Two-photon absorption and self-phase modulation in InGaAsP/InP multi-quantum-well waveguides

We report the first measurement of two-photon absorption (TPA) and self-phase modulation in an InGaAsP/InP multi-quantum-well waveguide. The TPA coefficient, β2, was found to be 60±10 cm/GW at 1.55 μm. Despite operating at 200 nm from the band edge, self-phase modulation as high as 8±2 rad was observed for 30-ps optical pulses at 3.8-W peak input power. A theoretical calculation indicates that this enhanced phase modulation is primarily due to bandfilling in the quantum wells and the free-carrier plasma effect.

光系统II复合物的光仰制特征及其内源保护机理

本文以菠菜PSⅡ颗粒PSⅡ核心复合物和PSⅡ反应中心复合物为材料通过比较光抑制处理和单线态氧处理对上述制剂色素、蛋白和光谱特性的影响，．以及光抑制对细胞色素b559 (Cyt b559)和放氧的影响，研究了PSⅡ光抑制及其内源保护机理得到如下的结果: 1)光抑制处理和外源单线态氧处理对PSⅡ具有相似的破坏特性,同时，加入单线态氧的特异性清除剂组氨酸(His)可明显遏制光抑制处理对PSⅡ各组分的破坏这些结果说明单线态氧参与了PSⅡ的光破坏过程. 2) PSⅡ蛋白组分不仅受到强光的破坏，而且在照光后暗放置过程中还继续受到破坏 这种暗放置破坏过程具有温度敏感性因此推测在光照后暗放置过程中的PSⅡ蛋白降解是酶促反应这些结果证明，PSⅡ蛋白的光破坏具有活性氧损伤和酶促水解两种可能的破坏机理． 3)首次观察到PSⅡ中Cyt b559的高电势态(qt b559 HP)的百分含量在光抑制初期上升，随后下降的现象且这种变化受到外加强His的遏制。表明光抑制产生的单线态氧参与了Cytb559 HP百分含量的改变,同时还观察到这种变化的时间进程与PSⅡ蛋白二级结构在光抑制中变化的时间进程相似后者也表现出双相变化进程这说明光抑制产生的单线态氧引起了蛋白构象的变化后者导致了Cytb559 HP百分含量的改变. 4)在不同的处理条件下，PSⅡ放氧活性的变化与Cyt b559 HP百分含量的变化具有明显的相关性它们的变化可能具有相同的原因，即PSⅡ蛋白构象的改变． 5)无氧条件下照光时’PSⅡ反应中心复合物中的Cytb559的低电势态(Cytb559 LP)可从Pheo得到电子而被还原具有较高反应活性的Pheo被清除这体现了Cytb559 LP的一种光保护功能. 综合上述结果及参考已有的文献我们提出了一种以Cytb559为中心的PSⅡ光抑制快速内源保护机理的调控模型。光抑制通过影响PSⅡ蛋白构象而使Cytb559 HP和Cytb559 LP发生相互转换。Cytb559 HP具有清除活性氧的功能，而Cytb559 LP态则具有从Pheo或QA吸收电子的作甩因此它们可受PSⅡ不同状态的调节进行相互转换以淬灭活性自由基达到保护PSⅡ功能的目的。

INVISCID BLADE-TO-BLADE PREDICTION OF A WAKE-GENERATED UNSTEADY FLOW.

A description is presented of a time-marking calculation of the unsteady flow generated by the interaction of upstream wakes with a moving blade row. The inviscid equations of motion are solved using a finite volume technique. Wake dissipation is modeled using an artificial viscosity. Predictions are presented for the rotor mid-span section of an axial turbine. Reasonable agreement is found between the predicted and measured unsteady blade surface static pressures and velocities. These and other results confirm that simple theories can be used to explain the phenomena of rotor-stator wake interactions.

