20240026901. GAS TURBINE ENGINE WITH VARIABLE PITCH INLET PRE-SWIRL FEATURES simplified abstract (General Electric Company)
Contents
GAS TURBINE ENGINE WITH VARIABLE PITCH INLET PRE-SWIRL FEATURES
Organization Name
Inventor(s)
Brandon Wayne Miller of Liberty Township OH (US)
Arthur William Sibbach of Boxford MA (US)
GAS TURBINE ENGINE WITH VARIABLE PITCH INLET PRE-SWIRL FEATURES - A simplified explanation of the abstract
This abstract first appeared for US patent application 20240026901 titled 'GAS TURBINE ENGINE WITH VARIABLE PITCH INLET PRE-SWIRL FEATURES
Simplified Explanation
The abstract describes a gas turbine engine that includes a fan with multiple fan blades, a turbomachine connected to the fan to drive it, and a nacelle that surrounds and partially encloses the fan. The engine also has an inlet pre-swirl feature located upstream of the fan blades, which can be adjusted to different angles with respect to the longitudinal axis of the nacelle.
- The gas turbine engine includes a fan with multiple blades.
- A turbomachine is connected to the fan to drive it.
- The engine has a nacelle that surrounds and partially encloses the fan.
- An inlet pre-swirl feature is located upstream of the fan blades.
- The inlet pre-swirl feature can be adjusted to different angles with respect to the longitudinal axis of the nacelle.
Potential applications of this technology:
- Gas turbine engines used in aircraft propulsion systems.
- Gas turbine engines used in power generation systems.
- Gas turbine engines used in marine propulsion systems.
Problems solved by this technology:
- Improved efficiency of the gas turbine engine.
- Enhanced control over the airflow entering the engine.
- Reduction of noise generated by the engine.
Benefits of this technology:
- Increased fuel efficiency and reduced emissions.
- Improved performance and power output of the engine.
- Enhanced control and stability of the engine operation.
- Reduced noise levels during engine operation.
Original Abstract Submitted
a gas turbine engine includes a fan having a plurality of fan blades, a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath, a nacelle surrounding and at least partially enclosing the fan, the nacelle defining a longitudinal axis, and an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle, wherein the inlet pre-swirl feature is transitionable between a first angle with respect to the longitudinal axis of the nacelle and a second angle with respect to the longitudinal axis of the nacelle.