18615448. VARIABLE PITCH FANS FOR TURBOMACHINERY ENGINES simplified abstract (GENERAL ELECTRIC COMPANY)
Contents
VARIABLE PITCH FANS FOR TURBOMACHINERY ENGINES
Organization Name
Inventor(s)
Daniel A. Niergarth of Norwood OH (US)
Martin Manning of Cincinnati OH (US)
Nicholas M. Daggett of Camden ME (US)
Christopher J. Kroger of West Chester OH (US)
Ian F. Prentice of Cincinnati OH (US)
VARIABLE PITCH FANS FOR TURBOMACHINERY ENGINES - A simplified explanation of the abstract
This abstract first appeared for US patent application 18615448 titled 'VARIABLE PITCH FANS FOR TURBOMACHINERY ENGINES
The abstract describes a turbomachinery engine with a fan assembly containing variable pitch fan blades that define specific parameters related to the hub-to-tip radius ratio, fan pressure ratio, bearing spanwise force, and fan area.
- The first VPF parameter is the hub-to-tip radius ratio divided by the fan pressure ratio, falling within a range of 0.10 to 0.40.
- The second VPF parameter is the bearing spanwise force divided by the fan area, within a range of 1-30 lbf/in.
Potential Applications: - Aerospace industry for aircraft engines - Power generation for gas turbines - Marine propulsion systems
Problems Solved: - Improved efficiency and performance of turbomachinery engines - Enhanced control over fan blade pitch for optimal operation
Benefits: - Increased fuel efficiency - Reduced emissions - Enhanced reliability and durability
Commercial Applications: Title: "Advanced Turbomachinery Engine Technology for Enhanced Performance" This technology can be utilized in commercial aircraft, power plants, and marine vessels to improve efficiency and reduce environmental impact.
Questions about the technology: 1. How does the variable pitch fan blade design contribute to the overall performance of the turbomachinery engine? 2. What are the key factors influencing the selection of the first and second VPF parameters in the design of the fan assembly?
Original Abstract Submitted
A turbomachinery engine can include a fan assembly with a plurality of variable pitch fan blades. The fan blades are configured such that they define a first VPF parameter and a second VPF parameter. The first VPF parameter is within a range of 0.10 to 0.40 and is defined as the hub-to-tip radius ratio divided by the fan pressure ratio. The second VPF parameter is within a range of 1-30 lbf/inand is defined as the bearing spanwise force divided by the fan area. In certain examples, the turbomachinery engine further includes a pitch change mechanism, a vane assembly, a core engine, and a gearbox.
