초록
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Systems and methods for adjusting airflow distortion in a gas turbine engine using a secondary airflow passage assembly are disclosed. A gas turbine engine can include a compressor section, a combustion section, and a turbine section in series flow and defining at least in part an engine airflow path. A casing can enclose the gas turbine engine and be at least partially exposed to a bypass airflow. The gas turbine engine can further include a secondary airflow passage assembly comprising a door and a duct, the duct defining an inlet located on the casing...
Systems and methods for adjusting airflow distortion in a gas turbine engine using a secondary airflow passage assembly are disclosed. A gas turbine engine can include a compressor section, a combustion section, and a turbine section in series flow and defining at least in part an engine airflow path. A casing can enclose the gas turbine engine and be at least partially exposed to a bypass airflow. The gas turbine engine can further include a secondary airflow passage assembly comprising a door and a duct, the duct defining an inlet located on the casing, the duct defining an outlet in airflow communication with the engine airflow path, the duct comprising an airflow passage extending between the inlet and outlet. The door can be moveable between an open and closed position to allow a portion of the bypass airflow to flow through the airflow passage to adjust airflow distortion.
대표
청구항
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1. A core engine of a 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 for the gas turbine engine;a casing at least partially enclosing the compressor section, combustion section, and turbine section of the core engine, the casing at least partially exposed to a bypass airflow; anda secondary airflow passage assembly, comprising a duct, the duct defining an inlet located on the c...
1. A core engine of a 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 for the gas turbine engine;a casing at least partially enclosing the compressor section, combustion section, and turbine section of the core engine, the casing at least partially exposed to a bypass airflow; anda secondary airflow passage assembly, comprising a duct, the duct defining an inlet located on the casing, the duct defining an outlet in airflow communication with the engine airflow path, the duct defining an airflow passage extending between the inlet and outlet, and;a door moveable between an open position and a closed position, the door allowing at least a portion of the bypass airflow to flow through the airflow passage when in the open position, the door restricting substantially all airflow through the airflow passage when in the closed position. 2. The core engine of claim 1, wherein the door is configured to be controlled based at least in part on an airflow distortion in the engine airflow path. 3. The core engine of claim 2, further comprising: one or more pressure sensor devices located at least partially in the engine airflow path for obtaining one or more measurements associated with airflow distortion. 4. The core engine of claim 1, wherein the core engine comprises a plurality of secondary airflow passage assemblies. 5. The core engine of claim 4, wherein the core engine comprises a plurality of pressure sensor devices, wherein each secondary airflow passage assembly is associated with a pressure sensor device configured to obtain one or more measurements associated with the secondary airflow passage assembly. 6. The core engine of claim 4, wherein the core engine defines a circumferential direction, wherein the plurality of secondary airflow passage assemblies is spaced about the circumferential direction of the core engine. 7. The core engine of claim 1, wherein the core engine defines an axial direction, wherein the door is movable at least partially along the axial direction between the open and closed positions. 8. The core engine of claim 1, wherein the door extends at least partially into the bypass airflow in the open position to direct a portion of the bypass airflow into the airflow passage. 9. The core engine of claim 1, wherein the door is additionally movable to an intermediate position between the open and closed positions, wherein the portion of airflow in the intermediate position is less than the portion of airflow in the open position and more than the portion of airflow in the closed position. 10. The core engine of claim 9, wherein the door is movable between the open, closed, and intermediate positions based on signals from a controller to adjust an airflow distortion in the engine airflow path. 11. The core engine of claim 9, wherein the secondary airflow passage assembly comprises one or more actuators operable for moving the door between the open, closed, and intermediate positions. 12. 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 compressor section, combustion section, and turbine section at least partially enclosed in a casing, the casing at least partially exposed to a bypass airflow, the method comprising: determining, by one or more control devices, an airflow distortion condition associated with the engine airflow path; andcontrolling, by the one or more control devices, a door of a secondary airflow passage to adjust the airflow distortion condition of the gas turbine engine, the secondary airflow passage assembly comprising a duct, the duct defining an inlet located on the casing, the duct defining an outlet in airflow communication with the engine airflow path, the duct defining an airflow passage extending between the inlet and outlet, the door allowing at least a portion of the bypass airflow to flow through the airflow passage when in the open position, the door restricting substantially all airflow through the airflow passage when in the closed position. 13. The method of claim 12, wherein the door is additionally movable to an intermediate position between the open and closed position, wherein the portion of airflow in the intermediate position is less than the portion of airflow in the open position and more than the portion of airflow in the closed position. 14. The method of claim 13, wherein controlling the door of the secondary airflow passage assembly comprises moving the door between the open, closed, and intermediate positions. 15. The method of claim 12, wherein controlling the door of a secondary airflow passage assembly to adjust the airflow distortion condition comprises controlling the door of a secondary airflow passage assembly to reduce the airflow distortion condition. 16. The method of claim 12, wherein determining the airflow distortion condition associated with the engine airflow path comprises obtaining one or more measurements using one or more pressure sensor devices. 17. The method of claim 12, wherein controlling the door comprises sending a control signal to one or more actuators operable for moving the door. 18. A gas turbine engine system for an aircraft comprising: a compressor section, a combustion section, and a turbine section in series flow and defining at least in part an engine airflow path,a casing at least partially enclosing the compressor section, combustion section, and turbine section, the casing at least partially exposed to a bypass airflow;a secondary airflow passage assembly, comprising a duct and a door, the duct defining an inlet located on the casing, the duct defining an outlet in airflow communication with the engine airflow path, the duct defining an airflow passage extending between the inlet and outlet, the door moveable between an open position and a closed position, the door allowing at least a portion of the bypass airflow to flow through the airflow passage when in the open position, the door restricting substantially all airflow through the airflow passage when in the closed position; anda controller operably connected to the door of the secondary airflow passage assembly, the controller comprising one or more processors and one or more memory devices located on an 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; andcontrol the door to adjust an airflow through the airflow passage to adjust the determined airflow distortion condition. 19. The gas turbine engine system of claim 18, wherein the core engine comprises one or more pressure sensor devices located at least partially in the engine airflow path for obtaining one or more measurements for determining the airflow distortion condition. 20. The gas turbine engine system of claim 17, wherein the door is additionally movable to an intermediate position between the open and closed position, wherein the portion of airflow in the intermediate position is less than the portion of airflow in the open position and more than the portion of airflow in the closed position.
