bluuebunny/crossref_metadata_2025_split huggingface dataset:
Systematic review of electronic remote blood issue
Authors: Sellen K. M. , Jovanovic A. , Perrier L. , Chignell M. 
Published: April 2015

Background and ObjectivesThe implementation of electronic remote blood issue (ERBI) may provide safety and efficiency gains for transfusion medicine. This systematic review's objective was to assess whetherERBIaffects incidents of adverse events, time taken for blood issue and delivery, and cross‐match to transfusion ratios, among other measures of safety and efficiency. The review also sought to uncover barriers and facilitators ofERBIimplementation.Materials and MethodsWe searched four aggregated electronic databases (Medline,EMBASE,CINAHLandBIOSIS) up to 19July 2012, with an updated search performed on 5March 2014 for studies onERBI. No specific study design criteria were used in the initial inclusion due to the low number of studies onERBI.ResultsA total of 4758 citations were initially identified; after 1844 duplicates were removed, 2612 citations were excluded on the basis of the abstract. Two reviewers evaluated a total of 302 full‐text articles independently; of these, seven citations were eligible for inclusion. An updated search and the authors' own collections confirmed an additional five citations, totalling 13 citations and six studies within these.ConclusionThere is insufficient evidence to demonstrate whetherERBIsignificantly impacts safety and efficiency of blood transfusion and delivery processes. Rigorously designed studies to assess safety and efficiency outcomes are required using proxy or corollary measures. A number of positive results were reported, however, and most studies included suggestions for facilitatingERBIimplementation.
Radiofrequency Probe and Sharp Transection for Tenoscopic‐Guided Desmotomy of the Accessory Ligament of the Superficial Digital Flexor Tendon
Authors: Nelson Brad B. , Kawcak Chris E. , Ehrhart E.J. , Goodrich Laurie R. 
Published: April 2015

ObjectiveTo compare intra and postoperative clinical features of desmotomy of the accessory ligament of the superficial digital flexor tendon (ALSDFT) using the Saber radiofrequency (SaberRF) electrosurgical probe versus sharp transection with a tenotomy knife.Study DesignRandomized, controlled, blocked (horse) design.AnimalsAdult horses (n = 6).MethodsEach horse received bilateral, tenoscopic‐guided ALSDFT desmotomy with a SaberRF and tenotomy knife, randomly assigned to left, or right limb. The desmotomy duration and intraoperative hemorrhage grades were recorded. Postoperatively, the grades for surgical incision, carpal sheath effusion, carpal range of motion, flexion pain, and lameness were recorded. Light microscopy using hematoxylin and eosin, and viability staining were performed on the ALSDFT, flexor carpi radialis tendon, radial head of the deep digital flexor tendon, and the deep digital flexor tendon. Variables were compared between desmotomy methods with a paired t‐test, Wilcoxon signed rank test, or a repeated measures mixed model. Statistical significance was set at P < .05.ResultsDesmotomy of the ALSDFT was completed in all horses. Only mild hemorrhage was observed and not different between methods (SaberRF 2/5 limbs; tenotomy knife 5/6 limbs, P = .078). Carpal sheath effusion was greater for SaberRF at Day 1 (P = .019) but not different from tenotomy knife at any later time. There was no significant difference between methods for viability staining or other measured outcomes.ConclusionsTenoscopic‐guided ALSDFT desmotomy with the SaberRF probe showed no difference in measured outcomes to sharp transection with a tenotomy knife and minimal collateral tissue damage was observed.
Molecular phylogeny and divergence time estimation of Cosmodela (Coleoptera: Carabidae: Cicindelinae) tiger beetle species from Southeast Asia
Authors: López‐López Alejandro , Abdul Aziz Azidah , Galián José 
Published: April 2015

