Rotating Detonation Engine for Rocket Propulsion

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9300-19-P-1002
Agency Tracking Number: F182-063-0450
Amount: $149,998.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: AF182-063
Solicitation Number: 2018.2
Timeline
Solicitation Year: 2018
Award Year: 2019
Award Start Date (Proposal Award Date): 2019-02-27
Award End Date (Contract End Date): 2020-02-27
Small Business Information
6210 Kellers Church Road, Pipersville, PA, 18947
DUNS: 929950012
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Vineet Ahuja
 (215) 766-1520
 vineet@craft-tech.com
Business Contact
 Brian York
Phone: (215) 766-1520
Email: york@craft-tech.com
Research Institution
N/A
Abstract
The use of a detonation cycle involving constant volume combustion offers significant promise in improving the efficiency, increasing specific impulse and reducing fuel consumption over conventional deflagration based propulsion systems.Recent accomplishments including testing with Rotating Detonation Engine (RDE) demonstrators for gas turbine applications have shown successful operation and feasibility at operating pressures below 10 atmospheres.However, for operation at elevated pressures suitable for rocket applications there are several additional challenges associated with sustaining a stable detonation front in the combustion chamber.At operating pressures characteristic of rocket engines, the characteristic injection times and mixing rates are very different.Injection schemes with slower refresh rates or sub-optimal mixing will result in pulsations, irregular detonation periods and weakening of the detonation wave resulting in a transition to the deflagration mode, thereby negating all the accrued advantages of the RDE over the conventional Brayton cycle.In this proposal a multi-fidelity suite of design tools will be developed to identify injector designswith optimal mixing efficiency and minimal total pressure losses as well as nozzle designs for performance enhancement of the RDE.The component designs will be incorporated in an RDE which will be tested and demonstrated for stability.

* Information listed above is at the time of submission. *

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