General electric company (20240280056). TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES simplified abstract
TURBOMACHINERY ENGINES WITH HIGH-SPEED LOW-PRESSURE TURBINES
Organization Name
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 20240280056 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 consists of multiple fan blades.
- The low-pressure turbine has 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.
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 turbines
Benefits: - Increased power output - Reduced fuel consumption - Enhanced durability and reliability
Commercial Applications: Title: "Advanced Turbomachinery Engine for Aerospace and Power Generation" This technology can be utilized in commercial aircraft, power plants, and marine vessels for improved performance and efficiency.
Questions about the technology: 1. How does the area ratio of the low-pressure turbine impact engine performance? 2. What are the key advantages of using a gearbox in a turbomachinery engine design?
Frequently Updated Research: Ongoing research focuses on optimizing the area ratio of low-pressure turbines for further efficiency gains in turbomachinery engines.
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.