You are here

Multidisciplinary Optimization of Vane-type Heat Exchangers for Non-uniform Aircraft Inlets

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-22-C-0449
Agency Tracking Number: N22A-T002-0012
Amount: $139,957.00
Phase: Phase I
Program: STTR
Solicitation Topic Code: N22A-T002
Solicitation Number: 22.A
Solicitation Year: 2022
Award Year: 2022
Award Start Date (Proposal Award Date): 2022-07-11
Award End Date (Contract End Date): 2023-01-17
Small Business Information
34 Lexington Avenue
Ewing, NJ 08618-2302
United States
DUNS: 096857313
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Shahaboddin Alahyari Beig
 (609) 538-0444
Business Contact
 Melissa Kinney
Phone: (609) 538-0444
Research Institution
 The Pennsylvania State University
 John Hanold
112 Hammond Building
University Park, PA 16802-0000
United States

 (814) 863-5423
 Nonprofit College or University

To increase efficiency, reduce weight, and improve performance of next-generation aircraft, it is essential to design integrated systems that comprise multiple functionalities.  Modern propulsion systems integrate aircraft engines and air intake diffusers into the airframe to reduce drag.  However, such diffusers often introduce undesirable flow features such as flow separation and distortions, thus reducing the efficiency of propulsion systems.  Continuum Dynamics, Inc., The Pennsylvania State University, and Reaction Engines, Inc. propose to design a multifunctional heat exchanger device in the form of a guide vane cascade that can simultaneously extract swirl and flow distortions for improved engine performance and dissipate a large amount of aircraft waste heat.  This technology will allow for unobtrusive installation and retrofitting into existing engine intake diffusers (e.g., serpentine ducts).  Accordingly, the emphasis of Phase I effort will be on performing numerical simulations, multi-objective optimization processes, and preliminary experimental testing in a simplified flow environment at bench level to demonstrate the feasibility and practicality of the proposed heat exchanger technology.  Phase II will focus on finalizing the design, fabrication, and ground testing of the proposed device to further evaluate heat exchanger effectiveness, pressure loss, and distortion reduction for a representative inlet geometry under various operating conditions.

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

US Flag An Official Website of the United States Government