Development of Axial Compressor Heat-Extraction Capability for Thermal Management Applications

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$99,800.00
Award Year:
2011
Program:
SBIR
Phase:
Phase I
Contract:
NNX11CD92P
Award Id:
n/a
Agency Tracking Number:
105737
Solicitation Year:
2010
Solicitation Topic Code:
A2.10
Solicitation Number:
n/a
Small Business Information
11995 El Camino Real, Suite 200, San Diego, CA, -
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
Y
Duns:
133709001
Principal Investigator:
Parthiv Shah
Principal Investigator
(858) 480-2101
parthiv.shah@ata-e.com
Business Contact:
Ronan Cunningham
Director, Business Development
(858) 480-2015
ronan.cunningham@ata-e.com
Research Institute:
Stub




Abstract
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.

* information listed above is at the time of submission.

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