Small Business Innovation Research/Small Business Tech Transfer
Development of Axial Compressor Heat-Extraction Capability for Thermal Management Applications
Project Description
ATA Engineering, Inc. (ATA) proposes a small business innovation research (SBIR) program for a novel compressor heat-extraction development program in response to NASA's solicitation for advanced design concepts to enable increased high stage loading in single and multi-stage axial compressors while maintaining or improving aerodynamic efficiency and operability. The 'compressor cooling' development program proposed herein will be applicable to advanced turbomachinery based combined cycle (TBCC) propulsion systems suitable for high Mach number flight vehicles that extend to the hypersonic range as well as to conventional high bypass ratio (HBPR) engines that operate with high compressor exit temperatures. Cooling in the rear stages of a compressor would improve mass flow capability, increase margins set by material temperature limits, and improve turbine blade cooling effectiveness by reducing bleed air temperatures. The Phase I proposal technical objectives are to 1) estimate the system level benefit of compressor heat extraction for a mutually agreed-on TBCC-powered aircraft mission, 2) understand the fluid dynamics of flows with surface heat extraction in a multistage compressor using computational fluid dynamics, and 3) define the necessary validation steps on cascade and compressor component rig hardware to advance the technology readiness level of compressor cooling to the point where it may be implemented in an aircraft engine application. The final deliverable will be a written report to NASA presenting a conceptual design of a cooled compression system and a proposed test plan for Phase II rig validation, based on the requirements set forth in a design specification that is defined at the beginning of the program.
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Anticipated Benefits
Gas-turbine applications extend well beyond NASA's developmental programs, and it is believed that all of the potential benefits suggested in the NASA commercial applications section would apply to the sphere of interest of the aircraft engine manufacturers, for both military and commercial engine applications. In addition, compressor heat extraction schemes in some cases may provide additional opportunities for performance and life improvement in industrial gas turbine applications where intercooling and water injection are routinely used.
The most immediate opportunities for a compressor heat-extraction system are: 1) as an enabler to advanced turbomachinery based combined cycle (TBCC) propulsion systems used in NASA's next generation high flight Mach number vehicles, such as single-stage-to-orbit (SSTO) concepts and 2) to improve performance of multi-stage compressors in NASA's next generation high bypass ratio turbofan-powered aircraft applications (N+1 and beyond) that are currently limited by both compressor material temperature limits and compressor bleed air temperature limitations on turbine blade cooling effectiveness. NASA would also be able to potentially realize ancillary cycle benefits from compressor heat extraction in the form of pre-heating of fuel and "cooling of cooling air" in turbine blade applications where compressor bleed is the heat sink. More »
The most immediate opportunities for a compressor heat-extraction system are: 1) as an enabler to advanced turbomachinery based combined cycle (TBCC) propulsion systems used in NASA's next generation high flight Mach number vehicles, such as single-stage-to-orbit (SSTO) concepts and 2) to improve performance of multi-stage compressors in NASA's next generation high bypass ratio turbofan-powered aircraft applications (N+1 and beyond) that are currently limited by both compressor material temperature limits and compressor bleed air temperature limitations on turbine blade cooling effectiveness. NASA would also be able to potentially realize ancillary cycle benefits from compressor heat extraction in the form of pre-heating of fuel and "cooling of cooling air" in turbine blade applications where compressor bleed is the heat sink. More »
Primary U.S. Work Locations and Key Partners
| Organizations Performing Work | Role | Type | Location |
|---|---|---|---|
| ATA Engineering, Inc. | Lead Organization | Industry | San Diego, California |
Glenn Research Center
(GRC)
|
Supporting Organization | NASA Center | Cleveland, Ohio |
Primary U.S. Work Locations
-
California
-
Ohio
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