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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

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