A Turbo-Brayton Cryocooler for Aircraft Superconducting Systems

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$1,196,822.00
Award Year:
2013
Program:
SBIR
Phase:
Phase II
Contract:
NNX13CC07C
Award Id:
n/a
Agency Tracking Number:
114849
Solicitation Year:
2011
Solicitation Topic Code:
A2.01
Solicitation Number:
n/a
Small Business Information
NH, Hanover, NH, 03755-3116
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
072021041
Principal Investigator:
AnthonyDietz
Principal Investigator
(603) 640-2310
ajd@creare.com
Business Contact:
JamesBarry
Business Official
(603) 640-2487
contractsmgr@creare.com
Research Institute:
Stub




Abstract
Hybrid turboelectric aircraft with gas turbines driving electric generators connected to electric propulsion motors have the potential to transform the aircraft design space by decoupling power generation from propulsion. Resulting aircraft designs such as blended-wing bodies with distributed propulsion can provide the large reductions in emissions, fuel burn, and noise required to make air transportation growth projections sustainable. The power density requirements for these electric machines can only be achieved with superconductors, which in turn require lightweight, high-capacity cryocoolers. We have developed a Cryoflight turbo-Brayton cryocooler concept that exceeds the mass and performance targets identified by NASA for superconducting aircraft. In Phase I of this project, we extended our initial design study and developed modeling tools to support system-level optimization and individual component designs. We focused on the critical component for mass reduction?the recuperative heat exchanger?and performed risk reduction activities to demonstrate the feasibility of our concept for this component. In Phase II, we will design, build, and test two compact lightweight, high-performance recuperators for the Cryoflight cryocooler. This development effort will provide an enabling technology for the superconducting systems needed for hybrid turboelectric aircraft to be feasible.

* information listed above is at the time of submission.

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