A small perturbation theory for cycloidal propellers

A hydromechanical theory is developed for cycloidal propellers for two limiting modes of operation wherein U » ΩR and U « ΩR, with U the rectilinear propeller speed (speed of advance) and ΩR the rotational blade speed. A first order theory is developed from the basic principles of the kinematics and dynamics of fluid motion and proceeds from the point of view of unsteady hydrofoil theory.

Explicit expressions for the instantaneous forces and moments produced by blade motions are presented. On the basis of these results an optimization procedure is carried out which minimizes the energy loss under the constraint of specified mean thrust. Under optimal conditions the propeller is found to possess high Froude efficiencies in both the high and low speed modes of propulsion. This efficiency is defined as the ratio of the average useful work obtained during one cycle of propeller operation to the average power input required to sustain the motion of the propeller during the cycle.

Mitochondria and the development of sea urchin embryos

After artificial activation or fertilization of non-nucleate fragments or eggs of the sea urchin, the mitochondria actively synthesize RNA. The RNA made in non-nucleate fragments is shown to be mostly single stranded and to be associated primarily with the low speed pellet of centrifuged cellular homogenates.

Protein synthesis is observed in non-nucleate fragments in the presence or absence of the mitochondrial RNA synthesis: it is found to be qualitatively similar but quantitatively less in the absence of the RNA synthesis. The continued syntheses of proteins in the non-nucleate fragments in the absence of mitochondrial RNA synthesis provides additional evidence for the presence of a stable messenger RNA component in the unfertilized sea urchin egg.

Since the uptake or actinomycin D was found to be inhibited by the presence of a fertilization membrane, ethidium bromide, at 10 μgs/ml, is used as an effective inhibitor of RNA synthesis in non-nucleate fragments and in early cleavage stage embryos. However, this same concentration of ethidium bromide is found to be only partially effective in blocking RNA synthesis at the mesenchyme blastula stage of development.

Low concentrations of ethidium bromide (2 and 5 μgs/ml) are found not to be lethal but to be capable of producing moderate developmental defects. In the presence of concentrations of ethidium bromide adequate to inhibit all the mitochondrial RNA synthesis (10 μgs/ml of ethidium bromide), from fertilization on, the embryos do not cleave beyond the 4-8 cell stages. When similar concentrations of ethidium bromide are added at an early mesenchyme blastula stage, the embryos do not gastrulate but continue to swim for more than 24 additional hours (adequate for control embryos to develop to a late prism stage). These results lead to the conclusion that mitochondrial RNA synthesis may be very essential for normal development to occur.

DNA is synthesized in the non-nucleate fragments of sea urchin eggs. None of the newly synthesized DNA is found in the closed circular form. When phenol extracted directly from the fragments, the DNA is found to sediment at approximately 38 and 27s in sucrose gradients but neither of these size classes could be found associated with the isolated mitochondria. The template for the synthesis of DNA in non-nucleate fragments remains unknown.

Avaliação da influência do material de confecção das matrizes no teste de conversão monomérica por espectrometria no infravermelho de um compósito

