Cascade testing and flow analysis of three high-turning supercritical compressor blades were conducted. The blades were designed at an inlet Mach number (M1) of 0.87 and inlet flow angle of 48.4 deg, with high camber angles of about 55 deg. The baseline blade was a conventional Controlled Diffusion Airfoil (CDA) design and the other two were optimized blades. The blades were tested for an inlet Mach number range from 0.61 to 0.95 and an inlet flow angle range from 44.4 deg to 50.4 deg, at high Reynolds numbers (1.2-1.9x10^6 based on the blade chord). The test results have shown lower losses and better incidence robustness for the optimized blades at higher supercritical flow conditions (M1>0.83). At the design condition, 30% loss reduction was achieved. The blade-to-blade flow was computed by solving the two-dimensional steady Navier-Stokes equations. Experimental results, in conjunction with the CFD flowfield characterization, revealed the loss reduction mechanism: severe boundary layer separation occurred on the suction surface of the baseline blade while no separation occurred for the optimized blades. Furthermore, whether the boundary layer was separated or not was found due to different shock patterns, different shock-boundary layer interactions and different pressure distributions on the blades. For the baseline blade, the strong passage shock coincided with the adverse pressure gradient due to the high blade front camber at 20% chord, leading to the flow separation. For the optimized blades, the high blade camber shifted to more downstream (30-40% chord), resulting in stronger flow leading edge acceleration, less strength of the passage shock near the blade surface, favorable pressure gradient right after the passage shock, thus no flow separation occurred. The flow understanding obtained by the current research can be used to guide the design of high-turning compressor blades at higher supercritical flow conditions. / Ph. D.

A stator cascade was developed to simulate the flow conditions within a close-stage-spacing transonic axial compressor. Experiments were conducted in a linear transonic blowdown cascade wind tunnel with an inlet Mach number of 0.65. The bow shock from the downstream rotor was simulated by a single moving normal shock generated with a shock tube. First, steady pressure data were gathered to ensure that the stator cascade operated properly without the presence of the shock. Next, the effects of the passing shock on the stator flow field were investigated using shadowgraph photography and Digital Particle Image Velocimetry (DPIV). Measurements were taken for three different shock strengths. In every case studied, a vortex formed near the stator trailing edge as the shock impacted the blade. The size of this vortex was shown to be directly related to the shock strength, and the vortex remained present in the trailing edge flow field throughout the cycle duration. Analysis of the DPIV data showed that the vortex acts as a flow blockage, with the extent of this blockage ranging from 2.9% of the passage for the weakest shock, to 14.3% of the passage for the strongest shock. The vortex was also shown to cause flow deviation up to 75° for the case with the strongest shock. Further analysis estimated that the total pressure losses due to shock-induced vorticity ranged from 46% to 113% of the steady wake losses. Finally, the total pressure loss purely due to the upstream-propagating normal shock was estimated to be roughly 0.22%. / Master of Science

A high-turning compressor stator with a unique flow control design was developed and tested. Both boundary layer suction and trailing edge blowing developed from a single supplied motive pressure source are employed on the stator. Massflow removed through boundary layer suction is added to the motive massflow, and the resulting combined flow is used for trailing edge blowing to reduce the total pressure deficit generated by the stator wake. The effectiveness of the flow control design was investigated experimentally by measuring the reduction in the total pressure loss coefficient. The experiment was conducted in a linear transonic blowdown cascade wind tunnel. The inlet Mach number for all tests was 0.79, with a Reynolds number based on stator chordlength of 2,000,000. A range of inlet cascade angles was tested to identify the useful range of the flow control design. The effect of different supply massflows represented as a percentage of the passage throughflow was also documented. Significant reductions in the total pressure loss coefficient were accomplished with flow control at low cascade angles. A maximum reduction of 65% in the baseline (no flow control) loss coefficient was achieved by using a motive massflow of 1.6% of the passage throughflow, at cascade angle of 0°. The corresponding suction and blowing massflow ratio was approximately 1:3.6. Cascade angle results near 0° showed significant reductions in the loss coefficient, while increases in the cascade angle diminished the effects of flow control. Considerable suction side separation and the presence of a leading edge shock are noticeable as the cascade angle is increased, and contribute to the losses across the stator surface. Also identified was the estimated increase in wake turning due to flow control of up to 4.5°. / Master of Science

