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Uncertainties and Limitations of Experimental Thrust and Pressure Gain Measurements in a Rotating Detonation Combustor

Conference · · AIAA SCITECH 2023 Forum
DOI:https://doi.org/10.2514/6.2023-0930· OSTI ID:1995215
 [1];  [2];  [2]
  1. University of Michigan; University of Michigan, Aerospace Engineering
  2. University of Michigan
+ Show Author Affiliations
Experimentally measuring the pressure gain through the method of equivalent available pressure is prone to many experimental uncertainties. This study performs a detailed uncertainty analysis of the thrust and pressure gain measurements utilizing data from a H2/air operated rotating detonation combustor with an axial air inlet and a 50% exit constriction. The measured (negative) pressure gain values agree with the results in literature for similar inlet-to-exit area ratios. Specific considerations are given to the uncertainty in thrust measurement introduced by the base drag correction on the inner-body. The assumed unity Mach number utilized in the equivalent available pressure methodology is evaluated experimentally with two different methods using time-averaged measurements at the exhaust plane. A definitive demonstration of gain will be challenging given the assessed uncertainties, but recommendations are given to increase the precision of the equivalent available pressure methodology to estimate pressure gain.
Research Organization:
University of Michigan, Ann Arbor
Sponsoring Organization:
USDOE Office of Fossil Energy and Carbon Management (FECM)
DOE Contract Number:
FE0031228
OSTI ID:
1995215
Report Number(s):
DOE-UMICH-FE0031228-004
Conference Information:
Journal Name: AIAA SCITECH 2023 Forum
Country of Publication:
United States
Language:
English

References (21)

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