NASA SBIR 2016 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 16-1 A1.03-7624
SUBTOPIC TITLE: Low Emissions/Clean Power - Combustion Technology/Emissions Measurement Techniques
PROPOSAL TITLE: Fluidic Fuel Flow Modulation for Active Combustion Control

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Advanced Fluidics, LLC
4217 Red Bandana Way
Ellicott City, MD 21042 - 5928
(443) 864-5295

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr SURYA RAGHU
sraghu@advancedfluidics.com
4217 Red Bandana Way
Ellicott City, MD 21042 - 5928
(443) 864-5295

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr Surya Raghu
sraghu@advancedfluidics.com
4217 Red Bandana Way
Ellicott City, MD 21042 - 5928
(443) 864-5295

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 1
End: 3

Technology Available (TAV) Subtopics
Low Emissions/Clean Power - Combustion Technology/Emissions Measurement Techniques is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
We propose a novel method of high frequency, high control authority fluidic modulation of pilot fuel flow to enable implementation of active combustion instability control (ACIC) either by feedback control or decoupling of the heat release frequency with that of the resonance frequency of the combustion chamber. The possible rugged design of the fluidic device permits its installation in the harsh environment right upstream of the fuel injector thus enabling closer coupling for high-fidelity control action. The method also provides a means of accurate measurement of fuel flow metered through the device. In Phase I, we propose design, fabrication and testing of two fluidic methods of pulsing the fuel � one method is driven by a fluidic oscillator and a second method by a vortex diode using an externally triggered pulse for phase controlled pulsations. In Phase II, based on the obtained performance characteristics and the customer needs, we will down-select the best of the options for further development.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The fluidic fuel flow modulator developed in this project will enable NASA GRC to evaluate the device in its specially designed characterization test rig for suitability in using it for active combustion instability control. The device will also help in the development of suitable control algorithms by NASA for implementation in actual jet engines. The fuel flow modulator can also be used to mitigate combustion instabilities in liquid fuel rockets as well - thus making the technology available for space launch vehicle design.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The market need for fuel modulators for active control of combustion instability in lean-burn combustors runs in millions both for aircraft engines as well as land-based gas turbines for power generation. In addition, there is a demand for such modulators for active control of reheat buzz in the military airplanes with afterburners. Potential end-customers are: Pratt & Whitney General Electric Siemens Rolls Royce

TECHNOLOGY TAXONOMY MAPPING (NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.)
Aerodynamics
Launch Engine/Booster

Form Generated on 04-26-16 15:14