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Thrust augmentation options for the Beta 2 two-stage-to-orbit vehicleNASA LeRC is continuing to study propulsion concepts for a horizontal takeoff and landing, fully reusable, two-stage-to-orbit vehicle. This will be capable of launching and returning a 10,000 pound payload to a 100 nautical mile polar orbit using low-risk technology. The vehicle, Beta 2, is a derivative of the USAF/Boeing Beta vehicle which was designed to deliver a 50,000 pound payload to a similar orbit. Beta 2 stages at Mach 6.5 and about 100,000 ft altitude. The propulsion system for the booster is an over/under turbine bypass engine/ramjet configuration. In this paper, several options for thrust augmentation were studied in order to improve the performance of this engine where there was a critical need. Options studies were turbine engine overspeed in the transonic region, water injection at a various turbine engine locations also during the transonic region, and water injection at the turbine engine face during high speed operation. The methodology, constraints, propulsion performance, and mission study results are presented.
Document ID
19940017090
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Snyder, Christopher A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1993
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-8301
AIAA PAPER 93-4014
NASA-TM-106448
NAS 1.15:106448
Meeting Information
Meeting: AIAA Aircraft Design, Systems and Operations Meeting
Location: Monterey, CA
Country: United States
Start Date: August 11, 1993
End Date: August 13, 1993
Sponsors: AIAA
Accession Number
94N21563
Funding Number(s)
PROJECT: RTOP 505-70-00
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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