POWER TRANSFER SYSTEMS AND METHODS FOR AIRCRAFT ENGINES

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POWER TRANSFER SYSTEMS AND METHODS FOR AIRCRAFT ENGINES - A simplified explanation of the abstract

This abstract first appeared for US patent application 18406967 titled 'POWER TRANSFER SYSTEMS AND METHODS FOR AIRCRAFT ENGINES

Simplified Explanation: The patent application describes an aircraft engine with a unique power transfer system that efficiently transfers power between the low-pressure and high-pressure sections of the engine.

Key Features and Innovation:

Aircraft engine with a fan and gas turbine engine
Power transfer system with a differential and gearbox
Efficient transfer of power between low-pressure and high-pressure sections

Potential Applications: This technology can be applied in various aircraft engines to improve power transfer efficiency and overall performance.

Problems Solved: This technology addresses the challenge of effectively transferring power between different sections of an aircraft engine.

Benefits:

Improved power transfer efficiency
Enhanced overall performance of the aircraft engine

Commercial Applications: Potential commercial applications include the aviation industry for the development of more efficient and high-performance aircraft engines.

Prior Art: Readers can start their search for prior art related to this technology by exploring patents and research papers in the field of aircraft engine design and power transfer systems.

Frequently Updated Research: Stay updated on the latest research in aircraft engine design and power transfer systems to discover advancements and innovations in the field.

Questions about Aircraft Engine Power Transfer System: 1. How does the power transfer system in this aircraft engine differ from traditional systems? 2. What are the potential implications of this technology for the aviation industry?

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Original Abstract Submitted

An example aircraft engine includes a fan and a gas turbine engine to drive the fan. The gas turbine engine has a low-pressure drive shaft operatively coupling a low-pressure turbine and a low-pressure compressor and a high-pressure drive shaft operatively coupling a high-pressure turbine and a high-pressure compressor. The aircraft engine includes a power transfer system including a differential having an input shaft, a first output shaft in gear with the low-pressure drive shaft, and a second output shaft in gear with the high-pressure drive shaft, and a gearbox between the low-pressure drive shaft of the gas turbine engine and the first output shaft of the differential. The gearbox is configured to provide power transfer through the differential from the low-pressure drive shaft to the high-pressure drive shaft.