17805986. MULTI-TEMPERATURE FUEL INJECTORS FOR A GAS TURBINE ENGINE simplified abstract (General Electric Company)

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MULTI-TEMPERATURE FUEL INJECTORS FOR A GAS TURBINE ENGINE

Organization Name

General Electric Company

Inventor(s)

Hejie Li of Mason OH (US)

Shai Birmaher of Cincinnati OH (US)

Michael A. Benjamin of Cincinnati OH (US)

MULTI-TEMPERATURE FUEL INJECTORS FOR A GAS TURBINE ENGINE - A simplified explanation of the abstract

This abstract first appeared for US patent application 17805986 titled 'MULTI-TEMPERATURE FUEL INJECTORS FOR A GAS TURBINE ENGINE

Simplified Explanation

The patent application describes a gas turbine engine that includes a combustor, fuel nozzles, and fuel manifolds. The engine has two fuel circuits, each connected to different fuel manifolds and fuel nozzles.

  • The gas turbine engine has a combustor with a combustion chamber.
  • Fuel is injected into the combustion chamber by a plurality of fuel nozzles.
  • The engine has a first fuel circuit and a second fuel circuit.
  • The first fuel circuit distributes fuel to at least one fuel nozzle through a first fuel manifold at a first temperature.
  • The second fuel circuit distributes fuel to at least one fuel nozzle through a second fuel manifold at a second temperature.
  • The second temperature is lower than the first temperature.

Potential applications of this technology:

  • Gas turbine engines used in power generation.
  • Gas turbine engines used in aircraft propulsion.
  • Gas turbine engines used in marine propulsion.

Problems solved by this technology:

  • Allows for more precise control of fuel temperature in different parts of the engine.
  • Helps optimize engine performance and efficiency.
  • Reduces the risk of fuel overheating and potential damage to the engine.

Benefits of this technology:

  • Improved fuel distribution and combustion efficiency.
  • Enhanced engine performance and power output.
  • Increased fuel efficiency and reduced emissions.
  • Better control over fuel temperature, reducing the risk of engine damage.


Original Abstract Submitted

A gas turbine engine including a combustor, a plurality of fuel nozzles, and at least one fuel manifold. The combustor includes a combustion chamber. The plurality of fuel injects fuel into the combustion chamber of the combustor. The gas turbine engine may include a first fuel circuit and a second fuel circuit. The first fuel circuit includes a first fuel manifold fluidly connected to at least one fuel nozzle of the plurality of fuel nozzles to distribute the fuel to the at least one fuel nozzle at a first temperature. The second fuel circuit includes a second fuel manifold fluidly connected to at least one fuel nozzle of the plurality of fuel nozzles to distribute the fuel to the at least one fuel nozzle at a second. The second temperature is less than the first temperature.

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