NASA SBIR 2008 Solicitation


PROPOSAL NUMBER: 08-1 A2.02-9878
SUBTOPIC TITLE: Combustion for Aerospace Vehicles
PROPOSAL TITLE: Scramjet Combustion Stability Behavior Modeling

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Gloyer-Taylor Laboratories LLC
2212 Harton Blvd
Tullahoma, MS 37388 - 5583
(931) 393-5108

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Paul Gloyer
2212 Harton Blvd
Tullahoma, MS 37388 - 5583
(931) 393-5108

Expected Technology Readiness Level (TRL) upon completion of contract: 3 to 4

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
A recent breakthrough in combustion stability analysis (UCDS) offers the means to accurately predict the combustion stability of a scramjet. This capability is very important due to the extreme scramjet operational environment, which makes cut-and-try development approaches impractical. With UCDS, it is now possible to accurately predict the scramjet pressure oscillation amplitudes, along with critical parameters, including the unsteady wall heat flux.
The UCDS tools were recently applied to the Ares I thrust oscillation issue in support of NASA's Thrust Oscillation Focus Team (TOFT). This effort included the analysis of the Shuttle four segment solid rocket motor (RSRM) to validate the capabilities of UCDS. After analyzing the new five segment (RSRMV) motor being developed for Ares I, GTL used the UCDS insight to identify a relatively minor motor modification that will eliminate the organized motor oscillations.
With this validation of the capabilities and effectiveness of UCDS, GTL proposes to extend the application of UCDS by applying it to examine the stability characteristics of a representative scramjet. In addition to predicting the amplitudes of the scramjet pressure oscillations, a UCDS sensitivity analysis will be used to identify critical design parameters and establish development guidelines.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Since the UCDS models are built from a general formulation, they can be used to analyze practically any combustion device, including rockets (liquid, solid, hybrid), turbojets (combustors, augmentors), ramjets, scramjets, combined cycle engines and so on. As such, UCDS can be used by NASA in the development of practically any propulsive device. Specific near term NASA applications for UCDS include:
- Continued effort to mitigate the Ares I thrust oscillation effort
- Working with the Ares V team to avoid potential thrust oscillation issues
- Supporting the Constellation Program by identifying and avoiding potential stability issues that will arise when engines and motors are scaling up to meet performance requirements
- Supporting the development of new propulsion devices, such as scramjets

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
With its broad capabilities, UCDS can be used by any combustion device developer, including the Air Force, Navy, Army, MDA, DARPA, DOE, and commercial propulsion developers, such as ATK, Aerojet, Pratt & Whitney and others. One specific non-NASA applications for UCDS is the Air Force/Aerojet Hydrocarbon Boost Engine development program.

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.

Aircraft Engines
Fundamental Propulsion Physics

Form Generated on 11-24-08 11:56