Cosmodela Rivalier, 1961, represents a genus of tiger beetles that currently contains 13 described species widely distributed across Southeast Asia. A phylogenetic analysis based on the mitochondrial DNA fragments 16S and COI and the nuclear marker wingless and a phylogeographic analysis using a COI fragment were carried out on two subspecies of Cosmodela aurulenta (C. a. juxtata and C. a. aurulenta). The results support the hypothesis that these two subspecies are significantly different to be considered as separate species that diverged during the Pleistocene. TAXONDNA analysis was used to investigate the capability of the COI region as a marker for discriminating both entities and to quantify intra‐ and intertaxa genetic variation. The minimum distance between C. aurulenta and C. juxtata was 2.7837%, and no overlap of intra‐ and intertaxa genetic divergence was observed. Both taxa, here considered as valid species, occur in sympatry in the Malay Peninsula, with C. aurulenta most probably originating from the area and C. juxtata a secondary colonizer that expanded southwards from the Asian mainland. Our data infer a continental origin of the Indonesian samples of C. aurulenta, and they most likely dispersed across the land bridges that emerged during glacial maxima to form Sundaland.
Implementation Approaches to Sequencing in Microprocessor-Based Controllers
Authors: Sreetharan M. , Langenbacher F. 
Published: April 2015

Traditional relay-based sequencing is increasingly being replaced by microprocessor-based programmable sequence controllers.
Microprocessor-based sequencers are flexible, easy to use and eliminate the expensive reworking of hardwired logic each time a sequencing scheme is revised. However, the logical (bit-oriented) nature of the computations involved in implementing sequencing systems offer considerable challenge to the designers of microprocessor-based (byte/word oriented) sequencers to provide novel software and/or hardware architectures that are cost effective to implement and meet the speed requirements.
This paper examines several possible implementation techniques of automatic digital sequencers. In particular, it describes the requirements and the design concepts that formed the basis of the sequencer implemented as part of a multi-processor based full authority controller at the authors’ company, that is capable of controlling a range of turbines in various applications. A comparative study of the performances of several existing sequencing systems is also presented.
Statistical Analysis of Fracture of Silicon Nitride (RBSN) Using the Short Span Bending Technique
Authors: Lamon J. 
Published: April 2015

The short-span bending technique, pionneered with rod specimens of porcelain for the separation of the respective influences of surface and volume flaw populations upon strength, was applied to reaction bonded silicon nitride, prime candidate for use in advanced gas turbine systems. General approach for the statistical analysis of brittle fracture under tensile multiaxial stress states was extended to square specimens, and used to interpret experimental results.
Surface and volume flaw populations appeared to exhibit different characteristics, and thus exert different influences upon the reliability of RBSN. Implications for the interpretation of bending tests and some important trends in the failure strength with specimen size are discussed.
The Active Magnetic Bearing Enables Optimum Control of Machine Vibrations
Authors: Habermann Helmut , Brunet Maurice 
Published: April 2015

The active magnetic bearing is based on the use of forces created by a magnetic field to levitate the rotor without mechanical contact between the stationary and moving parts. A ferromagnetic ring fixed on the rotor “floats” in the magnetic field generated by the electromagnets, which are mounted as two sets of opposing pairs. The current is transmitted to the electromagnetic coils through amplifiers.
The four electromagnets control the rotor’s position in response to the signals transmitted from the sensors. The rotor is maintained in equilibrium under the control of the electromagnetic forces. Its position is determined by means of sensors which continuously monitor any displacements between rotor and stator through an electronic control system.
As in every control system, damping of the loop is provided by means of a phase advance command from one or more differenciating circuits of the position error signal.
The vibrations of the rotor and stator of a machine are generated by different forces:
- centrifugal forces due to the misalignment between the geometrical axis and the inertial axis of the rotor (unbalance),
- reaction forces due to aerodynamical forces on the rotor and stator blades.
The active magnetic bearing allows the decrease and in many cases the fully cancelling of effects of these forces i.e. the vibrations of the machine. The inertial forces can be cancelled by shifting the axis of rotation of the rotor from the geometrical axis to the inertial axis (this system is usually called automatic balancing).
The reaction forces due to aerodynamical effects can be cancelled by the creation by the magnetic bearings of forces in opposition.
The vibrations are measured on the stator by accelerometers, and the signals drive magnetic bearings which generate forces having the same amplitude but in phase opposition.
The improvement in vibrations amplitude usually ranges from 20 Db to 40 Db over a large band of frequencies.
Developing Concepts in the Rotordynamic Analysis of Aero Gas Turbines
Authors: Bellamy R. A. , Jonson C. P. , Gaffney R. 
Published: April 2015

