Browse Topic: Coating processes
Maintaining the operational readiness of military helicopters demands repair solutions that are fast, reliable, and adaptable. This paper presents the integration of Gamma Alloys' advanced metal matrix composites (MMCs) into additive manufacturing (AM) techniques - specifically Cold Spray and Friction Stir Additive Manufacturing (FSAM) - as a transformative approach to helicopter repair and replace for the US Army.
The continual replacement of the bleed band actuator caused a supply shortage resulting in production work stoppage. A re-design effort restored the actuator housing through rework modification of a sleeve repair. The re-design substantion is presented along with the qualification test and manufacturing process. Significant value engineering savings and increased supply readiness resulted from the re-design effort for the U. S. Army. However, the re-designed sleeved actuator housing became costly and inefficient over time and subsequently stopped. The overhaul discrepancy is still present on the newer T55 gas turbine engine model. A review of new repair technology available identified another solution that does not generate hazardous industrial waste. That solution is cold spray technology. Cold spray solid state additive technology is evaluated for re-design of the housing as comparison to the existing sleeve re-design. Cost decrease and manufacturing efficiency increase are both a result from this evaluation. Two cold spray powders presented are options for the re-design housing. While both powders provide a better overall solution to the sleeve re-design, the cold spray hard coat powder appears to provide improved wear resistance, e.g. 20 times better than hexavalent chrome plating.
Researchers have shown how to coat glass and plastic with porous titanium dioxide. The fabrication process is straightforward, the materials are cheap, and the ceramic’s gas sensing performance is considerably improved compared with current devices.
The aluminum alloy Al7075 is commonly used in aircraft industry due to its high mechanical resistance to weight ratio. Nevertheless when the structure is being serviced upon the severe environmental conditions or loads degradation mechanisms could often been found in the material. To improve its behavior the cold spray process with various titanium powders (e.g. CP Ti, Ti-64) deposited onto Al7075 was investigated. The spraying of angular titanium powder was performed in the presence of nitrogen and helium supplied at process parameters (temperature, pressure), which were the maximum values attainable by the CS system used. The deposits were sprayed while maintaining a standoff distance in the range from 20 to 100 mm increased by 10 mm. The experimental data indicated that the deposition efficiency had increased significantly with increasing standoff distance. The coating porosity first decreased to minimum 0.6% and then increased significantly to 9.8%. The mechanical properties of the coatings reached the highest values when the porosity was minimum. No new phases were reported in the cold sprayed titanium coatings when compared with the starting feedstock. The same process parameters were transferred to Ti- 6Al-4V coral like powder deposition process. The shear strength between Ti coating material and Al7075 substrate was measured. Additionally the tensile strength of the deposit only, previously disintegrated from the substrate, was checked out. The data obtained indicate that the consolidation of Ti powder with Al7075 substrate made by cold spray could be served for both: materials integration and building a component by materials disintegration, where Al substrate is removed on spraying and machining; and simply used as a technological support for additive manufacturing of a self-standing real life component.
The Structures Division at the Naval Air Systems Command (NAVAIR) continues to support capital investment in enabling technologies for sustainment of our aircraft which will lower total life cycle costs, ensure safety, and increase operational readiness. This paper presents a general overview of the major improvements which have been made in the area of Structural Health and Usage Management (SHUM), including: usage severity monitoring via regime recognition (RR), gross weight and center of gravity (GW/CG) estimation, local/global damage detection, environmental effects monitoring, damage alleviation, prognostication, and individual asset/component tracking (IAT). Advances in structural analyses have been made in the accuracy of predicted rotorcraft loads using coupled rotor and fuselage interactions. Innovative approaches to fatigue testing at both the component and full scale airframe levels will allow for more accurate introduction of vibratory loading content from operation, reveal failure modes, and improve fatigue life predictions. Additive manufacturing (AM) of fly-away aircraft parts and the standardization of cold spray repair applications present unique qualification challenges and benefits to the warfighter.
The U.S. Army overhauls aircraft weapon system (AH-64, CH-47, UH-60) and associated components. Significant damage, corrosion, and wear are a main cause of component discrepancies. Typical issues with current fusion weld/thermal spray repair is high distortion and a large heat affected zone (HAZ) to an operational aviation component. These repairs often require large and complex fixtures and processes to stabilize the component during the repair process. The additive repair / manufacture (AR/M) has shown to give a very small HAZ and footprint not requiring the use of complex fixtures. This paper outlines the approach taken to develop and qualify AR/M necessary for airworthiness qualification. Two areas that are researched are laser additive manufacturing (LAM) powder fed systems (or directed energy deposition (DED)) and cold spray additive manufacturing. Establishment of mechanical and metallurgical properties of AR/M are presented. Significant return on investment is being shown using these AR/M repair processes.
This paper was prepared to support supersession of MIL-S-8879C with Screw Thread Conformity Task Force selected industry standard AS8879C, published by the Society of Automotive Engineers (SAE). Other documentation changes will be covered by separate papers. Separate papers are anticipated for thread gaging issues, and thread gage calibration procedures. The STC-TF decided that the thread design standard needed to be completed before thread gage definition could be addressed. Thread gage definition has to be known before calibration procedures can be addressed.
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