Numerical Propulsion System Simulation's National Cycle Program

Evans, Austin L.; Follen, Gregory J.; Naiman, Cynthia; Lopez, Isaac

doi:10.2514/6.1998-3113

Cited by 28 publications

(12 citation statements)

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“…NPSS, ROCETS and REDTOP-2) require several thermophysical properties of a given propellant in order to perform conceptual vehicle designs. These properties include enthalpy, entropy, density, kinematic viscosity and thermal conductivity [8][9][10]. For most of the potential new HEDM propellants, this thermophysical data either does not exist or is incomplete over the range of temperature and pressure necessary for liquid rocket engine design and analysis.…”

Section: Introductionmentioning

confidence: 99%

Characterizing high-energy-density propellants for space propulsion applications

et al. 2009

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A technique for computationally determining the thermophysical properties of high-energy-density matter (HEDM) propellants is presented. HEDM compounds are of interest in the liquid rocket engine industry due to their high density and high energy content relative to existing industry-standard propellants. In order to accurately model rocket engine performance, cost and weight in a conceptual design environment, several thermodynamic and physical properties are required over a range of temperatures and pressures. The approach presented here combines quantum mechanical and molecular dynamic (MD) calculations and group additivity methods. A method for improving the force field model coefficients used in the MD is included. This approach is used to determine thermophysical properties for two HEDM compounds of interest: quadricyclane and 2-azido-N,N-dimethylethanamine (DMAZ). The modified force field approach provides results that more accurately match experimental data than the unmodified approach. Launch vehicle and Lunar lander case studies are presented to quantify the system level impact of employing quadricyclane and DMAZ rather than industry standard propellants. In both cases, the use of HEDM propellants provides reductions in vehicle mass compared to industry standard propellants. The results demonstrate that HEDM propellants can be an attractive technology for future launch vehicle and Lunar lander applications.

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Section: Introductionmentioning

confidence: 99%

Characterizing high-energy-density propellants for space propulsion applications

et al. 2009

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“…The booster consists of 3 stages (7 blade rows). A frame strut separates the booster and HPC, The full-turbofan engine simulation utilizes the NPSS thermodynamic cycle system modeling software described by Evans et al [11], along with toolkits developed for NPSS, to couple the high-fidelity 3D CFD software. NPSS is a component-based, object-oriented, engine cycle simulator designed to perform cycle design, steady state and transient offdesign performance prediction.…”

Section: Methodsmentioning

confidence: 99%

Multi-Fidelity Simulation of a Turbofan Engine With Results Zoomed Into Mini-Maps for a Zero-D Cycle Simulation

Turner

Reed²,

Ryder³

et al. 2004

Volume 2: Turbo Expo 2004

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A Zero-D cycle simulation of the GE90-94B high bypass turbofan engine has been achieved utilizing mini-maps generated from a high-fidelity simulation. The simulation utilizes the Numerical Propulsion System Simulation (NPSS) thermodynamic cycle modeling system coupled to a high-fidelity full-engine model represented by a set of coupled 3D computational fluid dynamic (CFD) component models. Boundary conditions from the balanced, steady-state cycle model are used to define component boundary conditions in the full-engine model. Operating characteristics of the 3D component models are integrated into the cycle model via partial performance maps generated from the CFD flow solutions using one-dimensional meanline turbomachinery programs. This paper high-lights the generation of the highpressure compressor, booster, and fan partial performance maps, as well as turbine maps for the high pressure and low pressure turbine. These are actually “mini-maps” in the sense that they are developed only for a narrow operating range of the component. Results are compared between actual cycle data at a take-off condition and the comparable condition utilizing these mini-maps. The mini-maps are also presented with comparison to actual component data where possible.

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“…For the TSTO vehicle class that IDEA is currently centered around, the keel line design from which the first stage is lofted comes from SRGULL. For turbine analysis, plans are in place to integrate IDEA with the Numerical Propulsion System Simulation (NPSS) tool from NASA Glenn 20 . NPSS has become an industry standard cycle analysis tool in the turbomachinery world and is currently in use by all of the major aircraft engine manufacturers.…”

Section: Idea Contents and Capabilitiesmentioning

confidence: 99%

An Overview of NASA'S Integrated Design and Engineering Analysis (IDEA) Environment

Robinson

2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Numerical Propulsion System Simulation's National Cycle Program

Cited by 28 publications

References 1 publication

Characterizing high-energy-density propellants for space propulsion applications

Characterizing high-energy-density propellants for space propulsion applications

Multi-Fidelity Simulation of a Turbofan Engine With Results Zoomed Into Mini-Maps for a Zero-D Cycle Simulation

An Overview of NASA'S Integrated Design and Engineering Analysis (IDEA) Environment

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