18088990. COMPOSITE AIRFOIL ASSEMBLY HAVING A DOVETAIL PORTION simplified abstract (GENERAL ELECTRIC COMPANY)
Contents
COMPOSITE AIRFOIL ASSEMBLY HAVING A DOVETAIL PORTION
Organization Name
Inventor(s)
Nicholas Joseph Kray of Mason OH (US)
Michael John Franks of Cincinnati OH (US)
COMPOSITE AIRFOIL ASSEMBLY HAVING A DOVETAIL PORTION - A simplified explanation of the abstract
This abstract first appeared for US patent application 18088990 titled 'COMPOSITE AIRFOIL ASSEMBLY HAVING A DOVETAIL PORTION
The abstract describes a composite blade assembly for a turbine engine, consisting of a core and a laminate skin with composite structure and plies forming different angles relative to a horizontal plane.
- Simplified Explanation:
- Composite blade assembly for a turbine engine with core and laminate skin. - Core has composite structure, laminate skin has composite plies at different angles.
- Key Features and Innovation:
- Core and laminate skin made of composite materials. - Laminate skin with plies at varying angles for strength and aerodynamics.
- Potential Applications:
- Aerospace industry for turbine engines. - Wind turbine blades. - Marine propulsion systems.
- Problems Solved:
- Enhances strength and durability of turbine blades. - Improves aerodynamic performance. - Reduces weight compared to traditional metal blades.
- Benefits:
- Increased efficiency and performance. - Longer lifespan. - Reduced maintenance costs.
- Commercial Applications:
- Used in aircraft engines for improved efficiency. - Wind turbines for increased energy production. - Marine propulsion systems for enhanced performance.
- Questions about Composite Blade Assembly:
1. How does the composite structure of the core contribute to the overall strength of the blade assembly? 2. What are the advantages of having laminate skin with plies at different angles for aerodynamics and performance?
- Frequently Updated Research:
- Ongoing studies on optimizing composite materials for turbine applications. - Research on advanced manufacturing techniques for composite blade assemblies.
Original Abstract Submitted
A composite blade assembly for a turbine engine, the composite blade assembly having a core and a laminate skin. The core having a composite structure. The laminate skin having at least one composite ply. The laminate skin having a first portion forming a first angle relative to a horizontal plane, and a second portion forming a second angle relative to the horizontal plane.
