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Extreme Environment Hot Fire Durability of Post-Processed Additively Manufactured GRCop-Alloy Combustion Chambers in LOX/Hydrogen and LOX/MethaneExtreme environment survivability of metal additive manufactured (AM) GRCop-alloy thrust chambers has been demonstrated in different bi-propellants at near stoichiometric and even oxygen rich combustion. GRCop-alloy chambers tested at NASA Marshall Space Flight Center (MSFC) have accumulated over 26,000 seconds of hot fire duration and over 500 starts. These chambers are produced using an AM process called laser powder bed fusion (L-PBF). A major feature of this process is high wall surface roughness which can be customized in post processing to leverage various performance advantages. Post-processing can include heat treatment, final machining, polishing, and welding and is key to hardware survivability in extreme environments. Surface finish enhancement techniques were applied to the hot wall and coolant channels to reduce the overall total heat load to the chamber walls. Performance optimization of various thrust class TCA’s is a strategic technology goal of NASA MSFC. Three different chamber geometries using cryogenic methane and de-ionized water as coolants were hot fire tested to obtain their life cycle, pressure drop, and heat load performances. Several 1.2K lbf LOX/H2 chambers, 1K lbf LOX/CH4 chambers, and 7K lbf LOX/CH4 chambers were tested. All post-processed configurations performed remarkably well when subjected to extreme hot fire test conditions. Streaking and blanching due to localized oxygen rich conditions were observed on some test articles in their as-built surface finish state. However, this is actually a function of the injector mixing and only serves to further establish the durability of L-PBF GRCop-alloy thrust chambers. Several different polishing techniques were applied to the hot wall and integrated coolant channels prior to hot fire testing and their performances assessed. Overall, AM produced GRCop chambers are extremely reliable, durable, and customizable to the desired performance metrics.
Document ID
20210018268
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Thomas Teasley
(Marshall Space Flight Center Redstone Arsenal, Alabama, United States)
Paul Gradl
(Marshall Space Flight Center Redstone Arsenal, Alabama, United States)
Marissa B Garcia
(Marshall Space Flight Center Redstone Arsenal, Alabama, United States)
Benjamin Williams
(Marshall Space Flight Center Redstone Arsenal, Alabama, United States)
Christopher Protz
(Marshall Space Flight Center Redstone Arsenal, Alabama, United States)
Date Acquired
July 6, 2021
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: 2021 AIAA Propulsion and Energy Forum
Location: Virtual
Country: US
Start Date: August 9, 2021
End Date: August 11, 2021
Sponsors: American Institute of Aeronautics and Astronautics
Funding Number(s)
WBS: 571232.04.34.62
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
Single Expert
Keywords
grcop
additive manufacturing
laser powder bed fusion
hydrogen
methane
hot fire test
combustion
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