光系统Ⅱ反应中心细胞色素b559结构和功能的研究

植物已经演化出多种保护其免受强光抑制和破坏的机制，从而使植物体在自然界能够应付复杂多变的光照环境。虽然人们早就确定Cyt b-559存在于PSII反应中心内，但目前对其性质与功能的认识还不充分。本工作的目的就是研究Cyt b-559天然分子特性，探讨其生理功能和存在的意义。取得了一些有新意的结果： 1、依据PSII反应中心分离纯化的原理，应用更有效的层析介质DEAE-Sephacel，我们设计了快速高效的从菠菜和水稻中分离纯化Cyt b-559的方法和流程，获得了高纯度的样品。它们在非变性胶电泳中具有相同的泳动性。蛋白组分的HPLC结果证明，纯化的Cyt b-559的确由两个亚基组成，α亚基和β亚基的分子量用我们设计的适合于分析小蛋白的Tricine—SDS—PAGE方法准确测定为9.4kDa和4.5kDa。 2、利用HPLC技术分析了纯化的Cyt b-559样品的色素组成，结果表明Cytb-559中含有Chl α而不含类胡萝卜素分子，这一结果通过吸收光谱和共振拉曼光谱的分析得到进一步地证明。通过等电聚焦方法分析了Cyt b-559的等电点，发现其亚基的等电点相差很大，全蛋白的等电点与...更多D1、D2蛋白的等电点也不相同，推测在体内生理pH条件下它们具有相反带电性而在PSII组装中发挥作用。 3、低温荧光光谱的检测结果表明，Cyt b-559的荧光发射峰位在563nm和666nm;首次证明Cyt b-559可以发出荧光和将电子传递给结合在其上的辅助叶绿素，但传递能力比较低故而导致其荧光特性与PSII反应中心的不相同。Cytb-559的紫外荧光光谱表明Trp残基位于其内部的疏水区域，证明Cyt b-559中的芳香族氨基酸可能在其功能的发挥中起一定作用。 4、通过MCD的分析，发现Cyt b-559中血红素的MCD信号在540—580nm和400—440nm波段，而且光谱形状和强度与PSII反应中心的相一致，说明PSII反应中心该范围内的MCD信号中有Cyt b-559的贡献。FTIR光谱的测定结果证明Cyt b-559血红素的配体是组氨酸，其二级结构中α-螺旋占了一半。此外，还比较了Cyt b-559和PSII反应中心的膜脂成分，发现两者有很大的相似性。不同植物来源的Cyt b-559在许多性质上都表现出高度一致，从一个侧面证明Cyt b-559在进化中的保守性。 5、PSll反应中心发生光破坏时，原初电子供体P680己受到严重破坏。我们发现，在光抑制的最初一段时间内，Cyt b-559吸收峰值发生变化：在受体侧光抑制的条件下，其吸收峰值先略有增加而后才下降，而在供体侧光抑制条件下则相反，说明 Cyt b-559对光抑制的发生非常敏感，可能在光抑制早期保护PSll反应中心。 6、纯化的Cyt b-559的组氨酸含量在照光前后没有显著的变化，说明 PSll反应中心内被破坏的组氨酸不属于Cyt b-559。PSll反应中心所含的组氨酸中有些可被DEPC修饰，但我们的实验结果表明DEPC不能修饰Cyt b-559的组氨酸。这可能有利于Cyt b-559保护功能的发挥。 7、我们观察到，在两种光抑制条件下，LP Cyt b-559光还原和 HP Cyt b-559光氧化具有对pH值的依赖性，说明Cyt b-559在光保护中的作用不仅与其高低电势态有关，而且与其质子化程度有联系。CCCP促进HP Cyt -559释放质子，从而维持循环电子传递。DCBQ和 DCMU在很低浓度时都抑制 Cyt b-559光还原，前者不影响Cyt b-559光氧化而后者在CCCP存在时也会抑制Cyt b-559光氧化。 8、Cyt b-559有定位PSll反应中心其它蛋白的锚蛋白的作用。黄化苗转绿实验证明在 HP Cyt b-559的含量增加超过 45％以后放氧活性开始逐渐增加。Cytb－559从低电势态到高电势态的转变是放氧复合物组装到PSll反应中心的关键步骤之一。在植物正常生长时，Cyt b-559与 P680的其它电于供体发生竟争，起到安全阀门的作用。 9、在逆境条件下，Cyt b-559具有保护PSll反应中心免受强光破坏而起到“分于开关”的作用。我们的实验表明，在室温条件下存在通过Cyt b-559的环式电子流，存在从氧化态LP Cyt b-559到还原态HP Cyt b-559的一个循环，其中的氧化还原变化与质子化／去质子化反应相连。通过与其它血红素蛋白的比较，我们推测 Cyt b-559“分子开关”的关键是：光抑制情况下，铁原子与远端His之间的疏水空穴被氧自由基占据后使得铁进入叶琳中央孔中，迫使近端HIS向叶琳平面位移，从而引起 Cyt b-559构象改变，使电势态发生转变。

