18071743. GAS TURBINE ENGINE simplified abstract (GENERAL ELECTRIC COMPANY)
Contents
- 1 GAS TURBINE ENGINE
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 GAS TURBINE ENGINE - 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 How does the variable bleed assembly impact engine performance?
- 1.11 What materials are used in the construction of the annular cooling passage?
- 1.12 Original Abstract Submitted
GAS TURBINE ENGINE
Organization Name
Inventor(s)
Brandon Wayne Miller of Liberty Township OH (US)
Andrew Hudecki of Milford OH (US)
Eric Barre of Cincinnati OH (US)
GAS TURBINE ENGINE - A simplified explanation of the abstract
This abstract first appeared for US patent application 18071743 titled 'GAS TURBINE ENGINE
Simplified Explanation
The gas turbine engine described in the patent application includes a fan, a turbomachine, a bypass passage, an annular cooling passage, and a variable bleed assembly. The variable bleed assembly helps to regulate airflow through the cooling passage for efficient cooling of the engine components.
- Fan drivingly coupled to a turbomachine
- Bypass passage over the turbomachine
- Annular cooling passage between CP inlet and CP outlet
- Variable bleed assembly with a duct for regulating airflow
- Airflow communication between working gas flowpath, bypass passage, and cooling passage
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 in improving the efficiency and performance of gas turbine engines by providing effective cooling of engine components, thereby enhancing overall engine reliability and longevity.
Benefits
The benefits of this technology include increased engine efficiency, improved cooling capabilities, enhanced engine performance, and extended engine lifespan.
Potential Commercial Applications
The technology could find commercial applications 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 variable bleed systems in gas turbine engines for airflow regulation and cooling purposes.
Unanswered Questions
How does the variable bleed assembly impact engine performance?
The variable bleed assembly helps in regulating airflow through the cooling passage, but the specific impact on engine performance in terms of efficiency and power output is not detailed in the patent application.
What materials are used in the construction of the annular cooling passage?
The patent application does not specify the materials used in the construction of the annular cooling passage for efficient cooling of the engine components.
Original Abstract Submitted
A gas turbine engine is provided. The gas turbine engine includes: a fan; a turbomachine drivingly coupled to the fan and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine, the turbomachine defining an annular cooling passage extending between a CP inlet and a CP outlet, the CP inlet in airflow communication with the working gas flowpath and the CP outlet in airflow communication with the bypass passage; and a variable bleed assembly including a variable bleed duct extending between a VB inlet and a VB outlet, the VB inlet in airflow communication with the working gas flowpath at a location downstream of the CP inlet and the VB outlet in airflow communication with the annular cooling passage for urging an airflow through the cooling passage.