The objective of a coating operation is to transfer a defect free liquid film onto a continuous substrate in order to meet the requirements of the final products. Mainly two concerns govern the process. The first concern is the economics of the process and the second concern is the quality of the coated film. The economics of the process are dictated by the speed of coating and the film thickness. Clearly, higher speeds mean better productivity hence less cost of operation and thinner films are desirable because less material is being used. Quality is governed by film uniformity and integrity, indicating that the film will perform as designed. Film defects such as streaks or tiny air bubbles are indication that the film properties are not uniform rendering it unacceptable to customers. One of the most versatile coating systems to achieve thin films at high speeds is reverse roll coating which has been used for a long time all over the world. At low speed, typically 1m/s, this coating operation is inherently stable and with small gaps of order 100 microns can ii lead to film thickness of order 30-50 microns. Much research, theoretical and experimental, has been devoted to this coating flow but only at low speeds and for large gaps (>100 microns). There are no comprehensive data how very thin films, 20 microns and less (particularly lower limits in the region of 5 microns) can be achieved at high speeds, of 2 or more metres per second. This study is concerned precisely with this aim, that of investigating the effect of large speeds and small roller gaps (rollers nearly touching or in elastohydrodynamic contact) to achieve the very thin films desired by modern applications (electronics, medical and others). In order to achieve this aim, a rig was designed and built to enable to understand the effect of various coating conditions and liquid properties on the metered film thickness and coating instability. To achieve thin films at high speeds, small roll gap and low viscosity are needed, however flow instabilities will develop under these conditions. To achieve stable coating window at high speeds high surface tension is needed. It was found that the roll gap and the viscosity have complicated effect on the coating window. In the case of low viscosity liquid (7mPa.s), small roll gaps are needed, whereas in the case of high viscosity liquid (more than 30mPa.s), large gaps are needed. It was found that Weber number is better describer for ribbing instability in rigid reverse roll coating unlike in rigid forward roll coating in which capillary number is the one. In addition the potential of reverse deformable roll coating (rolls in elastohydrodynamic contact) was investigated in order to achieve much thinner films at higher speeds. As a result of the investigation of reverse deformable roll coating, it was found that there is a possibility to get much thinner stable films at much higher speeds compared to reverse rigid roll coating. The liquid transfer from an applicator roller to a PET film was investigated in this study. It was found that air stagnation at downstream meniscus and air entrainment at upstream meniscus depend on the liquid properties such as viscosity and surface tension and coating conditions such as web tension and wrap angle of web. As a result, wet film instability also depends on liquid properties and coating conditions. It was found that air stagnation causes streaks on the wet film and air entrainment caused bubbles on the wet film. To get a stable wet film, it was found that suitable viscosity and high surface tension were needed. / TOYOBO

This thesis presents the results of a study performed in the Virginia Tech low speed linear cascade wind tunnel operating at a Reynolds number of 382,000 designed to model an axial compressor rotor. To simulate the flow created by the junction of a set of inlet guide vanes and the compressor casing, vortex generators were glued to a moving end wall. In this investigation, the tip clearance was varied from 0.83% to 12.9% chord. Measurements of the midspan and the tip blade loading were made using static pressure taps. The tip loading shows that the minimum suction surface pressure coefficient increases in magnitude linearly up to a tip clearance of 7.9% chord. Unsteady pressure was measured on the pressure and suction surfaces at the tip of two cascade blades using an array of 23 microphones mounted subsurface. These measurements reveal that the unsteady pressure at the blade tip is a linear function of tip clearance height. The instantaneous pressure shows that the surface pressure at the blade tip has the same character regardless of whether or not the blade is disturbed by the inflow vortices. This suggests that the vortex generators simply stimulate and organize the existing response of the blade. Single sensor hot-wire measurements were made within the tip clearance on the suction side of the blade 1mm from the tip gap exit. These measurements show that the mass flux through the tip clearance is closely related to the pressure difference across the tip gap. / Master of Science