新型光系统II电子传递抑制剂的抑制特性及作用位点的研究

本文由两部分组成，一部分是关于一组新型除草剂(K-15，K-23)的抑制特性及作用位点的研究;另一部分是关于碳酸氢盐对细胞色素b-559高电势的保护作用的研究。 在第一部分，我们首先研究了抑制剂K-23对Psn放氧活性、DCIP光还原和可变荧光等光合特性的影响。研究发现，K-23在低浓度时刺激放氧活性，而在相对高浓度时抑制放氧活性。但是，K-23在低浓度时却有效地抑制了可变荧光。这些数据表明了新型抑制剂的抑制反应是基于氧化还原作用而不是猝灭作用。此外，通过采用胰蛋白酶消化类囊体膜的方式初步检测了新型抑制剂的作用部位，其结果表明：虽然新型抑制剂抑制受体侧电子传递，但它的抑制部位与DCMU不同。 其次，研究了新型抑制剂对光系统II色素蛋白复合体与多肽组分的影响及抑制剂的键合蛋白。应用SDS-PAGE技术，发现新型抑制剂主要作用于光系统II的反应中心蛋白。用温和的Deriphat-PAGE分析也证实了新型抑制剂作用于核心复合物，导致核心复合物二聚体消失。 进一步用SDS-PAGE分析新型抑制剂对Psn多肽组分的影响，发现新型抑制剂主要影响D．、D2、CP43和CP47。用荧光发射的方法确定了K-15键合在D2蛋白上。 最后，结合荧光动力学和HPLC方法，分别从定性和定量的角度，以核心复合物以及抑制剂存在下从BBY中分离的核心复合物为研究对象，详细研究了抑制剂对QA的取代作用。研究发现，在无去垢剂或低浓度去垢剂存在情况下，由于不能创造出适合于QA存在的疏水环境，我们没有得到QA被K-15取代的实验证据。而在抑制剂K-15存在下，用2.2% HTG从BBY分离的核心复合物的实验中，检测不到正的可变荧光Fv，而是得到了降低的FM，这个结果表明QA已被抑制剂在它的作用位点处所取代。 在第二部分，研究了pH5.0—7.0范围内碳酸氢盐对Cyt b-559氧化还原状态转变的影响。首先研究了pH5.0～7.0条件下碳酸氢盐对PSII Cyt b-559还原减氧化差异吸收光谱的影响，发现铁氰化钾还原的PSII Cyt b-559 HP的含量随介质pH值的降低而减少。然而，碳酸氢盐的加入阻止了由于介质pH降低而引起的Cyt b-559由高电势向低电势的转化。比如，当样品温育在pH5.0的介质中，铁氰化钾还原的Cyt b-559 HP含量占总量的25%-30%，当介质中加入2mmol/L碳酸氢盐后Cyt b-559 HP的含量上升，占总量的50%-56%。碳酸氢盐效应对氢醌还原的Cyt b-559HP含量的影响尤为显著。pH6.5时碳酸氢盐对Cyt b-559的还原氧化状态的影响不显著。其次，分别研究了PSII经Tris处理去除锰簇和三个外周蛋白及NH20H处理去除锰簇和17 kDa和23 kDa后，碳酸氢盐对Cytb一559 HP影响的pH依赖值，发现不论在pH5.0还是pH6.5的介质中碳酸氢盐效应都不存在。 综合以上实验结果，我们认为碳酸氢盐对酸化引起的Cyt b-559氧化还原状态的影响与它和锰的作用有关，但也不能排除钙离子与碳酸氢盐之间的协同作用。

