NASA SBIR 2018-II Solicitation

Proposal Summary

 18-2- H10.01-4202
 Advanced Propulsion Systems Ground Test Technology
 Balanced Floating Piston Valve for Ultra-High Pressure, High-Volume Liquid and Gaseous Flow Control
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
C-Suite Services, LLC
114 Mulberry Drive
Metairie, LA 70005
(303) 594-4300

PRINCIPAL INVESTIGATOR (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Bruce Farner
1072 Clipper Drive
Slidell, LA 70458
(985) 710-2005

BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Kevin Pollard
114 Mulberry Drive
Metairie, LA 70005 - 4015
(303) 594-4300

Estimated Technology Readiness Level (TRL) :
Begin: 5
End: 7
Technical Abstract (Limit 2000 characters, approximately 200 words)

Contractor has completed all scheduled work and accomplished the Technical Objectives (milestones): (1) Finite Element Analyses (FEA), (2) Computational Fluid Dynamics (CFD) analyses, as well as (3) Seal Design and Material Selection.  A 4th Technical Objective was added:(4) Geometry Design and Material Selection, as critical to the successful design of a manufacturable valve.

Technical Objective

Work Plan

Key Results

FEA optimized design

Highly iterative design process modeled with ANSYS

Piston design met  balance requirements with displacement ≤0.002”

A-286 stainless steel was selected as the material for the piston

CFD flow-path optimization

Highly iterative flow-path process modeled with ANSYS

Decision to use the Drilled Holes Concept rather than the 3-Hole Strut results in 86.5% of the Cv (700) of the ideal ball valve

Seal design and material

Collaboration with Saint-Gobain

Decision to use a bi-directional, spring-assisted, pressure-energized, polymer fiber-filled Teflon seal

Seat geometry and material

Collaborative process that included FEA and CFD analyses

Decision of 60º and Silicon Aluminum Bronze C64200 material

The 12 Tasks of the Work Plan in the SBIR Phase I were completed.  NASACustomer requirements were investigated and confirmed; industries and markets were researched and new commercial opportunities identified.

The manufacturability of the ultimate valve design was validated with the receipts of two quotes from two pre-qualified machine shops, both of which indicated their willingness and ability to manufacture a FPV prototype.  The modifications to the FPV during the SBIR Phase I Feasibility Study have resulted in a safer, cost-effective, far more reliable alternative to conventional ball valves currently used for rocket engine ground testing at Stennis Space Center’s (SSC) E Complex.

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

Contractor believes that the FPV, as modified, will be proven as a “drop in” replacement for the existing ball valves at NASA's rocket propulsion testing grounds. Contractor also believes that the FPV can be miniaturized for cryogenic fluid flow control aboard space craft and storage stations in deep space environments.

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

The following additional commercial opportunities were identified: private space flight; oil and gas processing; upstream and midstream pipeline; hydrocarbon exploration and production; and, aircraft markets. Additionally, Contractor believes that the FPV can be successfully modified as a Pilot-Operated Relief Valve (PORV) and a Pressure Relief Devices (PRD) for many other applications.

Duration: 24

Form Generated on 05/13/2019 13:31:45