General electric company (20240280057). TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES simplified abstract

TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES

Organization Name

general electric company

Inventor(s)

Pranav R. Kamat of Bengaluru (IN)

Bhaskar Nanda Mondal of Bengaluru (IN)

Jeffrey D. Clements of Evendale OH (US)

TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES - A simplified explanation of the abstract

This abstract first appeared for US patent application 20240280057 titled 'TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES

The patent application describes a turbomachinery engine comprising a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes multiple fan blades, while the low-pressure turbine consists of 3-5 rotating stages. The area ratio of the low-pressure turbine is calculated by dividing the annular exit area of the aft-most rotating stage by the annular exit area of the forward-most rotating stage, falling within a range of 3.1-5.1 in some cases.

• The turbomachinery engine includes a fan assembly with multiple fan blades.
• The low-pressure turbine is composed of 3-5 rotating stages.
• The area ratio of the low-pressure turbine is within a range of 3.1-5.1.

Potential Applications: This technology can be applied in aircraft engines, power generation systems, and marine propulsion systems.

Problems Solved: This innovation improves the efficiency and performance of turbomachinery engines by optimizing the area ratio of the low-pressure turbine.

Benefits: Enhanced fuel efficiency, increased power output, and improved overall performance of turbomachinery engines.

Commercial Applications: This technology can be utilized in the aerospace industry for aircraft engines, in the energy sector for power generation systems, and in the marine industry for propulsion systems.

Questions about the technology: 1. How does the area ratio of the low-pressure turbine impact the performance of the turbomachinery engine? 2. What are the potential drawbacks of optimizing the area ratio within a specific range?

Original Abstract Submitted

a turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. the fan assembly includes a plurality of fan blades. the low-pressure turbine includes 3-5 rotating stages. the low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. in some instances, the area ratio is within a range of 3.1-5.1.