Thesis advisor: X. Peter Zhang / Thesis advisor: James P. Morken / Chapter 1. Stereoselective Cyclopropanation of Alkenes with Alkynyl- and Vinyl-Substituted Diazo Compounds Alkynyl- and vinyl-substituted cyclopropanes are ubiquitous structural motifs in drug molecules and bioactive compounds. In addition, alkynyl- and vinyl-substituted cyclopropanes may serve as useful intermediates for stereoselective organic synthesis. Metal-catalyzed cyclopropanation of alkenes with alkynyl- and vinyl-substituted diazo compounds offers a potentially general approach for stereoselective construction of these valuable three-membered ring structures. This chapter summarizes the development of stereoselective olefin cyclopropanation with alkynyl- and vinyl-substituted diazo compounds. Chapter 2. Metalloradical Activation of In Situ-Generated α-Alkynyldiazomethanes for Asymmetric Radical Cyclopropanation of Alkenes We have developed a Co(II)-based metalloradical system that is highly effective for asymmetric radical cyclopropanation of alkenes with in situ-generated α-alkynyldiazomethanes. Through fine-tuning the cavity-like environments of D₂-symmetric chiral amidoporphyrins as the supporting ligand, the optimized Co(II)-based metalloradical system is broadly applicable to different alkynyldiazomethanes for asymmetric cyclopropanation of a broad range of alkenes, providing general access to valuable chiral alkynyl cyclopropanes in high yields with excellent diastereoselectivities and enantioselectivities. Chapter 3. Asymmetric Radical Process for Cyclopropanation of Alkenes with In Situ-Generated α-Vinyldiazomethanes We have demonstrated the feasibility of using vinyl aldehyde-derived sulfonylhydrazones as new metalloradicophiles for the generation of allylic radicals. Through fine-tuning the cavity-like environments of D₂-symmetric chiral amidoporphyrins as supporting ligands, the key α-Co(III)-allylic radical intermediates are exclusively engaged in the highly asymmetric cyclopropanation with wide-ranging alkenes in the optimized Co(II)-based metalloradical system, as shown broadly applicable to activate different α-vinyldiazomethanes. Chapter 4. Asymmetric Synthesis of Vinyl-Substituted Cyclopropanes by Radical C-H Alkylation from Alkynes and In Situ-Generated Alkyldiazomethanes via Co(II)-Based Metalloradical Catalysis We have successfully expanded the application of Co(II)-based MRC by applying in-situ generated alkyldiazomethanes as new radical precursors for stereoselective synthesis of vinyl-substituted cyclopropanes by radical cascade C-H alkylation of alkynes. Through fine-tuning of D₂-symmetric chiral amidoporphyrins as the supporting ligands, the Co(II)-catalyzed radical cascade process, which proceeds in a single operation under mild conditions, enables asymmetric construction of vinyl-substituted cyclopropanes in high yields with excellent diastereoselectivities and good enantioselectivities. / Thesis (PhD) — Boston College, 2022. / Submitted to: Boston College. Graduate School of Arts and Sciences. / Discipline: Chemistry.

Non-suicidal self-injury (NSSI), the deliberate and direct damage of one’s body tissue without suicidal intent, is a pervasive public health concern often leading to clinically significant long-term consequences (e.g., permanent scarring, hospitalization) that is theorized to be facilitated by negative affect and emotion dysregulation. The Emotional Cascade Model proposes that NSSI partially functions to disrupt the reciprocal and rapid amplification of negative affect driven by rumination. However, limited research has focused on state rumination and the distinct contribution of maladaptive and adaptive rumination subtypes, as well as the role of positive affect within this framework. Thus, the purpose of the current study was to replicate and explore the independent influences of overall and momentary (1) positive and negative affect and (2) rumination on NSSI acts and urges, as well as (3) the extent to which rumination moderates the relationship between affect and NSSI. To do so, rumination, affect, and NSSI urges and acts were assessed 4 times daily via ecological momentary assessment for 21-days among thirty undergraduate participants with past month NSSI. Our results partially replicated existing literature, such that overall negative affect was associated with greater overall NSSI urge strength and momentary negative affect and rumination predicted stronger NSSI urges at the next alert, with increased momentary rumination strengthening the relationship between momentary negative affect and NSSI urge. Exploratory investigations of overall and momentary positive affect showed some negative associations with NSSI urges and behaviors, with no moderating effect of rumination. Data did not support the independent examination of maladaptive and adaptive rumination subtypes. Taken together, this study highlighted the importance of exploring state rumination (in addition to trait) and affect in understanding NSSI thoughts and behaviors, and calls for future studies to further investigate distinct properties of rumination to understand its impact on specific emotions that maintain NSSI engagement. / Psychology

Borderline personality disorder (BPD) is an impairing mental illness and has a core component of emotional dysregulation. Evidence suggests the emotional cascade model describes how this emotional dysregulation leads to engaging in risky and life-threatening behaviors, such as non-suicidal self-injury (NSSI). Specifically, this model describes rumination as a cognitive component that links the emotional and behavioral dysregulation. The current study aimed to expand the model by investigating how individuals with heightened BPD traits engage in NSSI and in cognitive strategies to cope with their negative affect. Specifically, it was investigated whether behaviors like suicide attempts and cognitions differentiated between those with mild/moderate and severe NSSI. Criterion for severe NSSI was hospitalization or medical care because of NSSI. Participants (N = 292) were screened to endorse a history of NSSI and then self-selected to take a self-report survey through Mturk. Correlations and a binomial logistic regression were completed. Results indicated suicide attempts, BPD symptoms, and anger rumination differentiated mild/moderate and severe NSSI. Evidence reinforces the strong relationships between NSSI, suicide attempts, and BPD. Additionally, it reinforces anger rumination as a potential cognitive mechanism in NSSI. Future research can continue to test this model and include other potential thought processes to increase efficiency in assessment and treatment of BPD and NSSI.