Este estudo teve por objetivo avaliar, in vitro, a influência do material de confecção das matrizes, traçando um perfil da conversão monomérica de um compósito micro-híbrido, além de avaliar qual dos materiais testados mais se assemelha a uma matriz de dentina. A avaliação foi feita através da análise do grau de conversão (GC). Foram confeccionadas 3 matrizes bipartidas, sendo estas de teflon negro, tefon branco e aço inoxidável, ambas com 10mm de diâmetro e 2 mm de profundidade. Para o grupo controle foi utilizado um incisivo central bovino, o qual teve sua face vestibular aplainada em uma lixadeira sob refrigeração constante, com o auxílio de uma lixa de carbeto de silício, número 800. Após, este dente foi preparado com uma broca diamantada número 2294 (KG Sorensen) em alta rotação, própria para a preparação de cavidades padronizadas para ensaios de laboratório, apresentando um limitador de penetração. Em seguida, com um motor de baixa rotação foi realizado o acabamento das paredes, obtendo-se uma cavidade de 2,0 mm de profundidade por 9,0 mm de diâmetro. Pela palatina desse dente, com uma broca carbide cilíndrica de numeração 2056 (KG Sorensen), fez-se uma penetração até se obter uma parede de dentina extremamente fina, porém sem que esta fosse rompida. Assim, com uma agulha, fez-se uma pequena perfuração no centro dessa dentina para que este instrumental servisse como um pino para remoção do corpo de prova de dentro da matriz de dente. Os corpos de prova (CP) foram obtidos a partir da inserção do compósito no interior da perfuração das matrizes em um único incremento e cobertos na superfície externa com uma matriz de poliéster mais uma lamínula de vidro. Os CP foram fotopolimerizados por 40 s pela fonte de luz halógena Optilux 501 (Demetron), com 500 mW/cm. Imediatamente após a polimerização, os corpos de prova eram submetidos no topo e na base para a análise de espectrometria no infravermelho para a determinação da profundidade de polimerização, pela técnica do filme vazado para o compósito não polimerizado e pela técnica da pastilha de brometo de potássio (KBr) para o compósito polimerizado. Foram confeccionados 5 CP de cada grupo. Em cada grupo, o compósito da base e do topo das amostras foi moído até se obter de 1,5 a 2,0 mg de pó e misturado com 70 mg de KBr, para obtenção da pastilha de KBr. Foi feita a análise de espectrofotometria no infravermelho por Transformada de Fourier (FTIR). As absorções selecionadas para o cálculo foram 1610 cm-1 e 1637 cm-1, os picos dos espectros das ligações dos carbonos aromáticos e alifáticos, respectivamente. Os dados obtidos foram tratados estatisticamente. Os grupos Gr1B, Gr2B, Gr3B e Gr4B representam, respectivamente, as bases dos CP confeccionados pelas matrizes de DB, TN, TB e AI. Já os Gr1T, Gr2T, Gr3T e Gr4T representam os topos. Médias (%) e DP: Gr1T (46,461,99), Gr2T (39,864,51), Gr3T (44,053,44) e Gr4T (38,045,08). Gr1B (40,441,49), Gr2B (36,153,81), Gr3B (40,093,18) e Gr4B (35,593,35). Em posse dos resultados, pôde-se concluir que os grupos do teflon negro, teflon branco e aço inoxidável não apresentaram diferenças entre o grau de conversão do topo e da base, enquanto que o grupo da dentina apresentou maior conversão do topo. Comparando as matrizes entre elas, pôde-se perceber que no topo, o GC do dente bovino é maior que o GC do aço inoxidável e do que o de teflon negro, o GC do teflon branco é maior que o GC do aço inoxidável e do que o de teflon negro. Já o topo dos grupos de dente bovino e teflon banco foram semelhantes. Nas bases dos CPs, não houve diferença significativa entre os grupos testados. De acordo com os resultados obtidos no experimento, pôde-se concluir que nos grupos do teflon negro, teflon branco e aço inoxidável não houve diferença entre 0 e 2 mm, ou seja, topo e base, o que mostra que o material de confecção da matriz não influênciou o grau de conversão do compósito. Já para o grupo da matriz de dentina, o topo apresentou valor de conversão monomérica maior, mostrando que, neste caso, o material da matriz interferiu no grau de conversão. Pode-se perceber também que existe uma tendência da matriz de teflon branco se assemelhar mais a matriz de dentina, pois foi o único grupo que apresentou semelhança nos valores de conversão monomérica no topo das amostras. Porém analisando a base das amostras, percebe-se que todos os grupos se comportaram de forma semelhante, obtendo valores do grau de conversão sem diferença significante.

基于低速面阵CCD的正弦相位调制干涉测量

正弦相位调制(SPM)干涉测量技术用于表面形貌测量时, 需要帧速高于300 frame/s的图像传感器, 同时要求调制信号频率与图像传感器帧速成确定的整数倍关系。提出一种基于低速CCD(30 frame/s)的帧速可调的高速图像传感技术, 通过控制每帧像素总数提高CCD帧速, 研制出一种高帧速图像传感器, 帧速可达300～1600 frame/s, 且每帧大小连续可调。将该CCD传感器用于正弦相位调制干涉泰曼-格林干涉仪, 测量镀膜玻璃板表面形貌, 当CCD图像传感器的帧速与调制信号频率呈16, 8, 4

A novel polarization modulator for a Moire system with grating imaging

A polarization modulator based on splitting with a Savart plate and rotation of an analyzer for a moire system with grating imaging is presented, and its modulation principle is analyzed. The polarization modulator is simple and achromatic. It is composed of a polarizer, a Savart plate, and an analyzer. The polarizer and the Savart plate are placed in front of the index grating to split the image of the scale grating in the moire system. The analyzer is placed behind the grating and rotated to realize the modulation of the moire signal. The analyzer can be rotated either continually with high speed or step by step with low speed to form different modulation modes. The polarization modulator makes the moire system insensitive to the change of initial intensity. In experiments, we verified the usefulness of the polarization modulator.

