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The design and cascade tests of free-streamline and full-contour 160 degrees turning supersonic-turbine-blade sections

Description: Report presenting a study of the flow characteristics of two supersonic-impulse-turbine-blade sections designed for a turning angle of 160 degrees. The primary difference between the two sections was the cutting away of a large portion of the convex surface and the presence of a free streamline as the boundary of flow in the passage. Results regarding the full-contour blade, free-streamline blade, and a comparison of the two are provided.
Date: August 16, 1957
Creator: Westphal, Willard R.
Partner: UNT Libraries Government Documents Department

Comparison of NACA 65-series compressor-blade pressure distributions and performance in a rotor and in cascade

Description: An investigation has been conducted to compare the performance of NACA 65-series compressor blades in two-dimensional cascade with that in an axial flow compressor. Blade pressure distributions were obtained by the use of a mercury-seal pressure-transfer device. The comparison indicated that cascade data accurately predicted the turning angle and blade pressure distribution obtained in the compressor at design conditions.
Date: March 1957
Creator: Westphal, Willard R. & Godwin, William R.
Partner: UNT Libraries Government Documents Department

Experimental investigation of a 90 degree cascade diffusing bend with an area ratio of 1.45:1 and with several inlet boundary layers

Description: Report presenting an experimental investigation in order to determine the performance of a 90 degree cascade diffusing bend with an area ratio of 1.45:1, a 19-by-19-inch inlet, and five inlet boundary layers varying in thickness and shape parameter. Tests were performed over a range of Mach and Reynolds numbers. Results regarding velocity distribution, performance, and some general considerations for this configuration are provided.
Date: April 1952
Creator: Friedman, Daniel & Westphal, Willard R.
Partner: UNT Libraries Government Documents Department

Design and investigation of a transonic axial-flow compressor rotor with an inlet hub-tip radius ratio of essentially zero

Description: Report presenting an investigation of an axial-flow compressor rotor with an inlet hub-tip radius ratio of basically zero. Results regarding the radial distribution of total-pressure ratio and efficiency, measured pressure ratio at design speed, weight flow, and low-speed cascade data are provided.
Date: March 11, 1957
Creator: Westphal, Willard R. & Maynard, John W., Jr.
Partner: UNT Libraries Government Documents Department

Application of the wire-mesh plotting device to incompressible cascade flows

Description: From Summary: "The methods used in the application of the wire-mesh plotting device to find the flow pattern about a cascade of airfoils in compressible inviscid flow and some mathematical checks that increase the accuracy of this application are described. Results for two typical turbine-blade cascades are shown to compare well with experimental data. A method of utilizing the wire mesh to design turbine blades with a prescribed pressure distribution in incompressible flow is presented."
Date: May 1950
Creator: Westphal, Willard R. & Dunavant, James C.
Partner: UNT Libraries Government Documents Department

High-Speed Cascade Tests of the NACA 65-(12A(sub 10))10 and NACA 65-(12A(sub 2)I(sub 8b))10 Compressor Blade Sections

Description: From Summary: "Two-dimensional porous-well cascade tests of the NACA 65- (l2Al0) 10 and NACA 65-(l2A2I8b)10 blade sections were made at Mach numbers from 0.3 to choking in most cases. Data were obtained at solidities of 1.0 and 1.5 at inlet-air angles of 45 deg. and 60 deg. for both blade sections. With a solid--wall modification to the cascade tunnel, schlieren observations were made of the flow in cascade at a solidity of 1.5 and inlet-air angle of 45 deg. and at a solidity of 1.0 and inlet-air angle of 60 deg."
Date: December 21, 1955
Creator: Dunavant, James C.; Emery, James C.; Walch, Howard C. & Westphal, Willard R.
Partner: UNT Libraries Government Documents Department