Science

1
2.2 Enabling Technologies2.2.2.1 Combustion
Driven Fluidic Actuators
Glezer (Ga Tech), Neumeier (Ga Tech), Jagoda
(Ga Tech)

• Science Technology Objective(s)
• Development of an innovative, combustion-based
  actuators.
• Mixing control
• Free jets for noise reduction
• Uniformly stirred combustors for ultra low
  emissions

• Collaborations
• Government ARL, AFRL
• URETI Ben Zinn (Ga Tech), Krish Ahuja (GTRI)
• Industry Val Kibens and William Bower (Boeing)
• Synergism with existing programs ARMY MURI,
  DARPA MAFC

Schematic rendition of proposed actuators for jet
noise control (left) and for combustor mixing
control (right).

• Proposed Approach
• Actuator performance analysis.
• Assessment of required momentum for combustor and
  free jet applications using existing large scale
  mechanical hardware (in collaboration with other
  URETI PIs)
• Parametric investigation of actuator performance,
  scaling and preferred dimensional configurations.
• Characterization of actuator jet.
• Demonstration on combustor and jet simulators (in
  collaboration with other URETI PIs)

Performance of a current combustion actuator.

• Milestones/Accomplishments
• Establishment of required actuation performance
  in the emission and noise control applications
  using existing subscale experimental facilities
  and mechanical actuators.
• Analysis of combustion based actuation to meet
  the established requirements.
• Design of prototypical experimental setup.
• Actuator performance characterization.
• Demonstration of combustion based actuation on
  subscale jet and combustor simulators.

• NASA Relevance/Impact
• Emissions
• Meeting NASA emission goals for subsonic aircraft
• Enabling acceptable emissions for supersonic
  transport
• Meeting NASA jet engine noise reduction goals

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2.2.2.1 Proposed Approach

• The required actuation performance for the
  emission and noise control applications will be
  established in existing subscale experimental
  facilities.
• Actuation will be provided using Georgia Techs
  advanced electromechanical actuators.
• Combustor rig will be operated at atmospheric and
  elevated pressures.
• The jet tests will be conducted from high
  subsonic to supersonic speeds.
• Analysis of combustion based actuation concepts
  will be conducted using low-level combustion
  models. Key issues will include performance
  tradeoffs and estimates of momentum and operating
  frequency.
• A prototypical actuator set up suitable for
  detailed parametric investigation of both the jet
  and the combustor actuators will be developed and
  constructed. Special consideration will be given
  to optical access and to measurements of the
  temperature and pressure and velocity
  distributions within the combustor.
• The performance of each actuator configuration
  will be characterized. The dependence of the
  actuator momentum on supply pressure, operating
  frequency, stoichiometry, spark energy, cooling
  effects, combustor volume and orifice geometry
  will be considered.
• The effects of combustion based actuation on jet
  noise and combustor mixing will be demonstrated
  in subscale jet and combustor simulators.
• Technology demonstration and transfer will be
  coordinated with industry and government partners.