Dried fish cakes with improved texture

To overcome the problem of underutilization of marine by-catches, Basu et al. (1985) developed fish cube from minced fish meat. Although the product was acceptable, it had little rubbery texture. An attempt was made to improve the texture of the cake by several methods. It was found that 5% tapioca starch along with 3% texturised soybean protein improved the texture and juiciness of the rehydrated product. Preheating of the minced meat at 70°C for 30 minutes also improved the texture appreciably. It was also found that mixing of the ingredients at low speed (less than 100 rpm) in a dough mixer gave the best texture, higher speed and sharp blades leading to rubbery texture. The dehydrated product (moisture 19-20%) thus prepared had a shelf life of six months at ambient temperature.

Unsteady transition in an axial-flow turbine. Part 2. Cascade measurements and modeling

Part 1 of this paper reanalyzed previously published measurements from the rotor of a low-speed, single-stage, axial-flow turbine, which highlighted the unsteady nature of the suction surface transition process. Part 2 investigates the significance of the wake jet and the unsteady frequency parameter. Supporting experiments carried out in a linear cascade with varying inlet turbulence are described, together with a simple unsteady transition model explaining the features of seen in the turbine.

Unsteady transition in an axial-flow turbine. Part 1. Measurements on the turbine rotor

Previously published measurements in a low-speed, single-stage, axial-flow turbine have been reanalyzed in the light of more recent understanding. The measurements include time-resolved hot-wire traverses and surface hot film gage measurements at the midspan of the rotor suction surface with three different rotor-stator spacings. This paper investigates the suction surface boundary layer transition process, using surface-distance time plots and boundary layer cross sections to demonstrate the unsteady and two-dimensional nature of the process.

Effects of rotating inlet distortion on multistage compressor stability

In multi-spool engines, rotating stall in an upstream compressor will impose a rotating distortion on the downstream compressor, thereby affecting its stability margin. In this paper experiments are described in which this effect was simulated by a rotating screen upstream of several multistage low-speed compressors. The measurements are complemented by, and compared with, a theoretical model of multistage compressor response to speed and direction of rotation of an inlet distortion. For co-rotating distortions (i.e., distortions rotating in the same direction as rotor rotation), experiments show that the compressors exhibited significant loss in stability margin and that they could be divided into two groups according to their response. The first group exhibited a single peak in stall margin degradation when the distortion speed corresponded to roughly 50% of rotor speed. The second group showed two peaks in stall margin degradation corresponding to distortion speeds of approximately 25-35% and 70-75% of rotor speed. These new results demonstrate that multistage compressors can have more than a single resonant response. Detailed measurements suggest that the two types of behavior are linked to differences between the stall inception processes observed for the two groups of compressors and that a direct connection thus exists between the observed forced response and the unsteady flow phenomena at stall onset. For counter-rotational distortions, all the compressors tested showed minimal loss of stability margin. The results imply that counter-rotation of the fan and core compressor, or LP and HP compressors, could be a worthwhile design choice. Calculations based on the two-dimensional theoretical model show excellent agreement for the compressors which had a single peak for stall margin degradation. We take this first-of-a-kind comparison as showing that the model, though simplified, captures the essential fluid dynamic features of the phenomena. Agreement is not good for compressors which had two peaks in the curve of stall margin shift versus distortion rotation speed. The discrepancy is attributed to the three-dimensional and short length scale nature of the stall inception process in these machines; this includes phenomena that have not yet been addressed in any model.

Three-dimensional interactions in the rotor of an axial turbine

This article presents a study of the development of the three-dimensional flowfield within the rotor blades of a low-speed, large-scale axial flow turbine. Measurements have been performed in the rotating and stationary frames of reference. Time-mean data have been obtained using miniature five-hole pneumatic probes, whereas the unsteady development of the flow has been determined using three-axis subminiature hot-wire anemometers. Additional information is provided by the results of blade-surface flow-visualization experiments and surface-mounted hot-film anemometers. The development of the stator exit flow, as it passes through the rotor blades, is described. Unsteady data suggest that the presence of the rotor secondary and tip leakage flows restricts the region of unsteady interaction to near midspan when the stator wakes and secondary flows are adjacent to the suction surface. Surface-mounted hot-film data show that this affects the suction-side laminar-turbulent transition process.

Blade row interaction in a high pressure steam turbine

This paper presents a study of the three-dimensional flow field within the blade rows of a high-pressure axial flow steam turbine stage. Compound lean angles have been employed to achieve relatively low blade loading for hub and tip section and so reduce the secondary losses. The flow field is investigated in a Low-Speed Research Turbine using pneumatic and hot-wire probes downstream of the blade row. Steady and unsteady numerical simulations were performed using structured 3D Navier-Stokes solver to further understand the flow field. Agreement between the simulations and the measurements has been found. The unsteady measurements indicate that there is a significant effect of the stator flow interaction in the downstream rotor blade. The transport of the stator viscous flow through the rotor blade row is described. Unsteady numerical simulations were found to be successful in predicting accurately the flow near the secondary flow interaction regions compared to steady simulations. A method to calculate the unsteady loss generated inside the blade row was developed from the steady numerical simulations. The contribution of various regions in the blade to the unsteady loss generation was evaluated. This method can assist the designer in identifying and optimizing the features of the flow that are responsible for the majority of the unsteady loss production. An analytical model was developed to quantify this effect for the vortex transport inside the downstream blade.