Aero engine manufacturers now use large, three dimensional, non-axisymmetric detailed finite element models of complete engines as a regular production design tool to evaluate the static and dynamic structural characteristics of new design.
These have replaced the simpler beam type models for which techniques and criteria for evaluating engine dynamics had evolved over many years.
The new tools produce an order of magnitude more information that is of better quality, but much more complicated and does not allow easy use of the old criteria for evaluation. Hence new ideas are developing and new criteria are required to answer the original question, “is this engine satisfactory from the dynamics point of view?”.
This paper identifies some of the problems raised by the capability to do a 3D analysis as a standard procedure, and discusses possible solutions.
A Hybrid Diffuser With Distorted Inflow
Authors: Adkins R. C. , Montazerin N. 
Published: April 2015

Tests have been conducted on a Conical Hybrid Diffuser of short length in order to determine the effects of a range of inlet flow distortions of an axisymmetric nature.
As with most other types of diffuser, the performance was impaired as the level of distortion was increased, although some restoration could be obtained by either increasing diffuser length or rate of bleed-off.
In general, diffuser performance, in terms of flow stability and pressure recovery, was satisfactory.
Application of Aero-Derivative Gas Turbines in the Onshore Oil Fields of Abu Dhabi
Authors: Saadawi H. 
Published: April 2015

For more than a decade, aircraft-derivative industrial gas turbines have been used in middle eastern oil fields for providing power to water injection and crude oil pumping installations.
The remote desert locations and the hostile environment provide a unique challenge. This paper describes some of the experiences gained in operating aero-derivative gas turbines in the onshore oil fields of Abu Dhabi.
Protective Coating Systems for High Temperature Gas Turbine Components
Authors: Harry N. J. F. V. 
Published: April 2015

The current generation of hot end turbine blade materials and coatings for Tyne RMIC and Olympus TM3B perform most satisfactorily under normal conditions of service. In general the overall picture is optimistic and the Royal Navy does not consider there is any fundamental requirement to upgrade these systems. With the introduction of the Spey SMIA into Fleet service and the current uprating programme for the 18MW SMIC, the need for materials research has not diminished. Both of these engines are designed for long life so the search continues for blade materials and coatings which will give enhanced creep life and corrosion resistance.
This paper looks at the performance of turbine blade materials and coatings in service and reports on early experience with SM1A.
Improvement of a Cycle J Integral for CT-Specimens
Authors: Shao-Lun Liu , Ji-Zhou Xie 
Published: April 2015

The cycle J integral formula for CT-specimens has been improved as follows
Δ J = 2 B b a 1 • U + a 2 • Δ δ + 2 B b U e { -1.2025 a w + 0.6233 0.3 ⩽ a w ⩽ 0.53 -0.02 Sin ⁡ π 0.23 a w - 0.53 0.53 < a w < 0.95
This formula is applicable to the fatigue crack propagation range of 0.3 ≤a/w<0.95. In comparision with other formulae of cycle J integral, the application range of the above expression is enlarged and its precision is also increased to a certain extent.
Lip Separate Flow Blowing and Analysis of Coherence of Inlet
Authors: Zhongwei He , Shiying Zhang 
Published: April 2015

It is found in the experiments that blowing at the lip separation of the inlet obviously reduces the turbulences at the inlet exit, and apparently reduces the intensity of pressure fluctuations caused by the shock-boundary layer interaction down-stream of throat. The coherence between pressure in the interaction region and total pressure at the exit is also reduced.
The coherence between the pressure in the lip separation region and total pressure at the exit is 0.32. If, in addition, there is a stronger shock down-stream of the throat the above mentioned coherence is reduced to 0.06.
Stratified Charge Rotary Engine for General Aviation
Authors: Mount Robert E. , Parente Anthony M. , Hady William F. 
Published: April 2015

