Investigation of Advanced Counterrotation Blade Configuration Concepts for High Speed Turboprop Systems, Task 1 PDF Download
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723185854
Category :
Languages : en
Pages : 156
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Book Description
The time-dependent three-dimensional Euler equations of gas dynamics were solved numerically to study the steady compressible transonic flow about ducted propfan propulsion systems. Aerodynamic calculations were based on a four-stage Runge-Kutta time-marching finite volume solution technique with added numerical dissipation. An implicit residual smoothing operator was used to aid convergence. Two calculation grids were employed in this study. The first grid utilized an H-type mesh network with a branch cut opening to represent the axisymmetric cowl. The second grid utilized a multiple-block mesh system with a C-type grid about the cowl. The individual blocks were numerically coupled in the Euler solver. Grid systems were generated by a combined algebraic/elliptic algortihm developed specifically for ducted propfans. Numerical calculations were initially performed for unducted propfans to verify the accuracy of the three-dimensional Euler formulation. The Euler analyses were then applied for the calculation of ducted propfan flows, and predicted results were compared with experimental data for two cases. The three-dimensional Euler analyses displayed exceptional accuracy, although certain parameters were observed to be very sensitive to geometric deflections. Both solution schemes were found to be very robust and demonstrated nearly equal efficiency and accuracy, although it was observed that the multi-block C-grid formulation provided somewhat better resolution of the cowl leading edge region. Hall, Edward J. and Delaney, Robert A. and Bettner, James L. Unspecified Center COMPRESSIBLE FLOW; COMPUTATIONAL FLUID DYNAMICS; CONTRAROTATING PROPELLERS; EULER EQUATIONS OF MOTION; FLOW DISTRIBUTION; FLOW EQUATIONS; PROP-FAN TECHNOLOGY; PROPELLER FANS; THREE DIMENSIONAL FLOW; TRANSONIC FLOW; CONVERGENCE; GRID GENERATION (MATHEMATICS); LEADING EDGES; RUNGE-KUTTA METHOD; TIME MARCHING...
Author: Edward J. Hall
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 354
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Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723185854
Category :
Languages : en
Pages : 156
Get Book Here
Book Description
The time-dependent three-dimensional Euler equations of gas dynamics were solved numerically to study the steady compressible transonic flow about ducted propfan propulsion systems. Aerodynamic calculations were based on a four-stage Runge-Kutta time-marching finite volume solution technique with added numerical dissipation. An implicit residual smoothing operator was used to aid convergence. Two calculation grids were employed in this study. The first grid utilized an H-type mesh network with a branch cut opening to represent the axisymmetric cowl. The second grid utilized a multiple-block mesh system with a C-type grid about the cowl. The individual blocks were numerically coupled in the Euler solver. Grid systems were generated by a combined algebraic/elliptic algortihm developed specifically for ducted propfans. Numerical calculations were initially performed for unducted propfans to verify the accuracy of the three-dimensional Euler formulation. The Euler analyses were then applied for the calculation of ducted propfan flows, and predicted results were compared with experimental data for two cases. The three-dimensional Euler analyses displayed exceptional accuracy, although certain parameters were observed to be very sensitive to geometric deflections. Both solution schemes were found to be very robust and demonstrated nearly equal efficiency and accuracy, although it was observed that the multi-block C-grid formulation provided somewhat better resolution of the cowl leading edge region. Hall, Edward J. and Delaney, Robert A. and Bettner, James L. Unspecified Center COMPRESSIBLE FLOW; COMPUTATIONAL FLUID DYNAMICS; CONTRAROTATING PROPELLERS; EULER EQUATIONS OF MOTION; FLOW DISTRIBUTION; FLOW EQUATIONS; PROP-FAN TECHNOLOGY; PROPELLER FANS; THREE DIMENSIONAL FLOW; TRANSONIC FLOW; CONVERGENCE; GRID GENERATION (MATHEMATICS); LEADING EDGES; RUNGE-KUTTA METHOD; TIME MARCHING...
