US 2017/0284296 A1 · SECONDARY AIRFLOW PASSAGE FOR ADJUSTING AIRFLOW DISTORTION IN GAS TURBINE ENGINE

Abstract

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.

Claims20

Dependent claims

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;
and
a 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.

3 more elements

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;
and
controlling, 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.

Dependencies are inferred from the claim text.

Secondary airflow passage for adjusting airflow distortion in gas turbine engine

Life of this patent

Secondary airflow passage for adjusting airflow distortion in gas turbine engine

Life of this patent

Abstract

Claims20