NDLI: Calculations of laminar heat transfer around cylinders of arbitrary cross section and transpiration-cooled walls with application to turbine blade cooling (Document No: 19930086734)

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Calculations of laminar heat transfer around cylinders of arbitrary cross section and transpiration-cooled walls with application to turbine blade cooling (Document No: 19930086734)

Content Provider	NASA Technical Reports Server (NTRS)
Copyright Year	1951
Description	An approximate method for development of flow and thermal boundary layers in laminar regime on cylinders with arbitrary cross section and transpiration-cooled walls is obtained by use of Karman's integrated momentum equation and an analogous heat-flow equation. Incompressible flow with constant property values throughout boundary layer is assumed. Shape parameters for approximated velocity and temperature profiles and functions necessary for solution of boundary-layer equations are presented as charts, reducing calculations to a minimum. The method is applied to determine local heat-transfer coefficients and surface temperature-cooled turbine blades for a given flow rate. Coolant flow distributions necessary for maintaining uniform blade temperatures are also determined.
File Size	6461305
Page Count	59
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19930086734
Archival Resource Key	ark:/13960/t53f93g5x
Language	English
Publisher Date	1951-09-24
Access Restriction	Open
Subject Keyword	Turbine Cooling Boundary Layer - Temperature Cooling - Gas Turbine Systems Heat Transfer Theory AND Experiment Heat Transfer, Aerodynamic Boundary Layer, Laminar - Calculations Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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