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TBCC Inlet Experiments and Analysis.


N20080006598

Publication Date 2007
Personal Author Saunders, D.; Slater, J.; Dippold, V.; Lee, J.; Sanders, B.; Weir, L.
Page Count 29
Abstract A research plan is being implemented at NASA to investigate inlet mode transition for turbine-based combined-cycle (TBCC) propulsion for the hypersonic community. Unresolved issues have remained on how to design an inlet system to supply both a turbine engine and a ram/scramjet flowpath that operate with both high performance and stability. The current plan is aimed at characterizing the design, performance and operability of TBCC inlets through a series of experiments and analyses. A TBCC inlet has been designed that is capable of high performance (near MIL-E-5008B recovery) with smooth transitioning characteristics. Traditional design techniques were used in an innovative approach to balance the aerodynamic and mechanical constraints to create a new TBCC inlet concept. The inlet was designed for top-end Mach 7 scramjet speeds with an over/under turbine that becomes cocooned beyond its Mach 4 peak design point. Conceptually, this propulsion system was picked to meet the needs of the first stage of a two-stage to orbit vehicle. A series of increasing fidelity CFD-based tools are being used throughout this effort. A small-scale inlet experiment is on-going in the GRC 1'x1' Supersonic Wind Tunnel (SWT). Initial results from both the CFD analyses and test are discussed showing that high performance and smooth mode transitions are possible. The effort validates the design and is contributing to a large-scale inlet/propulsion test being planned for the GRC 10' x10' SWT. This large-scale effort provide the basis for a Combined Cycle Engine Testbed, (CCET), that will be able to address integrated propulsion system and controls objectives.
Keywords
  • Computational fluid dynamics
  • Turbine engines
  • Engine inlets
  • Wind tunnel tests
  • Supersonic wind tunnels
  • Supersonic combustion ramjet engines
  • Engine design
  • Systems integration
  • Inlet pressure
  • Spacecraft propulsion
  • Stability
  • Turbine-Based Combined-Cycle(TBCC) propulsion
Source Agency
  • National Aeronautics and Space Administration
Corporate Authors NASA Glenn Research Center.
Supplemental Notes Text in English. Presented at FAP Annual Review, New Orleans, LA, United States, 30 Oct. - 1 Nov. 2007. Publicly available Unlimited. CASI.
Document Type Conference Proceedings
NTIS Issue Number 200811
Contract Number
  • NAS3-03110
TBCC Inlet Experiments and Analysis.
TBCC Inlet Experiments and Analysis.
N20080006598

  • Computational fluid dynamics
  • Turbine engines
  • Engine inlets
  • Wind tunnel tests
  • Supersonic wind tunnels
  • Supersonic combustion ramjet engines
  • Engine design
  • Systems integration
  • Inlet pressure
  • Spacecraft propulsion
  • Stability
  • Turbine-Based Combined-Cycle(TBCC) propulsion
  • National Aeronautics and Space Administration
  • NAS3-03110
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