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  • Other Sources  (6)
  • 1985-1989  (6)
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  • Other Sources  (6)
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  • 1
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    Simulation of multistage turbine flows (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A flow model has been developed for analyzing multistage turbomachinery flows. This model, referred to as the average passage flow model, describes the time-averaged flow field with a typical passage of a blade row embedded within a multistage configuration. Computer resource requirements, supporting empirical modeling, formulation code development, and multitasking and storage are discussed. Illustrations from simulations of the space shuttle main engine (SSME) fuel turbine performed to date are given.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Structural Integrity and Durability of Reusable Space Propulsion Systems; p 13-20
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Utilization of parallel processing in solving the inviscid form of the average-passage equation system for multistage turbomachinery (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A procedure is outlined which utilizes parallel processing to solve the inviscid form of the average-passage equation system for multistage turbomachinery along with a description of its implementation in a FORTRAN computer code, MSTAGE. A scheme to reduce the central memory requirements of the program is also detailed. Both the multitasking and I/O routines referred to are specific to the Cray X-MP line of computers and its associated SSD (Solid-State Disk). Results are presented for a simulation of a two-stage rocket engine fuel pump turbine.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-89845 , E-3508 , NAS 1.15:89845
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Average-passage simulation of counter-rotating propfan propulsion systems as applied to cruise missiles (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Counter-rotating propfan (CRP) propulsion technologies are currently being evaluated as cruise missile propulsion systems. The aerodynamic integration concerns associated with this application are being addressed through the computational modeling of the missile body-propfan flowfield interactions. The work described in this paper consists of a detailed analysis of the aerodynamic interactions between the control surfaces and the propfan blades through the solution of the average-passage equation system. Two baseline configurations were studied, the control fins mounted forward of the counter-rotating propeller and the control fins mounted aft of the counter-rotating propeller. In both cases, control fin-propfan separation distance and control fin deflection angle were varied.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-2943
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    The utilization of parallel processing in solving the inviscid form of the average-passage equation system for multistage turbomachinery (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A procedure is outlined which utilizes parallel processing to solve the inviscid form of the average-passage equation system for multistage turbomachinery along with a description of its implementation in a FORTRAN computer code, MSTAGE. A scheme to reduce the central memory requirements of the program is also detailed. Both the multitasking and I/O routines referred to in this paper are specific to the Cray X-MP line of computers and its associated SSD (Solid-state Storage Device). Results are presented for a simulation of a two-stage rocket engine fuel pump turbine.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-1108
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    A multistage mesh generator for solving the average-passage equation system (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: One means of numerically simulating the 3-D flow field within a multistage turbomachine is through the solution of the average-passage equation system. One requirement of a current algorithm used to solve this system of equations has been the ability to generate multiple blade row meshes which satisfy specific geometrical constraints. In addition to meeting this criterion, one desires a mesh generation code which requires minimal user input, utilizes variable mesh control parameters, generates diagnostics helpful to the user, and possesses the capability to handle widely varying geometries. A mesh generation code with these features was written and has been used in solving the inviscid form of the average-passing equation system for both ducted and unducted multiple blade row geometries. This paper serves as a user reference guide, with a description of the mesh generation algorithm, a sample input file, and examples of typical meshes generated.
    Keywords: AERODYNAMICS
    Type: NASA-CR-179539 , E-3928 , NAS 1.26:179539
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Average-passage simulation of counter-rotating propfan propulsion systems as applied to cruise missiles (1989)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Counter-rotating propfan (CRP) propulsion technologies are currently being evaluated as cruise missile propulsion systems. The aerodynamic integration concerns associated with this application are being addressed through the computational modeling of the missile body-propfan flowfield interactions. The work described in this paper consists of a detailed analysis of the aerodynamic interactions between the control surfaces and the propfan blades through the solution of the average-passage equation system. Two baseline configurations were studied, the control fins mounted forward of the counter-rotating propeller and the control fins mounted aft of the counter-rotating propeller. In both cases, control fin-propfan separation distance and control fin deflection angle were varied.
    Keywords: AERODYNAMICS
    Type: NASA-TM-102043 , E-4791 , NAS 1.15:102043 , AIAA PAPER 89-2943 , Joint Propulsion Conference; Jul 10, 1989 - Jul 12, 1989; Monterey, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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