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.

Modeling of unsteady transitional boundary layers

In turbomachinery, a considerable proportion of the blade surface area can be covered by transitional boundary layers. This means that accurate prediction of the profile loss and boundary layer behavior in general depends on the accurate modeling of the transitional boundary layers, especially at low Reynolds numbers. This paper presents a model for determining the intermittency resulting from the unsteady transition caused by the passage of wakes over a blade surface. The model is founded on work by Emmons (1951) who showed that the intermittency could be calculated from a knowledge of the behavior of randomly formed turbulent spots. The model is used to calculate the development of the boundary layer on the rotor of a low Reynolds number single-stage turbine. The predictions are compared with experimental results obtained using surface-mounted hot-film anemometers and hot-wire traverses of the rotor midspan boundary layer at two different rotor-stator gaps. The validity and limitations of the model are discussed.

Effect of blade tip geometry on the tip leakage flow in axial turbine cascades

The phenomenon of tip leakage has been studied in two linear cascades of turbine blades. The investigation includes an examination of the performance of the cascades with a variety of tip geometries. The effects of using plain tips, suction side squealers, and pressure side squealers are reported. Traverses of the exit flow field were made in order to determine the overall performance. A method of calculating the tip discharge coefficients for squealer geometries is put forward. In linking the tip discharge coefficient and cascade losses, a procedure for predicting the relative performance of tip geometries is developed. The model is used to examine the results obtained using the different tip treatments and to highlight the important aspects of the loss generation process.

Investigation of boundary layer development in a multistage LP turbine

This paper describes an investigation of the behavior of suction surface boundary layers in a modern multistage Low Pressure turbine. An array of eighteen surface-mounted hot-film anemometers was mounted on a stator blade of the third stage of a 4-stage machine. Data were obtained at Reynolds numbers between 0.9 × 105 and 1.8 × 105 and 1.8 × 105. At the majority of the test conditions, wakes from upstream rotors periodically initiated transition at about 40% surface length. In between these events, laminar separation occurred at about 75% surface length. It is inferred that the effect of the wakes on the performance of the bladerow is limited and that steady flow design methods should provide an adequate assessment of LP turbine performance during design.

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.

Investigation of boundary layer development in a multistage LP turbine

This paper describes an investigation of the behavior of suction surface boundary layers in a modern multistage Low-Pressure turbine. An array of 18 surface-mounted hot-film anemometers was mounted on a stator blade of the third stage of a four-stage machine. Data were obtained at Reynolds numbers between 0.9 × 105 and 1.8 × 105. At the majority of the test conditions, wakes from upstream rotors periodically initiated transition at about 40 percent surface length. In between these events, laminar separation occurred at about 75 percent surface length. Because the wake-affected part of the flow appeared to be only intermittently turbulent, laminar separation also occurred at about 75 percent surface length while this flow was instantaneously laminar. At all but the lowest Reynolds numbers, the time-mean boundary layer appeared to have re-attached by the trailing edge even though it was not fully turbulent. It is inferred that the effect of the wakes on the performance of the blade row is limited and that steady flow design methods should provide an adequate assessment of LP turbine performance during design.