Al6061-RAM2 Development and Hot-Fire Testing using Additive Manufacturing Laser Powder Directed Energy Deposition for Liquid Rocket Engine Channel-Cooled Nozzles

被引：2

作者：

Al Fedotowsky, Tessa ^{[1
]}

Williams, Ben B. ^{[2
]}

Gradl, Paul R. ^{[3
]}

Tinker, Darren C. ^{[2
]}

Iten, Jeremy ^{[4
]}

Hanerbino, Anthony ^{[4
]}

Polizzi, Adam ^{[4
]}

机构：

[1] NASA, Marshall Space Flight Ctr, Struct Dynam, Mail Stop ER41, Huntsville, AL 35812 USA

[2] NASA, Marshall Space Flight Ctr, Mail Stop ER13, Huntsville, AL 35812 USA

[3] NASA, Marshall Space Flight Ctr, Engine Syst Component Technol Branch, Huntsville, AL 35812 USA

[4] Elementum 3D, Erie, PA 80516 USA

来源：

AIAA SCITECH 2024 FORUM | 2024年

关键词：

D O I：

10.2514/6.2024-0994

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Aluminum 6061-RAM2 is a high-strength aluminum feedstock developed for additive manufacturing (AM) processes. This alloy leverages Reactive Additive Manufacturing (RAM) technology. The RAM aluminum alloys were developed to be weldable-therefore printable-while equaling or exceeding strength properties of high strength wrought aluminum alloys. NASA and industry partners developed Laser Powder Directed Energy Deposition (LP-DED) additive manufacturing of Al6061-RAM2 for use in aerospace applications. Efforts included establishing build parameters, characterizing the alloy, fabricating components, and completing hot-fire testing of complex internal channel-cooled nozzles. These efforts are to address the growing need for large-scale parts using high-performance light-weight materials. Two rocket engine nozzles were fabricated using LP-DED Al6061-RAM2 that included integral cooling channels. The Al6061-RAM2 has completed process development and initial properties were established. This paper provides an overview of the LP-DED process development, material characterization and properties, component manufacturing, supplemental development, and hot-fire testing. Results from hot-fire testing are provided for a lander-class 31 kN (7,000 lbf) thrust engine using Liquid Oxygen (LOX)/Liquid Hydrogen (LH2) and LOX/Methane (LCH4).

引用

页数：20