Exciting developments have occurred over the past two years in the technological status and production aspects of Stratified Charge Rotary Engines. A program is currently underway for the development, certification and production of a 400 HP aircraft engine in early 1990. The joint program is being conducted by John Deere’s Rotary Engine Division and AVCO Lycoming Williamsport Division. The engine will offer to the General Aviation community Jet-A fuel capability at substantial cost savings, improved altitude capability and lower fuel consumption over turbine power plants. Application to fixed wing and rotary wing aircraft are planned.
Other stratified charge rotary engine development work in progress involves ground power units, airborne APU’s, shipboard gensets and vehicular engines, supported by Deere production capabilities and DOD interests. Technology enablement efforts by NASA, aimed at highly advanced output and efficiency are in progress leading toward revolutionary engine capability for aircraft and other applications.
Production and Development of Secondary Flows and Losses Within Two Types of Straight Turbine Cascades: Part 1 — A Stator Case
Authors: Yamamoto A. 
Published: April 2015

The present study intends to give some experimental information on secondary flows and on the associated total pressure losses occurring within turbine cascades.
Part 1 of the paper describes the mechanism of production and development of the loss caused by secondary flows in a straight stator cascade with a turning angle of about 65°. A full representation of superimposed secondary flow vectors and loss contours is given at serial fourteen traverse planes located throughout the cascade, which shows the mechanism clearly. Distributions of static pressures and of the loss on various planes close to blade surfaces and close to an endwall surface are given to show the loss accumulation process over the surfaces of the cascade passage. Variation of mass-averaged flow angle, velocity and loss through the cascade, and evolution of overall loss from upstream to downstream of the cascade are also given.
Part 2 of the paper describes the mechanism in a straight rotor cascade with a turning angle of about 102°.
More Effective Control for Centrifugal Gas Compressors Operating in Parallel
Authors: Staroselsky Naum , Ladin Lawrence 
Published: April 2015

Parallel Operating centrifugal gas compressors are major elements in the chemical industry, in oil production and in natural gas gathering, injection, separation, transmission and LNG production. Large energy savings, reduced repairs and improved automation are possible with more effective solutions for compressor station control.
The authors suggest an improved definition of compressor energy efficiency. They analyze several common approaches to control of parallel compressors and evaluate them in terms of energy efficiency, stability of control, equipment protection and level of automation. An improved system developed by one of the authors will be described theoretically and with an example from field operation.
Study and Experiments of a Small Radial Turbine for Auxiliary Power Units
Authors: Ribaud Y. , Mischel C. 
Published: April 2015

The design of a small inward flow turbine with a 3.6 expansion ratio has been undertaken by MICROTURBO, in cooperation with ONERA for calculations and test results analysis.
Initially, the purpose and constraints of this study are underlined. Preliminary calculations have led to the design of the blade shape of the Nozzle Guide Vane and of the rotor. Following this, the results of the quasi-3D-flow computations, performed for the stator and the rotor, are given. Both the cold bench tests on this turbine and the corresponding hot tests on the turboshaft engine enable performances to be checked. The value of the calculations is confirmed when we look at the high total and static adiabatic efficiencies obtained. These good results are encouraging for the future use of this kind of turbomachine.
Development of HIDEC Adaptive Engine Control Systems
Authors: Landy R. J. , Yonke W. A. , Stewart J. F. 
Published: April 2015

