assembly defines a leading edge of the core casing,
• wherein the leading edge defines a first circumference in the first position,
• wherein the leading edge defines a second circumference in the second position, and
• wherein the second circumference is less than the first circumference.

A gas turbine engine system for an aircraft comprising:

• a compressor section, a combustion section, and a turbine section defining at least in part an engine airflow path for a core engine;
• an inner flowpath surface positioned at least partially within the compressor section and defining at least in part the engine airflow path;
• a core casing at least partially enclosing the compressor section and defining a forward end, the core casing comprising a moving inlet assembly at the forward end, the moving inlet assembly and inner flowpath surface together defining an inlet to the compressor section, the moving inlet assembly moveable between a first position defining a first inlet area at the inlet and a second position defining a second inlet area at the inlet, the first inlet area being greater than the second inlet area, wherein the core engine defines a centerline axis, wherein the moving inlet assembly is movable between the first position and the second position in a substantially uniform manner about the centerline axis of the core engine;
• and
• a controller operably connected to the moving inlet assembly, the controller comprising one or more processors and one or more memory devices located on the aircraft, the one or more memory devices storing instructions that when executed by the one or more processors cause the one or more processors to perform operations, the operations comprising:
• determine an airflow distortion condition within the engine airflow path;
• and
• control the moving inlet assembly to adjust an airflow through the engine airflow path to adjust the airflow distortion condition,
• wherein the moving inlet assembly defines a leading edge of the core casing,
• wherein the leading edge defines a first circumference in the first position,
• wherein the leading edge defines a second circumference in the second position, and
• wherein the second circumference is less than the first circumference.