TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES

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

This abstract first appeared for US patent application 20240280058 titled 'TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES

The patent application pertains to a turbomachinery engine comprising a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly consists of multiple fan blades, while the low-pressure turbine includes 3-5 rotating stages. The area ratio of the low-pressure turbine is determined by the annular exit area of the aft-most rotating stage divided 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 consists of 3-5 rotating stages.
The area ratio of the low-pressure turbine is within a range of 3.1-5.1.
The gearbox is an integral part of the engine system.
The design aims to optimize the performance and efficiency of the engine.

Potential Applications: - Aerospace industry for aircraft propulsion systems - Power generation for gas turbines - Marine propulsion systems for ships and boats

Problems Solved: - Enhances engine efficiency and performance - Improves airflow and power output - Reduces fuel consumption and emissions

Benefits: - Increased engine efficiency - Enhanced power output - Reduced fuel consumption and emissions - Improved overall performance

Commercial Applications: Title: "Advanced Turbomachinery Engine for Enhanced Performance" This technology can be utilized in commercial aircraft, power plants, and marine vessels to improve efficiency and reduce operational costs.

Questions about the technology: 1. How does the area ratio of the low-pressure turbine impact engine performance? 2. What are the potential cost savings associated with implementing this turbomachinery engine design?

Frequently Updated Research: Ongoing research focuses on further optimizing the design of the low-pressure turbine stages to achieve even greater efficiency and performance gains.

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.