General electric company (20240318661). TURBOMACHINE AND METHOD OF ASSEMBLY simplified abstract
Contents
TURBOMACHINE AND METHOD OF ASSEMBLY
Organization Name
Inventor(s)
Jixian Yao of Niskayuna NY (US)
Trevor Howard Wood of Clifton Park NY (US)
Kishore Ramakrishnan of Rexford NY (US)
William Joseph Solomon of Montgomery OH (US)
Giridhar Jothiprasad of Clifton Park NY (US)
Aaron J. King of West Harrison OH (US)
TURBOMACHINE AND METHOD OF ASSEMBLY - A simplified explanation of the abstract
This abstract first appeared for US patent application 20240318661 titled 'TURBOMACHINE AND METHOD OF ASSEMBLY
The abstract describes a gas turbine engine with an annular casing, a fan, a core turbine engine, and a variable bleed assembly.
- The gas turbine engine includes an annular casing.
- A fan is mounted inside the annular casing and rotates about an axial centerline.
- The core turbine engine is drivingly coupled to the fan and consists of a compressor section, a combustion section, and a turbine section.
- A variable bleed assembly includes a duct extending between a VB inlet and a VB outlet.
- The fan blades extend radially outward towards the annular casing.
- The fan's performance is determined by factors such as average chord fan width and the quantity of fan blades.
Potential Applications: - Aerospace industry for aircraft propulsion systems. - Power generation for electricity production. - Marine propulsion for ships and boats.
Problems Solved: - Improved efficiency in gas turbine engines. - Enhanced control over airflow and pressure within the engine.
Benefits: - Increased fuel efficiency. - Enhanced performance and reliability. - Reduced emissions and environmental impact.
Commercial Applications: Gas turbine engines can be used in commercial aircraft, power plants, and marine vessels for propulsion and power generation purposes.
Questions about Gas Turbine Engine: 1. How does the variable bleed assembly impact the performance of the gas turbine engine? 2. What are the key advantages of using a fan with variable blade configurations in a gas turbine engine?
Original Abstract Submitted
a gas turbine engine includes an annular casing, a fan disposed inside the annular casing and mounted for rotation about an axial centerline, a core turbine engine drivingly coupled to the fan and comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, and a variable bleed assembly comprising a variable bleed duct extending between a vb inlet and a vb outlet. the fan includes fan blades that extend radially outwardly toward the annular casing. the fan has an average chord fan width according to a first performance factor. the fan has a quantity of fan blades according to a second performance factor.