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723186257
Category :
Languages : en
Pages : 112
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Book Description
A procedure is studied for generating three-dimensional grids for advanced turbofan engine fan section geometries. The procedure constructs a discrete mesh about engine sections containing the fan stage, an arbitrary number of axisymmetric radial flow splitters, a booster stage, and a bifurcated core/bypass flow duct with guide vanes. The mesh is an h-type grid system, the points being distributed with a transfinite interpolation scheme with axial and radial spacing being user specified. Elliptic smoothing of the grid in the meridional plane is a post-process option. The grid generation scheme is consistent with aerodynamic analyses utilizing the average-passage equation system developed by Dr. John Adamczyk of NASA Lewis. This flow solution scheme requires a series of blade specific grids each having a common axisymmetric mesh, but varying in the circumferential direction according to the geometry of the specific blade row. Crook, Andrew J. and Delaney, Robert A. Unspecified Center COMPUTATIONAL GRIDS; COMPUTERIZED SIMULATION; COUNTER ROTATION; GRID GENERATION (MATHEMATICS); PROPULSION SYSTEM CONFIGURATIONS; TURBOFAN ENGINES; USER MANUALS (COMPUTER PROGRAMS); ALGORITHMS; APPLICATIONS PROGRAMS (COMPUTERS); COMPUTATIONAL FLUID DYNAMICS; COMPUTER AIDED DESIGN; FLOW DISTRIBUTION; PROPELLER BLADES; TURBOPROP ENGINES...
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 80
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 368
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Author:
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ISBN:
Category :
Languages : en
Pages : 126
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Author:
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ISBN:
Category :
Languages : en
Pages : 88
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Author:
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ISBN:
Category :
Languages : en
Pages : 206
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781724264725
Category :
Languages : en
Pages : 218
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The primary objective of this study was the development of a time-marching three-dimensional Euler/Navier-Stokes aerodynamic analysis to predict steady and unsteady compressible transonic flows about ducted and unducted propfan propulsion systems employing multiple blade rows. The computer codes resulting from this study are referred to as ADPAC-AOACR (Advanced Ducted Propfan Analysis Codes-Angle of Attack Coupled Row). This report is intended to serve as a computer program user's manual for the ADPAC-AOACR codes developed under Task 5 of NASA Contract NAS3-25270, Unsteady Counterrotating Ducted Propfan Analysis. The ADPAC-AOACR program is based on a flexible multiple blocked grid discretization scheme permitting coupled 2-D/3-D mesh block solutions with application to a wide variety of geometries. For convenience, several standard mesh block structures are described for turbomachinery applications. Aerodynamic calculations are based on a four-stage Runge-Kutta time-marching finite volume solution technique with added numerical dissipation. Steady flow predictions are accelerated by a multigrid procedure. Numerical calculations are compared with experimental data for several test cases to demonstrate the utility of this approach for predicting the aerodynamics of modern turbomachinery configurations employing multiple blade rows. Hall, Edward J. and Delaney, Robert A. and Adamczyk, John J. and Miller, Christopher J. and Arnone, Andrea and Swanson, Charles Unspecified Center NASA-CR-187125, NAS 1.26:187125 NAS3-25270; RTOP 535-03-10...
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781724265432
Category :
Languages : en
Pages : 202
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The focus of this task was to validate the ADPAC code for heat transfer calculations. To accomplish this goal, the ADPAC code was modified to allow for a Cartesian coordinate system capability and to add boundary conditions to handle spanwise periodicity and transpiration boundaries. The primary validation case was the film cooled C3X vane. The cooling hole modeling included both a porous region and grid in each discrete hold. Predictions for these models as well as smooth wall compared well with the experimental data. Hall, Edward J. and Topp, David A. and Heidegger, Nathan J. and Delaney, Robert A. Unspecified Center NASA-CR-195359, E-9024, NAS 1.26:195359 NAS3-25270; RTOP 538-03-11...
