20240026901. GAS TURBINE ENGINE WITH VARIABLE PITCH INLET PRE-SWIRL FEATURES simplified abstract (General Electric Company)

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GAS TURBINE ENGINE WITH VARIABLE PITCH INLET PRE-SWIRL FEATURES

Organization Name

General Electric Company

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.

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