SBIR/STTR Research Award

Novel, Functionally Graded Coating System for Reusable, Very High Temperature Applications

Award identifier 7fce1a302323611c7c2234699833dd5f107d209ebf858db9ebe35d34cfcfa57bAwarding agency National Aeronautics and Space Administration

Award amount

$749,311

Program and phase

SBIR · Phase II

Award year

2017

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Award details

Awarding agency
National Aeronautics and Space Administration
Branch
Not reported
Recipient company
Allcomp Inc.
Proposal award date
2017-05-31
Contract end date
2019-05-30
UEI
D55JVDSPY5K5
Solicitation number
Not reported
Topic code
H5.02

Research abstract

There is a clear need to advance the state-of-the-art carbon-carbon coated Nozzle Extensions (NE) beyond the engine/mission performance currently established by Herakles technology, which is intrinsically limited to about 3000 F. The well-established SiC-based (CVD, pack cementation) technologies currently available also have upper temperature limits around 3000 F, imposing stringent limitations on increased performance and system level changes (i.e. hotter propellant) for future NASA missions. In addition, the intrinsic CTE mismatch between C-C substrate and refractory carbides/oxides further limits the use of many other classical coating technologies. The successful Phase I results established the feasibility of overcoming these limitations through the use of a novel, functionally graded (FGM) coating technology. The proposed Phase II builds on the success of the Phase I program and clearly increases its TRL by offering subscale component testing at representative engine conditions. A successful Phase II program will clearly offer a new dimension in the nozzle extensions by offering different coating systems for multi-cycle capability at temperatures from 3000 F up to 4000 F. The expected ability of the coating to survive such an aggressive testing combined with the sufficient retention of mechanical properties offers a direct path for a Phase III with many of the commercial space payload companies. The overall approach is based upon a multi-piece C-C NE concept, which focuses the requirements for high temperature oxidation protection to smaller diameters of the nozzle extension (e.g. A cone), allowing the CVD coating technology to remain within current SOTA CVD capabilities. Larger diameter segments, which are exposed to lower temperatures, will utilize non-CVD lower cost technology which is well suited for large diameter components. The direct benefit to NASA is undisputed with direct applicability to several planned future missions, including the very challeng

Technology keywords

Not reported

Other awards by this recipient

Verified by the same UEI. These are other public SBIR/STTR award pages, not a merged company record.

Awards with the same topic code

Verified by an exact topic code match. This is not a text-similarity match.

Research funding history

62 SBIR/STTR records share this UEI (1999–2020). Reported award amounts total $22,355,305. Reported amounts are not federal obligations.

Phases: Phase I, Phase II

Agencies: Department of Defense, National Aeronautics and Space Administration, Department of Energy

Agency intelligence

National Aeronautics and Space Administration

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