Proposal Number:          21-1- Z7.04-1831

          

          

   

Subtopic Title:
      Landing Systems Technologies

          

          

   

Proposal Title:
      Multiphase Hypergolic Combustion Simulation Tool Based on Algebraic VOF and Compressible Flamelet Methodologies

          

          

   

Firm:

          

Streamline Numerics, Inc.

          

   

Address:

          

3221 North West 13th Street, Suite A, Gainesville, FL 32609

          

   

Phone:

          

(352) 271-8841                                                                                                                                                                                

          

   

Name:

          

Dr. Siddharth Thakur

          

   

E-mail:

          

st@snumerics.com

          

   

Address:

          

3221 North West 13th Street, Suite A, FL 32609 - 2189

          

   

Phone:

          

(352) 271-8841                                                                                                                                                                                

          

   

Name:

          

Dr. Jeffrey Wright

          

   

E-mail:

          

jeffwright83@gmail.com

          

   

Address:

          

12017 sw 122nd st, FL 32608 - 5847

          

   

Phone:

          

(352) 271-8841                                                                                                                                                                                

          

   

Estimated Technology Readiness Level (TRL) :                                                                                                                                                          
Begin: 2
End: 4

          

          

     

Technical Abstract (Limit 2000 characters, approximately 200 words):

The innovation proposed is an advanced multiphase hypergolic combustion simulation capability in a computational fluid dynamics (CFD) tool called Loci-STREAM, to improve the understanding of hypergolic ignition and transient flame dynamics which would enhance NASA’s ability to simulate engine-start, main-stage and shutdown characteristics of hypergolic engines. The key objectives of this work are: (1) demonstration of the suitability of compressible flamelet-based models for gas phase combustion of hypergolic propellants, (2) development of a spray combustion capability based on Lagrangian Particle (Droplet) Tracking algorithm, droplet evaporation models, and secondary breakup models, and (3) development of the foundation for modeling impingement of liquid hypergolic propellant jets based on an algebraic volume of fluid (VOF) method. The computational modeling capability resulting from this work will enable us to define the interrelationships between operational parameters (e.g., flows, pressures, timing, etc.) and combustion chamber dynamic responses. The results will help designers and modelers understand relevant environments and inform test engineers of instrumentation best practices to capture relevant behaviors. The user community will also benefit by preventing damage to hardware and designing safer and more efficient start-up sequences. Specifically, the following application areas will benefit immediately from this project: (a) NASA’s ability to simulate engine start, main-stage and shutdown characteristics of hypergolic engines, (b) NESC’s material compatibility assessment effort involving flammability and ignition susceptibility of titanium in NTO environments, (c) NESC effort to test different materials for O-rings for compatibility with hypergolic propellants, (d) Transient modeling in Draco and SuperDraco engines developed by Space-X, (e) Improved combustion instability predictions for existing and future hypergolic propellant engines, etc.

          

          

     

Potential NASA Applications (Limit 1500 characters, approximately 150 words):

(a)    NASA programs such as Orion Multi-Purpose Crew Vehicle, Commercial Crew Program, Mars 2020, Europa Clipper, International Space Station and the NESC.
(b)    NASA’s ability to simulate engine-start, main-stage and shutdown characteristics of hypergolic engines.
(c)    NESC’s material compatibility assessment effort involving flammability and ignition susceptibility of titanium in NTO (Nitrogen tetroxide, a hypergolic oxidizer).
(d)    NESC effort to test different materials for O-rings for compatibility with hypergolic propellants
 

          

          

     

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words):

(a)    Draco and SuperDraco engines developed by Space-X.
(b)    Agile Space Propulsion’s Advanced Space Engine (ASE) line of MON-25/MMH thrusters.
(c)    Aerojet Rocketdyne’s R-4D family of hypergolic engines (MMH & NTO oxidizer).
(d)    Army’s Impinging Stream Vortex Engine (ISVE) 
(e)    Improved combustion instability predictions for existing and future hypergolic propellant engines.
 

          

          

     

Duration:     6