High Suction Specific Speed Inducers for Cryogenic Upper Stage Engines

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: F04611-03-C-0027
Agency Tracking Number: 021PRO-1949
Amount: $749,827.00
Phase: Phase II
Program: SBIR
Awards Year: 2003
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
217 Billings Farm Road, White River Jct, VT, 05001
DUNS: 024355802
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Kerry Oliphant
 Principal Investigator
 (802) 296-2321
 kno@conceptsnrec.com
Business Contact
 Harold Keiling
Title: Sr. Vice President
Phone: (802) 296-2321
Email: hak@conceptsnrec.com
Research Institution
N/A
Abstract
There is a significant opportunity to meet higher upper stage engine performance levels by combining a much higher chamber pressure expander cycle engine with advanced technology turbomachinery. The Phase II SBIR goal is to provide a solid foundation foran upper stage engine design focused on IHPRPT goals. Three main Phase II technical objectives must be met to achieve this goal: 1) finalize the cycle configuration and the advanced thrust chamber design, 2) design and rig test a high suction specificspeed fuel pump and then use same methodology to design the oxidizer pump, 3) initiate the design of the other main flow path turbo machinery components, which includes the turbine stages. The Phase I work demonstrated the feasibility of a high chamberpressure expander cycle upper-stage engine to minimize total engine weight. In addition, advanced suction performance pumping technology developed by the proposer will be applied to minimize inlet pressure requirements while avoiding system instabilities,such as rotating cavitation and auto oscillation, without the need for boost pumps. This yields maximum possible rotational speed and performance while minimizing turbopump weight.

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

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