Influence of the state of the inlet endwall boundary layer on the interaction between pressure surface separation and endwall flows

This paper describes the effect of the state of the inlet boundary layer (laminar or turbulent) on the structure of the endwall flow on two different profiles of low-pressure (LP) turbine blades (solid thin and hollow thick). At present the state of the endwall boundary layer at the inlet of a real LP turbine is not known. The intention of this paper is to show that, for different designs of LP turbine, the state of the inlet boundary layer affects the performance of the blade in very different ways. The testing was completed at low speed in a linear cascade using area traversing, flow visualization and static pressure measurements. The paper shows that, for a laminar inlet boundary layer, the two profiles have a similar loss distribution and structure of endwall flow. However, for a turbulent inlet boundary layer the two profiles are shown to differ significantly in both the total loss and endwall flow structure. The pressure side separation bubble on the solid thin profile is shown to interact with the passage vortex, causing a higher endwall loss than that measured on the hollow thick profile.

Vortex Transport and Blade Interactions in High Pressure Turbines

This paper presents a study of the three-dimensional flow field within the blade rows of a high-pressure axial flow steam turbine stage. Half-delta wings were fixed to a rotating hub to simulate an upstream rotor passage vortex. The flow field is investigated in a Low-Speed Research Turbine using pneumatic and hot-wire probes downstream of the blade row. The paper examines the impact of the delta wing vortex transport on the performance of the downstream blade row. Steady and unsteady numerical simulations were performed using structured 3D Navier-Stokes solver to further understand the flow field. The loss measurements at the exit of the stator blade showed an increase in stagnation pressure loss due to the delta wing vortex transport. The increase in loss was 21% of the datum stator loss, demonstrating the importance of this vortex interaction. The transport of the stator viscous flow through the rotor blade row is also described. The rotor exit flow was affected by the interaction between the enhanced stator passage vortex and the rotor blade row. Flow underturning near the hub and overturning towards the mid-span was observed, contrary to the classical model of overturning near the hub and underturning towards the mid-span. The unsteady numerical simulation results were further analysed to identify the entropy producing regions in the unsteady flow field.

CALCULATIONS OF INLET DISTORTION INDUCED COMPRESSOR FLOWFIELD INSTABILITY.

Calculations are presented predicting the onset of flow instability for a multistage low speed axial compressor operating in circumferentially distorted inlet flow. The most important feature of the model used is that it attempts to properly account for the fluid dynamic interaction between the spoiled and unspoiled sectors of the compressor. The calculations show that there is an approximate stability criterion, the annulus averaged slope of the compressor pressure rise characteristic equal to zero, that is valid whenever the dynamics of the compressor distorted flowfield can be considered independent of the compressor environment. This approximate criterion is used to investigate the relationship between the present model and the 'parallel compressor' model. Further calculations are performed to investigate cases of interest when the dynamics of the compressor flowfield are coupled to the environment. Resonant cases and cases when the distortion is unsteady are studied.

Movement of deposited water on turbomachinery rotor blade surfaces

A theoretical approach for calculating the movement of liquid water following deposition onto a turbomachine rotor blade is described. Such a situation can occur during operation of an aero-engine in rain. The equation of motion of the deposited water is developed on an arbitrarily oriented plane triangular surface facet. By dividing the blade surface into a large number of facets and calculating the water trajectory over each one crossed in turn, the overall trajectory can be constructed. Apart from the centrifugal and Coriolis inertia effects, the forces acting on the water arise from the blade surface friction, and the aerodynamic shear and pressure gradient. Non- dimensionalisation of the equations of motion provides considerable insight and a detailed study of water flow on a flat rotating plate set at different stagger angles demonstrates the paramount importance of blade surface friction. The extreme cases of low and high blade friction are examined and it is concluded that the latter (which allows considerable mathematical generalisation) is the most likely in practice. It is also shown that the aerodynamic shear force, but not the pressure force, may influence the water motion. Calculations of water movement on a low-speed compressor blade and the fan blade of a high bypass ratio aero-engine suggest that in low rotational speed situations most of the deposited water is centrifuged rapidly to the blade tip region. Copyright © 2006 by ASME.