17970687. VARIABLE PITCH FAN OF A GAS TURBINE ENGINE simplified abstract (GENERAL ELECTRIC COMPANY)
Contents
VARIABLE PITCH FAN OF A GAS TURBINE ENGINE
Organization Name
Inventor(s)
Abhijeet Jayshingrao Yadav of Karad (IN)
Nicholas Joseph Kray of Mason OH (US)
Nicholas M. Daggett of Camden ME (US)
Matthew Mark Weaver of Loveland OH (US)
Srinivas Addagatla of Gebze (TR)
VARIABLE PITCH FAN OF A GAS TURBINE ENGINE - A simplified explanation of the abstract
This abstract first appeared for US patent application 17970687 titled 'VARIABLE PITCH FAN OF A GAS TURBINE ENGINE
The patent application describes a gas turbine engine with a turbomachine consisting of a compressor section, a combustion section, and a turbine section in sequential flow order. A fan with multiple fan blades rotates around a fan axis, and a pitch change mechanism adjusts the pitch of the fan blades. Each fan blade is connected to a counterweight and a spring mechanism that creates a twisting moment counter to the centrifugal twisting moment of the blade.
- The gas turbine engine includes a turbomachine with compressor, combustion, and turbine sections.
- A fan with multiple blades rotates around a fan axis.
- A pitch change mechanism controls the pitch of the fan blades.
- Each fan blade is connected to a counterweight and a spring mechanism.
- The spring mechanism creates a twisting moment counter to the centrifugal twisting moment of the blade.
Potential Applications: - Aerospace industry for aircraft engines - Power generation for gas turbine power plants - Marine propulsion systems
Problems Solved: - Improved control and efficiency of fan blades - Enhanced performance and reliability of gas turbine engines
Benefits: - Increased fuel efficiency - Enhanced engine performance - Reduced maintenance costs
Commercial Applications: Title: "Innovative Gas Turbine Engine Technology for Enhanced Efficiency" This technology can be utilized in commercial aircraft, power generation plants, and marine vessels to improve overall performance and reduce operational costs.
Prior Art: There may be existing patents related to fan blade control mechanisms in gas turbine engines, but this specific combination of counterweights and spring mechanisms may be unique.
Frequently Updated Research: Research on materials and designs for fan blades, counterweights, and spring mechanisms in gas turbine engines is ongoing to further optimize performance and efficiency.
Questions about Gas Turbine Engine Technology: Question 1: How does the pitch change mechanism work in controlling the fan blades? Answer: The pitch change mechanism adjusts the angle of the fan blades to optimize airflow and engine performance. Question 2: What are the potential challenges in implementing this technology in different types of gas turbine engines? Answer: Adapting the counterweight and spring mechanism to various engine designs and sizes may pose challenges in implementation.
Original Abstract Submitted
A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order. A fan defining a fan axis and comprising a plurality of fan blades is rotatable about the fan axis. A pitch change mechanism is operable with the plurality of fan blades to control a pitch of the plurality of fan blades. A counterweight is connected to each respective fan blade. A spring mechanism is operably associated with each fan blade of the plurality of fan blades to create a spring twisting moment on the respective fan blade that is counter to a centrifugal twisting moment of the respective fan blade.
