NASA SBIR 2012 Solicitation


PROPOSAL NUMBER: 12-2 A3.08-9070
SUBTOPIC TITLE: Propulsion Efficiency - Turbomachinery Technology
PROPOSAL TITLE: A Novel Plasma-Based Compressor Stall Control System

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Creare, Inc.
P.O. Box 71
Hanover, NH 03755 - 3116
(603) 643-3800

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Richard W. Kaszeta
P.O. Box 71
Hanover, NH 03755 - 3116
(603) 640-2441

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert J. Kline-Schoder
P.O. Box 71
Hanover, NH 03755 - 3116
(603) 643-3800 Extension :2487

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

Technology Available (TAV) Subtopics
Propulsion Efficiency - Turbomachinery Technology is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
Modern aircraft gas turbine engines utilize highly loaded airfoils in both the compressor and turbine to maximize performance while minimizing weight, cost, and complexity. However, high airfoil loading increases the likelihood of flow separation at lower mass flow rates. Dielectric Barrier Discharge (DBD) plasma actuators have been shown to be a very promising technique for compressor stall control. DBD devices can either be installed directly on rotor/stator surfaces or the compressor endwalls to control rotor tip flow. A fundamental challenge in driving DBD actuators is providing appropriate electrical waveforms to the devices. Creare proposes the development of an innovative compressor stall system which enables (1) substantially higher produced thrust than existing DBD actuator systems, (2) implements a unique excitation waveform that optimizes thrust production by DBD actuators, and (3) provides the potential ability to control spike-type compressor stall through controlling compressor tip leakage flow.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
This technology supports NASA's mission to help improve the performance of commercial aviation through development of advanced gas turbine engine systems. The technology also has the potential for enabling improved gas turbine engine performance for applications as far reaching as Unmanned Aerial Vehicles (UAVs) proposed for extraterrestrial exploration. An efficient DBD actuator system can provide active stall control for compressor blading and low-pressure turbine blades. Implementation of a practical DBD actuator system, including the necessary driving and control electronics, should allow significantly improved low mass flow operation of turbine engines, as well as greatly increased operational envelopes.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
In addition to military and NASA customers, a fully developed active flow control technology for turbomachinery may also prove useful in commercial applications in which separation phenomena are known to cause performance issues, including turbine engines (for both power generation and aircraft use) and aerial vehicles. The implementation of an effective and efficient compressor stall control system can greatly improve the operational envelopes for both existing retrofitted compressors, as well as enable new compressor designs with significantly lower stall limits.

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.)
Actuators & Motors
Atmospheric Propulsion
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)

Form Generated on 03-04-14 13:38