18524874. GAS TURBINE ENGINES WITH HEAT RECOVERY SYSTEMS simplified abstract (GENERAL ELECTRIC COMPANY)
Contents
- 1 GAS TURBINE ENGINES WITH HEAT RECOVERY SYSTEMS
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 GAS TURBINE ENGINES WITH HEAT RECOVERY SYSTEMS - A simplified explanation of the abstract
- 1.4 Simplified Explanation
- 1.5 Potential Applications
- 1.6 Problems Solved
- 1.7 Benefits
- 1.8 Potential Commercial Applications
- 1.9 Possible Prior Art
- 1.10 Original Abstract Submitted
GAS TURBINE ENGINES WITH HEAT RECOVERY SYSTEMS
Organization Name
Inventor(s)
Paul Hadley Vitt of Evendale OH (US)
Michael Simonetti of West Chester OH (US)
Ashish Sharma of Garching (DE)
GAS TURBINE ENGINES WITH HEAT RECOVERY SYSTEMS - A simplified explanation of the abstract
This abstract first appeared for US patent application 18524874 titled 'GAS TURBINE ENGINES WITH HEAT RECOVERY SYSTEMS
Simplified Explanation
The gas turbine engine described in the patent application includes a fan, compressor section, turbine section, core airflow path, rotary member, and outlet guide vane assembly. The outlet guide vane assembly consists of multiple outlet guide vanes with cold and heated fluid passageways.
- The gas turbine engine includes a fan, compressor section, turbine section, core airflow path, rotary member, and outlet guide vane assembly.
- The outlet guide vane assembly comprises multiple outlet guide vanes with cold and heated fluid passageways.
Potential Applications
The technology described in the patent application could be applied in aircraft engines, power generation systems, and industrial gas turbines.
Problems Solved
This technology helps improve the efficiency and performance of gas turbine engines by optimizing the airflow path and temperature control within the engine.
Benefits
The benefits of this technology include increased efficiency, reduced emissions, and improved overall performance of gas turbine engines.
Potential Commercial Applications
The technology could be commercialized in the aerospace industry, power generation sector, and other industries utilizing gas turbine engines.
Possible Prior Art
One possible prior art could be the use of outlet guide vanes in gas turbine engines to control airflow and temperature, but the specific design and features described in this patent application may be novel.
Unanswered Questions
How does this technology compare to existing outlet guide vane assemblies in gas turbine engines?
This article does not provide a direct comparison with existing outlet guide vane assemblies in gas turbine engines. Further research or a comparative analysis would be needed to answer this question.
What are the potential challenges in implementing this technology in existing gas turbine engines?
The article does not address the potential challenges in implementing this technology in existing gas turbine engines. Factors such as retrofitting, cost, and compatibility with current engine designs could be potential challenges that need to be explored further.
Original Abstract Submitted
A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway and another of the multiple guide vanes includes a heated fluid passageway.
