20240044304. GAS TURBINE ENGINE WITH THIRD STREAM simplified abstract (General Electric Company)

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GAS TURBINE ENGINE WITH THIRD STREAM

Organization Name

General Electric Company

Inventor(s)

Brandon Wayne Miller of Liberty Township OH (US)

Randy M. Vondrell of Cincinnati OH (US)

David Marion Ostdiek of Liberty Township OH (US)

Craig William Higgins of Liberty Township OH (US)

Alexander Kimberley Simpson of Cincinnati OH (US)

GAS TURBINE ENGINE WITH THIRD STREAM - A simplified explanation of the abstract

This abstract first appeared for US patent application 20240044304 titled 'GAS TURBINE ENGINE WITH THIRD STREAM

Simplified Explanation

The abstract describes a gas turbine engine that includes a turbomachine, an inlet duct, a fan duct inlet, and a core inlet. It also includes a primary fan driven by the turbomachine and a secondary fan located downstream of the primary fan within the inlet duct. The engine has a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10.

  • The gas turbine engine has a primary fan and a secondary fan, which are both located within the inlet duct.
  • The engine has a specific thrust to power airflow ratio and core bypass ratio, which determine the efficiency and performance of the engine.
  • The thrust to power airflow ratio is the ratio of the airflow through the bypass passage and the fan duct to the airflow through the core duct.
  • The core bypass ratio is the ratio of the airflow through the fan duct to the airflow through the core duct.

Potential applications of this technology:

  • Gas turbine engines are commonly used in aircraft propulsion systems, so this innovation could be applied to improve the efficiency and performance of aircraft engines.
  • The ability to control the thrust to power airflow ratio and core bypass ratio can lead to more efficient and environmentally friendly gas turbine engines.

Problems solved by this technology:

  • Gas turbine engines are known for their high fuel consumption and emissions. This technology aims to address these issues by optimizing the airflow ratios and improving overall engine efficiency.
  • The secondary fan located downstream of the primary fan helps in achieving better airflow management and control, leading to improved engine performance.

Benefits of this technology:

  • Improved fuel efficiency: By optimizing the airflow ratios, the gas turbine engine can achieve better fuel efficiency, reducing fuel consumption and operating costs.
  • Reduced emissions: The improved efficiency of the engine can also result in reduced emissions, contributing to a cleaner and more sustainable environment.
  • Enhanced performance: The ability to control the thrust to power airflow ratio and core bypass ratio allows for better engine performance, resulting in increased power output and improved overall aircraft performance.


Original Abstract Submitted

a gas turbine engine is provided. the gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. the gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.

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