No description available.

Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1990. / Vita. Abstract. Includes bibliographical references (leaves 41-42). Also available via the Internet.

No description available.

Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1994. / Vita. Abstract. Includes bibliographical references (leaves 84-86). Also available via the Internet.

Not available / text

Thesis (Ph. D.)--University of Texas at Austin, 2005. / Supervisor: Oguzhan Bayrak. Vita. Includes bibliographical references.

A study was conducted to determine the effect of strut position on the aerodynamic and acoustic performance of a supersonic inlet. The investigated inlet was a prototype 1/14 scale model of a mixed compression, axisymmetric supersonic inlet designed for the high speed civil transport aircraft. A 10.4 cm (4.1 in.) turbofan engine simulator was used in conjunction with the inlet to provide the typical noise signature of a high bypass turbofan engine. Two inlet configurations were investigated in this study. The first configuration was the standard inlet design where the struts are located immediately upstream of the fan. The new configuration has the struts located 3.3 chord length upstream of the fan. The purpose for relocating the strut position was to reduce the flow distortion and radiated noise level. The experiment was conducted at various fan operating conditions in order to simulate aircraft approach. The inlet was tested statically without simulating the inflight speed effects. Steady state measurements were made in order to evaluate the aerodynamic performance of the inlet. The aerodynamic results show that the movement of the struts to a new location allowed the strut wake to diffuse significantly before reaching the fan. This reduced the circumferential distortion parameter by a factor of 2.4, without affecting the pressure recovery of the inlet at a fan Abstract speed of 30,000 rpm (40 PNC). Acoustic measurements were taken in the far field in the 0°-110°sector from the inlet axis. The new configuration of the inlet showed an improved acoustic performance over the standard design. Relocating the struts upstream reduced the blade passing tone by an average of 8 dB (0°-110°) sector, and the overall sound pressure level was lowered by an average of 2.6 dB at a fan speed of 30,000 rpm (40 PNC). / Master of Science

A study was undertaken to investigate the compressive capacity of a specific group of single angle members. A review of existing literature and techniques was presented. Laboratory compression tests were performed on 22 angle members of four different sizes and two different lengths. Additional tests were performed to determine the yield strength of the material. The results, normalized with respect to the yield stress, were tabulated and discussed. Two existing analytic models were used to attempt to predict the ultimate capacity of the test members. The first, an elastic method, was based upon the AISC combined stress equation. The second, an inelastic method, was developed by Mueller and Erzurumlu of Portland State University. Comparisons were made with the results of the test program. The results indicate that both analytic models give conservative predictions when pinned end conditions are assumed and unconservative results for fixed end conditions. For the test members with L/r ratios greater than 125, the elastic method results closely paralleled the test results but for the members with L/r ratios less than 125 the correlation was less consistent. The results of the inelastic technique closely paralleled the results of all the member tests.

Pressure signals were taken on a rotor blade surface of a single-stage, low-speed axial flow compressor. The data showed unsteady, stationary pressure perturbations that correlated with the locations of five large downstream support struts. In the present work, these data are thoroughly analysed. Strut-induced pressure amplitudes as measured on the rotor are presented as a function of the downstream strut locations. Unsteady lift and moment are calculated by integrating the pressures measured by the blade-mounted transducers. In addition, a sequence of instantaneous pressure distributions on the blade surfaces presented over time shows how the rotor is influenced by the potential effect of the struts. The strut is shown to produce a significant effect on rotor flow. This effect exceeds the unsteady stator effect at design rotor-stator-strut spacing, but falls off rapidly as the struts are moved downstream. / M.S.

Diaphragm braced strut-purlins are commonly used in the roof systems of metal buildings. However, the design problem of combined uplift and axial loads on these members is not adequately addressed in the 1989 AISI specification. The objective of this thesis is to provide experimental evidence that strut-purlins can be designed with an existing interaction equation. It was a/so the objective of this thesis to find a method of determining the axial capacity of diaphragm braced strut-purlins and to experimentally verify the accuracy of the method. / Master of Science