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High-Speed Diagnostics in a Natural Gas–Air Rotating Detonation Engine

Journal Article · · Journal of Propulsion and Power (Online)
DOI:https://doi.org/10.2514/1.b37740· OSTI ID:1817706
 [1];  [2];  [3];  [2];  [2];  [2]
  1. Arnold Engineering Development Complex, Arnold AFB, TN (United States); Aerojet Rocketdyne, Inc.
  2. Purdue Univ., West Lafayette, IN (United States)
  3. Aerojet Rocketdyne, Inc., Canoga Park, CA (United States)

An application of high-speed diagnostic techniques in a natural gas-air rotating detonation engine at conditions relevant to land-based power generation is presented. Diagnostics included high-frequency chamber pressure measurements, chemiluminescence imaging of the combustor annulus (aft looking forward), and particle image velocimetry measurements at the exit plane of the engine and tangent to the center body. Detonation surface plots are created from chemiluminescence images and allow for the extraction of properties such as dominant mode frequencies and wave number, speed, and direction. Dynamic mode decomposition is also applied to the chemiluminescence images to isolate various spatial modes within each test. Singular-spectrum analysis is used to isolate modes corresponding to the detonation frequency in the signals of velocity components obtained from particle image velocimetry, maintaining instantaneous phase information. Results from a case with a primary mode corresponding to a single wave rotating clockwise with a minor wave rotating counterclockwise are presented. Results from a case with two detonation waves rotating clockwise in the combustor annulus are also presented. Furthermore, the dominant chamber frequency for the case with two co-rotating waves in the chamber is found to be 3.46 kHz, corresponding to two individual waves traversing the annular combustion chamber at average speeds of 68% of the Chapman-Jouguet velocity. Dynamic mode decomposition indicates the presence of two major detonation waves rotating clockwise and periodically intersecting with two minor, counterclockwise rotating waves in the annulus during operation. Axial and azimuthal components of velocity from this case are observed to remain nearly in phase and are determined to correspond to the two minor, counterclockwise rotating waves.

Research Organization:
Aerojet Rocketdyne, Inc., Canoga Park, CA (United States)
Sponsoring Organization:
USDOE Office of Fossil Energy (FE)
Grant/Contract Number:
FE0023983
OSTI ID:
1817706
Alternate ID(s):
OSTI ID: 1799786
Journal Information:
Journal of Propulsion and Power (Online), Journal Name: Journal of Propulsion and Power (Online) Journal Issue: 4 Vol. 36; ISSN 1533-3876
Publisher:
American Institute of Aeronautics and Astronautics (AIAA)Copyright Statement
Country of Publication:
United States
Language:
English

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