Titanium Alloy Fastener Composition for Aerospace Applications
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Solution Overview
Problem
Current methods for forming titanium alloy fasteners, such as the solution treating and age process, are time-consuming, resource-intensive, and limit the ability to maintain desired mechanical properties like shear strength and tensile strength, especially in thicker or larger diameter fasteners, while also restricting the use of scrap materials due to oxygen and iron content limitations.
Innovation Solution
A method and apparatus for forming titanium alloy fasteners with increased oxygen and iron content beyond industry maximums, specifically 5.50 to 6.75% aluminum, 3.50 to 4.50% vanadium, 0.25 to 0.50% oxygen, and 0.40 to 0.80% iron, which eliminates the need for solution treatment and aging, allowing for faster production and increased scrap material utilization, and maintains desired mechanical properties through annealing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If solution treating and aging process is used to improve shear strength and tensile strength, then mechanical properties are enhanced, but manufacturing time and resource consumption increase significantly
Solution Approach 1:
The desired mechanical properties are built into the material during the ingot formation stage by controlling the chemical composition (0.20-0.50% oxygen, 0.30-0.80% iron, 5.50-6.75% aluminum, 3.50-4.50% vanadium). This preliminary composition design eliminates the need for subsequent time-consuming solution treating and aging processes, as the material achieves required strength properties directly from the manufacturing process.
Solution Approach 2:
The patent changes the chemical composition parameters of the titanium alloy by increasing oxygen content to 0.20-0.50% and iron content to 0.30-0.80%, which are higher than traditional aerospace specifications. This parameter change fundamentally alters the material's inherent strength properties, allowing it to meet aerospace requirements without additional heat treatment processes.
2Strength
If solution treating and aging process is applied to thicker fastener material, then surface contamination is created, but the ability to maintain desired shear strength and tensile strength decreases
Solution Approach 1:
By modifying the chemical composition parameters (higher oxygen and iron content within controlled ranges), the material achieves uniform strength properties throughout its cross-section. This composition adjustment ensures that even in thicker fastener sections, the desired shear strength and tensile strength are maintained without creating surface contamination issues associated with traditional heat treatment processes.
3Reliability
If traditional titanium alloy composition with limited oxygen and iron is used, then aerospace standards are met, but scrap material utilization is restricted
Solution Approach 1:
The patent expands the acceptable parameter ranges for oxygen (0.20-0.50%) and iron (0.30-0.80%) content in titanium alloy, creating a broader composition window that still meets aerospace strength requirements. This relaxation of compositional constraints allows manufacturers to incorporate higher percentages of scrap materials containing these elements, improving resource utilization while maintaining reliability.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This approach enables the production of titanium alloy fasteners that meet aerospace industry standards for tensile and shear strength without the need for solution treating and aging, reducing manufacturing time and cost, and allowing for the use of higher percentages of scrap material, resulting in stronger and more cost-effective fasteners across varying diameters.
Implementation Method 1
The composition of oxygen and iron within the illustrative embodiments achieves the required ultimate tensile strength and shear strength for aerospace fasteners, without using a solution treat and age process on the fastener
Data Source
AI summary
A method and apparatus for forming a fastener for an aircraft. An annealed titanium alloy is provided with about 5.50 to about 6.75 weight percent aluminum, about 3.50 to about 4.50 weight percent vanadium, more than 0.20 weight percent oxygen, and more than 0.30 weight percent iron. Operations are performed to form the fastener for the aircraft from the annealed titanium alloy.