Gas Turbine Engine Exhaust Jet Shear-layer Pressure Measurement System

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-11-C-0466
Agency Tracking Number: N112-098-0714
Amount: $79,980.00
Phase: Phase I
Program: SBIR
Awards Year: 2011
Solicitation Year: 2011
Solicitation Topic Code: N112-098
Solicitation Number: 2011.2
Small Business Information
11995 El Camino Real, Suite 200, San Diego, CA, -
DUNS: 133709001
HUBZone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: N
Principal Investigator
 Parthiv Shah
 Senior Project Engineer
 (858) 480-2101
 parthiv.shah@ata-e.com
Business Contact
 Howard Matt
Title: Manager, Business Develop
Phone: (858) 480-2102
Email: howard.matt@ata-e.com
Research Institution
 Stub
Abstract
ATA Engineering proposes an SBIR program to design, develop, and demonstrate a jet shear-layer hydrodynamic pressure measurement system capable of detecting large-scale organized turbulence structures in full-scale military/commercial engine exhaust plumes. The ability to detect such structures at full-scale on an engine test stand is the necessary precursor to the ultimate goal of full-scale noise reduction through models that can be used for prediction and control of the spatio-temporal evolution of the jet shear-layer turbulence. ATA and its partners will leverage a breadth of expertise in the modeling of jet noise and the measurement, interpretation, and far-field projection of aeroacoustic noise sources using a high-resolution continuous-scan array technology developed under F-35 program SBIR funding and demonstrated at model-scale. Acquisition of fluctuating pressure data with a continuously moving array maximizes the efficiency of the data sampling in terms of sensor count, acquisition time (hence, engine run time), and measurement accuracy. The objective of the Phase I SBIR effort will be to determine the feasibility of the design of a near-field measurement system and propose a candidate mechanical and software design that can be built and demonstrated post-Phase I in an engine test stand environment.

* Information listed above is at the time of submission. *

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