TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES

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Inventor(s)

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

This abstract first appeared for US patent application 18430283 titled 'TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES

Simplified Explanation:

This patent application pertains to a turbomachinery engine that consists of a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes multiple fan blades, while the low-pressure turbine comprises 3-5 rotating stages with a specific area ratio.

The fan assembly features a plurality of fan blades.
The low-pressure turbine is composed 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.
The area ratio falls within a range of 3.1-5.1 in some cases.

Key Features and Innovation:

Fan assembly with multiple fan blades.
Low-pressure turbine with 3-5 rotating stages.
Specific area ratio calculation for the low-pressure turbine.

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 design of the low-pressure turbine.

Benefits:

Enhanced engine efficiency.
Improved power generation capabilities.
Increased fuel efficiency in aircraft engines.

Commercial Applications:

The technology can be utilized in the aerospace industry, power generation sector, and marine transportation for improved performance and efficiency.

Questions about Turbomachinery Engine:

1. How does the specific area ratio of the low-pressure turbine impact engine performance? 2. What are the potential challenges in implementing this technology in existing engine designs?

Frequently Updated Research:

Ongoing research focuses on further optimizing the design of turbomachinery engines for increased efficiency and performance.

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.