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Analysis of laminar incompressible flow on semiporous channels

Description: From Introduction: "Experimental results for flow in a rectangular channel with injection through a porous wall are given in reference 1. As part of the study to guide future experiments, laminar flow in a semiporous channel is investigated herein. In the present investigation, a third-order perturbation solution for laminar incompressible flow in a semiporous channel is presented."
Date: August 1, 1956
Creator: Donoughe, Patrick L
Partner: UNT Libraries Government Documents Department

Flow Coefficients for Orifices in Base of Transpiration-Cooled Turbine Rotor Blade

Description: Static tests on a segment of a transpiration-cooled turbine rotor blade with a wire-cloth shell were conducted to determine the flow coefficients associated with some representative metering orifices. Average flow coefficients from 0.96 to 0.79 were obtained for orifices of 0.031 to 0.102 inch diameter.
Date: December 11, 1953
Creator: Donoughe, Patrick L. & Prasse, Ernst I.
Partner: UNT Libraries Government Documents Department

Analysis of coolant flow and pressure requirements for a return-flow turbine rotor blade design using hydrogen, helium, or air as coolant

Description: From Introduction: "This report presents the results of an analysis to determine the coolant flow and pressure requirements for a particular return-flow turbine rooter blade design utilizing hydrogen, helium, or air as the coolant."
Date: May 7, 1957
Creator: Slone, Henry O & Donoughe, Patrick L
Partner: UNT Libraries Government Documents Department

Exploratory engine test of transpiration-cooled turbine-rotor blade with wire-cloth shell

Description: Engine tests were made on a transpiration-cooled blade that was fabricated from an internal load-carrying member with an external surface of wire cloth. After operation in the engine, some damage was noted at the tip region of the trailing edge of the blades. On other sections of the blade, the wire cloth did not appear greatly overheated, and it appeared that satisfactory chordwise temperature distribution was provided by orifices in the blade base.
Date: January 1, 1954
Creator: Donoughe, Patrick L & Diaguila, Anthony J
Partner: UNT Libraries Government Documents Department

Pressure distributions about finite wedges in bounded and unbounded subsonic streams

Description: An analytical investigation of incompressible flow about wedges was made to determine effects of tunnel-wedge ratio and wedge angle on the wedge pressure distributions. The region of applicability of infinite wedge-type velocity distribution was examined for finite wedges. Theoretical and experimental pressure coefficients for various tunnel-wedge ratios, wedge angles, and subsonic Mach numbers were compared.
Date: May 1, 1953
Creator: Donoughe, Patrick L & Prasse, Ernst I
Partner: UNT Libraries Government Documents Department

Extension of boundary-layer heat-transfer theory to cooled turbine blades

Description: An equation for average heat transfer of a surface was derived when the boundary layer changed from laminar to turbulent. Influences on the heat transfer through a laminar boundary layer of Mach number, temperature ratio (gas temperature divided by wall temperature), and exponents of gas-property temperature relations were shown to be relatively small for air with Mach numbers less than 2 and temperature ratios between 1 and 4. Good agreement was obtained with experimental results from cylinders, an airfoil, and turbine blades.
Date: August 11, 1950
Creator: Brown, W Byron & Donoughe, Patrick L
Partner: UNT Libraries Government Documents Department

Exact solutions of laminar-boundary-layer equations with constant property values for porous wall with variable temperature

Description: Exact solution of the laminar-boundary-layer equations for wedge-type flow with constant property values are presented for transpiration-cooled surfaces with variable wall temperatures. The difference between wall and stream temperature is assumed proportional to a power of the distance from the leading edge. Solutions are given for a Prandtl number of 0.7 and ranges of pressure-gradient, cooling-air-flow, and wall-temperature-gradient parameters. Boundary-layer profiles, dimensionless boundary-layer thicknesses, and convective heat-transfer coefficients are given in both tabular and graphical form. Corresponding results for constant wall temperature and for impermeable surfaces are included for comparison purposes.
Date: January 1, 1955
Creator: Donoughe, Patrick L & Livingood, John N B
Partner: UNT Libraries Government Documents Department