Acoustics and Performance of a Scaled Spacecraft Cabin Ventilation Fan



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2024 International Conference on Environmnetal Systems


An axial fan was designed at NASA Glenn Research Center using tools developed for aircraft turbine engines. The fan unit design size, flow rate and pressure rise were chosen to be broadly in the range of the Orion cabin fan. A ground test prototype was built and tested, confirming design predictions. Pressure rise and flow rate measurements were conducted over a range of fan speeds while in-duct and radiated acoustic measurements were collected. Unsteady flow measurements were acquired between the rotor and stator. These methods are a hybrid of the techniques used for small fans and those used for aircraft engine component tests. A larger version of the fan was recently designed, based on the original fan, using aerodynamic scaling laws resulting in a design with approximately twice the flow rate and twice the pressure-rise compared to the original fan. The mechanical structure was optimized using generative design for low weight. The paper discusses this larger fan design including the scaling laws, the predicted performance and acoustics.


David Stephens, NASA Glenn Research Center (GRC), USA
L. Danielle Koch, NASA Glenn Research Center (GRC), USA
Jonathan Goodman, NASA Glenn Research Center (GRC), USA
Christopher Allen, NASA Johnson Space Center (JSC), USA
ICES300: ECLSS Modeling and Test Correlations
The 53rd International Conference on Environmental Systems was held in Louisville, Kentucky, USA, on 21 July 2024 through 25 July 2024.


acoustics, fan, axial, aircraft