NASA SBIR 2020-I Solicitation

Proposal Summary


PROPOSAL NUMBER:
 20-1- A1.07-6799
SUBTOPIC TITLE:
 Propulsion Efficiency - Turbomachinery Technology for High Power Density Turbine-Engines
PROPOSAL TITLE:
 Axial Compressor Map Generation Leveraging Autonomous Self-Training AI
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
SoftInWay, Inc.
1500 District Ave
Burlington, MA 01803
(781) 685-4942

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Maksym Burlaka
E-mail:
m.burlaka@softinway.com
Address:
1500 District Ave Burlington, MA 01803 - 5069
Phone:
(781) 862-7866

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Leonid Moroz
E-mail:
l.moroz@softinway.com
Address:
1500 District Ave Burlington, MA 01803 - 5069
Phone:
(789) 685-4942
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

NASA is looking for improvement in aeropropulsive power density and efficiency in support of its Strategic Thrust in the area of Ultra-Efficient Subsonic Transports, focusing on small core turbofan engines for next-generation and future large commercial transport aircraft. The trend in the design of modern gas turbine engines is for ever-increasing cycle efficiency and reduced specific fuel consumption. To achieve these engine cycle efficiency goals, the low and high-pressure compressors (HPC) are pushed to ever-increasing levels of pressure ratio. Increasing levels of compressor pressure ratio results in higher rotor tip relative Mach number in the HPC front stages, and consequently steeper performance characteristic maps. The compressors with steep characteristics typically require variable geometry inlet guide vanes as well as variable stators in the first few stages to provides the desired performance and stability in an engine system. The design and development time of a modern high-pressure compressor with variable geometry can take years of design-build-test iterations which includes testing a large number of possible reset angles of the variable vanes. Determining the optimal combination of vane angle resets that will provide the desired compressor performance in an engine system environment is a time consuming and expensive part in the development of high-pressure compressors. It is proposed to address the optimization of the variable geometry reset angle schedules with the use of the innovative autonomous AI technology. The AI-based performance prediction model can be easily incorporated inside of the system analysis tool and reliably predict the performance with high accuracy across the entire operating range of compressor even with multiple variable guide vanes and thus helping to approach true optimal engine performance and reduce the chances of additional expensive design iterations in real-life projects.

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

The research is closely aligned with NASA Aeronautics programs in the areas of Compact Gas Turbine and Electrified Aircraft Propulsion and will augment the corresponding Advanced Air Transport Technology Project's Technical Challenges, in particular the use of artificial intelligence (AI) for highly accurate axial compressor performance map generation which will help to quickly find the optimal strategies of guide vanes reset angles variation to maximize performance. The improvements will help airlines to reduce costs by reduced fuel burn.

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

The AI-based performance prediction model is in high demand in the companies designing the airbreathing propulsion and power generation units because it would allow to dramatically reduce the engine development time and cost. Also, it can be useful to the end-users of the engines, by reconstructing the entire performance map of the compressor based on a limited number of performance points.

Duration: 6

Form Generated on 06/29/2020 21:07:54