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  • 1
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    A model for closing the inviscid form of the average passage equation system (1996)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: A mathematical model for closing or mathematically completing the system of equations is proposed. The model describes the time average flow field through the blade passages of multistage turbomachinery. These average-passage equation systems govern a conceptual model useful in turbomachinery aerodynamic design and analysis. The closure model was developed to insure a consistency between these equations and the axisymmetric through-flow equations. The closure model was incorporated into a calculation code for use in the simulation of the flow field about a high-speed counter rotating propeller and a high-speed fan stage.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: Unsteady Flows in Turbomachines; Volume 2; VKI-LS-1996-05-Vol-2
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    The numerical simulation of multistage turbomachinery flows (1996)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: The effect of the unsteady flow field in a multistage compressor on the time-averaged performance was assessed. The energy transport by the unsteady deterministic flow field was taken into account. The magnitude of the body force resulting from the aerodynamic loading on a blade row was compared to the gradient of the stress tensor associated with the unsteady time-resolved flow field generated by the blade row. The magnitude of the work performed by these forces was compared to the divergence of the energy correlations produced by the unsteady time-resolved flow field. The stress tensor and the energy correlations are non-negligible in the end wall regions. The results suggest that the turbulence is the primary source of flow mixing in the midspan region.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: Unsteady Flows in Turbomachines; Volume 2; VKI-LS-1996-05-Vol-2
    Format: text
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  • 3
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    The numerical simulation of multistage turbomachinery flows (1990)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: The need to account for momentum and energy transport by the unsteady deterministic flow field in modeling the time-averaged flow state within a blade row passage embedded in a multistage compressor is assessed. It was found that, within the endwall regions, large-scale three-dimensional unsteady structures existed which caused significant transport of momentum and energy across the time-averaged stream surface of a stator flow field. These experiments confirmed that the tranport process is dominated by turbulent diffusion in the midspan region. A model was then proposed for simulating this transport process, and a limited study was undertaken to assess its validity.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD, Secondary Flows in Turbomachines; 13 p
    Format: text
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  • 4
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    Simulation of Multistage Turbine Flows (1985)
    In:  CASI
    Details
    Publication Date: 2014-08-27
    Description: The numerical simulation of turbine flows serves to enhance the understanding of the flow phenomena within multistage turbomachinery components. The direct benefit of this activity is improved modeling capability, which can be used to improve component efficiency and durability. A hierarchy of equations was formulated to assess the difficulty in analyzing the flow field within multistage turbomachinery components. The Navier-Stokes equations provides the most complete description. The simplest description is given by a set of equations that govern the quasi-one-dimensional flow. The number of unknowns to be solved for increases monotonically above the number of equations. The development of the additional set of equations needed to mathematically close the system of equations forms the closure problem associated with that level of description. For the Navier-Stokes equation there is no closure problem. For the quasi-one-dimensional equation set random flow fluctuations, unsteady fluctuations, nonaxisymmetric flow variations, and hub-to-shroud variations on the quasi-one-dimensional flow must be accounted for.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Struct. Integrity and Durability of Reusable Space Propulsion Systems; p 27-36
    Format: text
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  • 5
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    A model for closing the inviscid form of the average-passage equation system (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A mathematical model is proposed for closing or mathematically completing the system of equations which describes the time average flow field through the blade passages of multistage turbomachinery. These equations referred to as the average passage equation system govern a conceptual model which has proven useful in turbomachinery aerodynamic design and analysis. The closure model is developed so as to insure a consistency between these equations and the axisymmetric through flow equations. The closure model was incorporated into a computer code for use in simulating the flow field about a high speed counter rotating propeller and a high speed fan stage. Results from these simulations are presented.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 86-GT-227
    Format: text
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  • 6
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    Three-dimensional unsteady Euler solutions for propfans and counter-rotating propfans in transonic flow (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An Euler code designed for computing the unsteady, three-dimensional, transonic flow about single-rotating and counter-rotating propfans using dynamic blocked-grids is presented. The algorithm is a finite volume, flux-split, upwind, implicit scheme and solves the equations which have been written in a time-dependent curvilinear coordinate system. Relative motion of the blades for counter-rotating configurations is handled by requiring that grid lines be aligned after each discrete rotation of fore and aft rotor grid blocks. The method by which information is passed across block interfaces, as well as how downstream characteristic outflow boundary conditions which enforce simple radial equilibrium are implemented, is discussed. Comparisons of computed flow-field parameters and propfan performance with experimental data indicate good overall agreement between predictions and measurements.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-1197
    Format: text
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  • 7
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    A numerical simulation of the inviscid flow through a counter-rotating propeller (1986)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The results of a numerical simulation of the time-averaged inviscid flow field through the blade rows of a multiblade row turboprop configuration are presented. The governing equations are outlined along with a discussion of the solution procedure and coding strategy. Numerical results obtained from a simulation of the flow field through a modern high-speed turboprop will be shown.
    Keywords: AERODYNAMICS
    Type: NASA-TM-87200 , E-2855 , NAS 1.15:87200 , International Gas Turbine Conference; Jun 08, 1986 - Jun 12, 1986; Dusseldorf; Germany
    Format: application/pdf
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  • 8
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    A model for closing the inviscid form of the average-passage equation system (1985)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A mathematical model is proposed for closing or mathematically completing the system of equations which describes the time average flow field through the blade passages of multistage turbomachinery. These equations referred to as the average passage equation system govern a conceptual model which has proven useful in turbomachinery aerodynamic design and analysis. The closure model is developed so as to insure a consistency between these equations and the axisymmetric through flow equations. The closure model was incorporated into a computer code for use in simulating the flow field about a high speed counter rotating propeller and a high speed fan stage. Results from these simulations are presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-87199 , E-2854 , NAS 1.15:87199 , International Gas Turbine Conference; Jun 08, 1986 - Jun 12, 1986; Dusseldorf; Germany
    Format: application/pdf
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  • 9
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    A numerical simulation of the inviscid flow through a counterrotating propeller (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: The results of a numerical simulation of the time-averaged inviscid flow field through the blade rows of a multiblade row turboprop configuration are presented. The governing equations are outlined along with a discussion of the solution procedure and coding strategy. Numerical results obtained from a simulation of the flow field through a modern high-speed turboprop will be shown.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 86-GT-138 , ASME, Transactions, Journal of Turbomachinery (ISSN 0889-504X); 108; 187-193
    Format: text
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