Integrated Brayton Cryocooler for LOx and LH2 Applications

NASA is in need of affordable and robust cryogenic cooling solutions for use in space applications. In support of the Artemis program, NASA seeks innovative integrated refrigeration cycles for use in liquefaction of hydrogen and oxygen from the lunar surface. Based on initial estimates from Phase I activities, 330+ W of cooling is needed at 90 K and 130+ W of cooling is needed at 20 K to support at least 11.7 metric tons per year. Currently, space-based cryocoolers have yet to demonstrate cooling beyond 20 W at 20. Concepts NREC (CN) is working towards the demonstration of two high-capacity helium-based reverse-Brayton cryocoolers, and plans to leverage these cryocoolers to develop a novel integrated two-stage helium system capable of supporting both oxygen and hydrogen liquefaction needs on the Moon. The proposed solution will increase the current state-of-the-art in cryogenic cooling by an order of magnitude. The two lowest TRL/MRL components derived from Phase I activities are a micro-tube recuperator with a titanium construction replacing the legacy materials, and a compressor capable of operation under lunar surface ambient conditions. The titanium micro-tube recuperators utilize a proven, underlying design; the same manufacturing method and models can easily be adapted to the changes brought upon by the change to titanium, and development risk is considered low. Lunar ambient compressor operation has the highest system risk when looking at the changes from legacy CN demonstrations. Existing turboalternator powertrain technology will be leveraged to develop a compressor powertrain that is capable of operation at the reduced ambient conditions. The capabilities of the newly developed powertrain will need to handle larger thrust loads at higher rotational speeds than what is currently found on the turboalternators. Results from this study will provide valuable input into NASAs on-going Cryogenic Fluid Management directives. NASA is in need of affordable and robust cryogenic cooling solutions for use in space applications.  In support of the Artemis program, NASA seeks innovative integrated refrigeration cycles for use in liquefaction of hydrogen and oxygen from the lunar surface. Based on initial estimates from Phase I activities, 330+ W of cooling is needed at 90 K and 130+ W of cooling is needed at 20 K to support at least 11.7 metric tons per year. Concepts NREC (CN) is working towards the demonstration of two high-capacity helium-based reverse-Brayton cryocoolers, and plans to leverage these cryocoolers to develop a novel integrated two-stage helium system capable of supporting oxygen and hydrogen liquefaction demand. The proposed solution will increase the current state-of-the-art in cryogenic cooling by an order of magnitude. One of the lowest TRL/MRL components derived from Phase I activities is a compressor capable of operation under lunar surface ambient conditions. Results from this study will provide valuable input into NASA’s on-going Cryogenic Fluid Management directives. The technical objective of the Phase II SBIR program effort will be to specifically design and mature the 200 K compressor technology, for use on the proposed two-stage helium cryocooler. At the completion of the program, the 200 K Helium compressor maturity is expected to increase to TRL = 5 and MRL = 5. To achieve the technical objectives identified, Concepts proposes the Phase II tasks as given below.  This development effort will involve the following primary activities: Design of 200 K compressor aerodynamics components Application of design modifications to the existing 30 K turboalternator drivetrain to operate as a compressor at 200 K. Modifications are expected to be limited to the aerodynamics and journal bearings.  In addition, modifications are not expected to require new modeling or manufacturing methods. Fabrication, procurement and assembly of 200 K compressor test articles. Testing of the 200 K compressor in CN test facility. Various facility capability improvements will be required, such as a cooled shroud for maintaining the compressor near 200 K, an aftercooler operating at 200 K and remote control of cryogenic valves. The primary deliverable will be a compressor assembly capable of operating in the 200 K temperature environment, and meeting all specified performance requirements.

NASA is in need of affordable and robust cryogenic cooling solutions for use in space applications.  In support of the Artemis program, NASA seeks innovative integrated refrigeration cycles for use in liquefaction of In-Situ Resource Utilization produced hydrogen and oxygen from the lunar surface. Based on initial estimates from Phase I activities, 330+ W of cooling is needed at 90 K and 130+ W of cooling is needed at 20 K to support at least 11.7 metric tons per year. The US Navy has identified multiple applications in minesweeping, degaussing, and ship-board power transmission.  The worldwide market for industrial and commercial cryocoolers is developing based on a need for High-Temperature Superconducting (HTS) cooling needs, superconducting generators for wind turbines being pursued in Europe as one example.

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