18152903. AIRCRAFT PROPULSION SYSTEM simplified abstract (GENERAL ELECTRIC COMPANY)

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AIRCRAFT PROPULSION SYSTEM

Organization Name

GENERAL ELECTRIC COMPANY

Inventor(s)

Jeffrey D. Rambo of Mason OH (US)

Brandon W. Miller of Middletown OH (US)

Scott G. Edens of Milford OH (US)

AIRCRAFT PROPULSION SYSTEM - A simplified explanation of the abstract

This abstract first appeared for US patent application 18152903 titled 'AIRCRAFT PROPULSION SYSTEM

The propulsion system described in the patent application consists of a turbine engine with a compressor section, a combustor, and a turbine section, a ramjet engine, and an inlet section that supplies airflow to both the turbine engine and the ramjet engine.

  • The turbine engine inlet portion includes an expansion turbine located upstream of the compressor section.
  • The system is designed to efficiently provide airflow to both the turbine engine and the ramjet engine, optimizing the overall propulsion process.

Potential Applications:

  • This propulsion system could be used in aircraft, missiles, or other vehicles requiring high-speed propulsion.
  • It may also find applications in military or aerospace industries for advanced propulsion systems.

Problems Solved:

  • The system addresses the need for a combined propulsion system that can efficiently utilize both turbine and ramjet engines.
  • It solves the challenge of providing adequate airflow to both engines for optimal performance.

Benefits:

  • Improved propulsion efficiency and performance.
  • Enhanced speed and maneuverability for vehicles equipped with this system.

Commercial Applications:

  • This technology could revolutionize the aerospace industry by providing a more efficient and powerful propulsion system for various applications.

Questions about the technology: 1. How does the combination of a turbine engine and a ramjet engine improve propulsion efficiency? 2. What are the potential challenges in integrating these two types of engines into a single propulsion system?


Original Abstract Submitted

A propulsion system includes (a) a turbine engine including a compressor section, a combustor, and a turbine section, (b) a ramjet engine, and (c) an inlet section including a turbine engine inlet portion and a ramjet inlet portion, the inlet section providing an inlet airflow to the turbine engine and to the ramjet engine. The turbine engine inlet portion includes an expansion turbine arranged upstream of the compressor section.

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