Plasma-Injection Module for Scramjet/Ramjet/Turbojet Applications

Efforts to understand and develop effective plasma-assisted combustion in gas turbine engines have been underway for 20+ years.  To date, no practical devices have yet been developed that provide:

  • reliable ignition,
  • appropriate mixing intensification,
  • suitable flame stabilization,
  • enhancement of combustion completeness, and
  • satisfactory pollution control. 

The University of Notre Dame has recently developed a plasma-injection module (PIM) that produces extended filamentary plasma that become entrained in the fuel-air mixing layer and thereby extended by the fuel-injection flow, penetrate into the main airflow, and then terminate far downstream.  Validating experiments have been performed in the supersonic blow-down wind tunnel SBR-50 at the University of Notre Dame.  In recent tests, the Quasi-DC discharge was employed for fuel ignition and flameholding in supersonic airflows; this type of electrical discharge is considered beneficial compared to plasma torches and less powerful discharges such as Dielectric Barrier Discharges.  Supplied by a DC voltage waveform, this discharge demonstrates an oscillatory pattern of its dynamics, significantly affecting flow structure and mixing processes.  Thus, proper operation of a Q-DC discharge in ND’s PIM configuration can be realized in high-speed flow in a wide range of gas density/pressure due to a strong coupling of the plasma to the flowing gas. The second generation of PIM demonstrated even higher performance due to application the magnetic-induced active rotation of the plasma filaments.

Figure 1. a) Operational concept of PIMs

Pic 1 Resized D20 010

 

                               

 

 

 

 

 

 

 

b) Schematics of the PIM assembly

 

Pic 2 Resized D20 010

 

 

 

 

 

 

 

Specific benefits of ND’s revolutionary PIM include:

  • long plasma filament located in the fuel-oxidizer mixing layer; which provides
  • significantly longer times for plasma - fuel interaction;
  • higher local power deposition at local gas temperatures up to 6kK;
  • extremely short ignition / reignition time.

Further, the PIM is made of refractory materials, which permit operation in a harsh environment, and the PIMs are flush-mounted on the combustor wall, thus eliminating any mechanical disturbance of the flowfield.  Finally, electronic operation of the PIMs allows their implementation in active close-loop control systems.

TRL 4: Validation in laboratory environment. 

PI: Dr. Sergey B. Leonov.  Dept. of Aerospace & Mechanical Engineering, University of Notre Dame

Patent status: Not yet filed.

Publications:  “Electrically Driven Supersonic Combustion”, Energies 2018, 11, 1733; doi:10.3390/en11071733

Available for licensing and research collaboration.

For more information, contact: Richard Cox, Director of Licensing & Business Development, ND IDEA Center.  Phone (574) 631-5158 | Email: rcox4@nd.edu