京都大学 / 新制・課程博士 / 博士(エネルギー科学) / 甲第25399号 / エネ博第478号 / 新制||エネ||89(附属図書館) / 京都大学大学院エネルギー科学研究科エネルギー基礎科学専攻 / (主査)教授 森井 孝, 教授 片平 正人, 教授 佐川 尚 / 学位規則第4条第1項該当 / Doctor of Energy Science / Kyoto University / DGAM

The instability modes and non-linear behavior of a cavitating flow have been studied based on the experimental data obtained from planar Particle Image Velocimetry (PIV). Three data-driven techniques, Proper Orthogonal Decomposition (POD), Dynamic Mode Decomposition (DMD), and Clustered-based Reduced Order Modeling (CROM), are applied to the snapshots of the fluctuating component of velocity to investigate instability modes of the cavitating flow. DMD and POD analysis yield multiple modes are corresponding to slow-varying drift flow, cloud-shedding, and Kelvin-Helmholtz (KH) instability for a fixed inlet flow condition. The high coherence measure obtained from the instabilities suggests a transfer of energy from the largest scales, fluctuating mean flow, to the smaller scales such as cloud cavitation and Kelvin-Helmholtz (KH) instability. It is demonstrated that the POD decorrelation of length scales yields inherently quasi-periodic time dynamics, e.g., incommensurate frequencies. Moreover, the eigenvalue obtained from DMD revealed multiple harmonic with different decay rates associated with the cloud cavitation. The above-mentioned intermittent transition between distinct cloud shedding regimes is investigated via Clustered-based Reduced Order Modeling (CROM). Four aperiodic shedding regimes are identified. 68% of the time, triplets of vortices are formed, while 28% of the time, a pair of vortices are formed in the near wake of the throat. Dominant mechanisms governing the momentum transport and the turbulence kinetic energy production, destruction, and redistribution in distinct regions of the flow field have been identified using Gaussian Mixture Models (GMMs). The preceding data-driven techniques and in-depth analysis of the results facilitated modeling of the cavitation inception and break-up. Accordingly, a phase transition field model is developed using the ultra-fast Time-Resolved Particle Image Velocimetry (TR-PIV) and vapor void fraction spatial and temporal data. The data acquisition is implemented in a Venturi-type test section. The approximate Reynolds number based upon the throat height is 10,000, and the approximate cavitation number is 1.95. The non-equilibrium cavitation model assumes that the phase production and destruction are correlated to the static pressure field, pressure spatial derivatives, void fraction, and divergence of the velocity field. Finally, the dependence of the model on the empirical constants has been investigated. / Doctor of Philosophy / A cavitation bubble occurs where the pressure field is below the saturation pressure of the liquid. Accumulation of the cavitation bubble forms a cavitating flow. This phenomenon is observed in pumps, propulsion systems, internal combustion engines, and rocket engines. Identifying the mechanisms leading to cavitation-induced damages is imperative in the design of the devices. In this regard, investigation of the cavitation bubble inception, deformation, collapse, and intermittent regime change is mandatory in learning the primary mechanisms of the stresses imposed on the device. Experiments and high-fidelity numerical and analytical methods can be employed to shed light on flow physics. The current study adopted joint experimental methods, data analysis techniques, and computational approaches to scrutinize the unsteady cavitating flow underlying physics as it occurs past the throat of a Venturi-type profile. Different mechanisms of instabilities are identified by applying the data-driven techniques to the raw images of the cavitating flow. The path of the transitions between physically different instabilities mechanisms is examined. The local dominant balance between stress terms in the conservation of momentum equation is identified, and the stress terms roles in cavitating flow instabilities and advective acceleration are determined. A new cavitation model is developed and validated against the experimental results. The new model improves the prediction of the void fraction in different regions of the flow field, making it feasible to simulate different regimes of cavitating flow. Finally, the dominant mechanism governing the liquid-vapor transition and the transport of the void fraction is described.