REVERSE FLOW GAS TURBINE ENGINE HAVING ELECTRIC MACHINE

Organization Name

Inventor(s)

Arthur William Sibbach of Boxford MA (US)

REVERSE FLOW GAS TURBINE ENGINE HAVING ELECTRIC MACHINE - A simplified explanation of the abstract

This abstract first appeared for US patent application 18307938 titled 'REVERSE FLOW GAS TURBINE ENGINE HAVING ELECTRIC MACHINE

Simplified Explanation: The patent application describes an aircraft engine assembly that includes a gas turbine engine with an intake channel that redirects incoming air flow to the engine's axial direction. An electric machine located at the aft end of the engine transfers heat to the incoming air flow within the intake channel during operation.

Gas turbine engine with intake channel redirecting incoming air flow
Electric machine at the aft end of the engine transferring heat to incoming air flow
Heat exchange communication between electric machine and intake flow of air

Key Features and Innovation:

Gas turbine engine with innovative intake channel design
Electric machine located at the aft end for heat transfer to incoming air flow
Efficient heat exchange process within the intake channel

Potential Applications: The technology can be applied in aircraft engines, power generation systems, and other industrial applications requiring efficient heat transfer processes.

Problems Solved: The technology addresses the need for improved heat transfer efficiency in aircraft engine assemblies, leading to enhanced performance and reduced fuel consumption.

Benefits:

Improved heat transfer efficiency
Enhanced performance of the gas turbine engine
Reduced fuel consumption

Commercial Applications: Potential commercial applications include aircraft manufacturing, power generation industries, and other sectors requiring advanced heat transfer technologies for improved efficiency.

Questions about the Technology: 1. How does the electric machine transfer heat to the incoming air flow within the intake channel? 2. What are the specific benefits of the heat exchange process in the aircraft engine assembly?

Original Abstract Submitted

An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and thereby form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.