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Highlights from a Mach 4 Experimental Demonstration of Inlet Mode Transition for Turbine-Based Combined Cycle Hypersonic PropulsionNASA is focused on technologies for combined cycle, air-breathing propulsion systems to enable reusable launch systems for access to space. Turbine Based Combined Cycle (TBCC) propulsion systems offer specific impulse (Isp) improvements over rocket-based propulsion systems in the subsonic takeoff and return mission segments along with improved safety. Among the most critical TBCC enabling technologies are: 1) mode transition from the low speed propulsion system to the high speed propulsion system, 2) high Mach turbine engine development and 3) innovative turbine based combined cycle integration. To address these challenges, NASA initiated an experimental mode transition task including analytical methods to assess the state-of-the-art of propulsion system performance and design codes. One effort has been the Combined-Cycle Engine Large Scale Inlet Mode Transition Experiment (CCE-LIMX) which is a fully integrated TBCC propulsion system with flowpath sizing consistent with previous NASA and DoD proposed Hypersonic experimental flight test plans. This experiment was tested in the NASA GRC 10 by 10-Foot Supersonic Wind Tunnel (SWT) Facility. The goal of this activity is to address key hypersonic combined-cycle engine issues including: (1) dual integrated inlet operability and performance issues-unstart constraints, distortion constraints, bleed requirements, and controls, (2) mode-transition sequence elements caused by switching between the turbine and the ramjet/scramjet flowpaths (imposed variable geometry requirements), and (3) turbine engine transients (and associated time scales) during transition. Testing of the initial inlet and dynamic characterization phases were completed and smooth mode transition was demonstrated. A database focused on a Mach 4 transition speed with limited off-design elements was developed and will serve to guide future TBCC system studies and to validate higher level analyses.
Document ID
20130003353
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Foster, Lancert E. (NASA Glenn Research Center Cleveland, OH, United States)
Saunders, John D., Jr. (NASA Glenn Research Center Cleveland, OH, United States)
Sanders, Bobby W. (TechLand Research, Inc. North Olmstead, OH, United States)
Weir, Lois J. (TechLand Research, Inc. North Olmstead, OH, United States)
Date Acquired
August 27, 2013
Publication Date
December 1, 2012
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA/TM-2012-217724
E-18435
Meeting Information
Meeting: 48th Joint Propulsion Conference and Exhibit
Location: Atlanta, GA
Country: United States
Start Date: July 30, 2012
End Date: August 1, 2012
Sponsors: Society of Automotive Engineers, Inc., American Society of Mechanical Engineers, American Society for Electrical Engineers, American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 599489.02.07.03.07.11.01
CONTRACT_GRANT: NNC08CA60C
Distribution Limits
Public
Copyright
Public Use Permitted.

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