The NASA Ames-Dryden Flight Research Facility is sponsoring a flight research program designated Highly Integrated Digital Electronic Control (HIDEC), whose purpose is to develop integrated flight-propulsion control modes and evaluate their benefits in flight on the NASA F-15 test aircraft.
The Adaptive Engine Control System (ADECS I) is one phase of the HIDEC program. ADECS I involves uptrimming the P&W Engine Model Derivative (EMD) PW1128 engines to operate at higher engine pressure ratios (EPR) and produce more thrust. In a follow-on phase, called ADECS II, a constant thrust mode will be developed which will significantly reduce turbine operating temperatures and improve thrust specific fuel consumption.
A Performance Seeking Control mode is scheduled to be developed. This mode features an onboard model of the engine that will be updated to reflect actual engine performance, accounting for deterioration and manufacturing differences. The onboard engine model, together with inlet and nozzle models, are used to determine optimum control settings for the engine, inlet, and nozzle that will maximize thrust at power settings of intermediate and above and minimize fuel flow at cruise.
The HIDEC program phases are described in this paper with particular emphasis on the ADECS I system and its expected performance benefits. The ADECS II and Performance Seeking Control concepts and the plans for implementing these modes in a flight demonstration test aircraft are also described. The potential pay-offs for these HIDEC modes as well as other integrated control modes are also discussed.
Optimum Design Technique for Rotating Wheels
Authors: Hattori Toshio , Ohnishi Hiroo , Taneda Motoharu 
Published: April 2015

Compressor rotors and turbine rotors are subject to centrifugal and thermal loads. These loads increase proportionally with tip speed, pressure ratio and gas temperature. On the other hand, the rotor weight must be lessened to improve rotor dynamics and restrict bearing load. Thus, an optimum design technique is required, which offers the lighest possible wheel shape under the stress limit restriction.
This paper introduces an optimum design system developed for turbo machinery rotors, and discusses several application results. The sequential linear programming method is used in the optimizing process, and centrifugal and thermal stress analyses of variable thickness rotating wheels are performed using Donath’s method. This system’s validity is confirmed by application to uniform strength rotating disk problems and comparison with analytical results. This optimum design program is then applied to the design of axial flow compressor wheels.
Simulation of the Heat Transfer in a Gas Turbine Combustor Fueled With Coal-Water Mixture: Part 2 — Model Predictions and Experimental Data
Authors: Farag Ihab H. , Vaillancourt Joseph L. 
Published: April 2015

Data was obtained from the combustion of coal derived fuels in a 30 inch diameter, 4 foot long bench scale atmospheric unit fueled with CWF. The data is presented and compared with model predictions of ash, temperature, and mole fraction distributions.
A computer model was developed to simulate the heat transfer processes taking place in a gas turbine combustor (GTC) burning a coal water fuel (CWF). It is to predict the species and temperature distribution, the heat flux patterns, and the contribution of both convection and radiation to the total heat transfer rate. This model was verified in part 1 of this paper.
Aircraft/Engine Integration for an Advanced Fighter Considering Mission Specifics
Authors: Rauh G. , Anders W. 
Published: April 2015

In this paper propulsion system integration is considered for an advanced twin engined, high performance agile air to air fighter aircraft in view of its requirements for extreme flight conditions and maneuvers.
The propulsion system mainly consists of air inlets, engines and nozzle/afterbody systems.
The air inlet, a propulsion subsystem within the aircraft manufacturers responsibility, is physically well integrated with the aircraft flight control system, processing hardware being part of it.
The engine itself, as the most complex propulsion subsystem and not within the aircraft manufacturers responsibility, is to have very simple and clearly defined interfaces with the aircraft. Its integration must therefore be on this basis i.e. functional.
A central utility data bus allows for easy communication between the engine control system and all relevant aircraft systems through a single point interface in normal operation.
This improved communication allows for better performance, operation and handling of the engine.
A special feature of the propulsion system is the vectoring nozzle system with thrust deflection for maneuvers at high angles of attack beyond maximum lift. This system is also integrated with the flight control system.
User Interface Description of a Gas Turbine Control System
Authors: Sreetharan M. , Fistere J. 
Published: April 2015

Human factors must be given primary consideration in the design of today’s control systems. It is essential to take into account the characteristics of the human operator, the plant control requirements and the inherent characteristics of the control system.
This paper discusses the objectives of the control interface development task for a turbomachinery microprocessor based control system. It discusses the design issues raised during development, the choices made in the early structuring of the system and selected implementation details that affect the operator interface.
Subjects discussed include:
• Overall Philosophy and Console Arrangement
• Pushbutton vs Keyboard Functions
• Video Display Philosophy and Organization
• Ladder-Diagram Graphic Symbols
• Keyboard Command Philosophy and Structure
• Diagnostic Features and Maintainability