TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES

Organization Name

Inventor(s)

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

This abstract first appeared for US patent application 18430317 titled 'TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES

Simplified Explanation:

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

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

Key Features and Innovation:

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

Potential Applications:

This technology can be used in aircraft engines, power generation systems, and other turbomachinery applications.

Problems Solved:

This technology improves the efficiency and performance of turbomachinery engines by optimizing the design of the fan assembly and low-pressure turbine.

Benefits:

Increased efficiency.
Improved performance.
Enhanced reliability.

Commercial Applications:

Potential commercial applications include aerospace industry, power generation sector, and marine propulsion systems.

Questions about Turbomachinery Engine:

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

Frequently Updated Research:

Ongoing research focuses on further optimizing the design and performance of turbomachinery engines for various applications.

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.