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 20240280055 titled 'TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES

The patent application describes a turbomachinery engine with 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. 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 calculated based on the annular exit areas of the rotating stages.
The area ratio typically falls within a range of 3.1-5.1.
The gearbox is also part of the turbomachinery engine.

Potential Applications: - Aerospace industry for aircraft engines - Power generation for turbines - Marine propulsion systems

Problems Solved: - Improved efficiency in turbomachinery engines - Enhanced performance in fan assemblies and low-pressure turbines

Benefits: - Increased power output - Reduced fuel consumption - Enhanced reliability and durability

Commercial Applications: Title: "Advanced Turbomachinery Engine for Aerospace and Power Generation" This technology can be utilized in commercial aircraft engines, power generation turbines, and marine propulsion systems. The market implications include improved efficiency, reduced operating costs, and increased competitiveness in the aerospace and power generation sectors.

Questions about Turbomachinery Engine: 1. How does the area ratio of the low-pressure turbine impact the overall performance of the turbomachinery engine? 2. What are the key advantages of using a gearbox in conjunction with the fan assembly and low-pressure turbine in this engine design?

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.