bluuebunny/crossref_metadata_2025_split huggingface dataset:
Operating Experience of the GT13E2 at Kawasaki Gas Turbine Research Center
Authors: Fujii Tatsuo , Uenaka Takakazu , Masuo Hitoshi 
Published: December 2014

The first Kawasaki-ABB GT13E2 gas turbine began operating at Kawasaki Gas Turbine Research Center (KGRC) in Sodegaura city, Japan in January 1994. This facility is a simple-cycle power station and is operated in DSS (Daily Start and Stop) operation mode as a peaking unit, and its output electricity is delivered to Tokyo Electric Power Company (TEPCO).
The GT13E2 gas turbine at KGRC was manufactured jointly by Kawasaki Heavy Industries (KHI) and Asea Brown Boveri (ABB). KHI and ABB have a joint test program with this facility to research for high reliability, high performance and low emission for the GT13E2 and future gas turbines.
The performance of the KGRC GT13E2 has been monitored continuously. It was found from these monitored data that the thermal efficiency has been maintained at a high level and could be recovered by compressor washing when the compressor was fouled.
Several factors which influence NOx emissions were studied on the gas turbine, and it was found that atmospheric humidity has a major influence on NOx emissions. Also other factor such as the position of the variable inlet guide vanes (VIGV) and fuel gas flow through each burner of the combustor were adjusted to reduce NOx emission. As a result, NOx emission from the KGRC GT13E2 has been maintained at a very low level.
Reliability, availability and maintainability (RAM) has been evaluated by Operational Reliability Analysis Program (ORAP®) of Strategic Power Systems, Inc. (SPS) in order to identify and improve RAM performance of the GT13E2 at KGRC. These analyses made it clear what kind of outage had an impact on the reliability, availability and starting reliability of the KGRC GT13E2 and appropriate actions have increased the starting reliability.
This paper describes operating experiences of the KGRC GT13E2 including performance, emissions and RAM performance.
Characterization of Deterministic Correlations for a Turbine Stage: Part 1 — Time-Averaged Flow Analysis
Authors: Bardoux Fabien , Leboeuf Francis , Dano Cédric , Toussaint Clément 
Published: December 2014

This paper analyses the flow in a transonic turbine stage, using time-dependent numerical results.
Unsteady blade-row interaction has repercussions on the time-averaged flow, which are represented by the so-called “deterministic correlations”. These correlations appear in the system of equations governing the time-averaged flow; they can be divided into four types with different physical meanings.
Time-dependent results enable direct computation of these correlations in both rotor and stator frames of reference. The computed deterministic correlations are analysed in the paper, in order to bind them to physical phenomena and to evaluate their influence on the time-averaged flow field.
This analysis is also intended to help assess the shortcomings of simple mixing-plane methods and more complex approaches using deterministic correlation models. While the first part focuses on one particular type of deterministic correlation, the so-called “spatial correlation”, the second part attempts a more detailed analysis of time-dependent results and gives some clues to the orders of magnitude of the four types of deterministic correlation. The conclusions should be taken with caution; they may partly depend on the present turbine configuration with a specified structure of unsteadiness and on the present turbulence model.
Characterization of Deterministic Correlations for a Turbine Stage: Part 2 — Unsteady Flow Analysis
Authors: Bardoux Fabien , Leboeuf Francis , Dano Cédric , Toussaint Clément 
Published: December 2014

The first part of this paper analysed the time-averaged flow in a transonic single stage turbine. In this second part, we analyse the three-dimensional unsteady flow and temporal correlations in the rotor frame of reference. Two main conclusions are deduced from the comparison of each correlation. First, all correlations have the same order of magnitude. This is an important conclusion for models that handle the interaction between blade rows, because the temporal correlations are usually neglected. Second, these correlations occur in complementary localizations. In particular, the largest values of spatial deterministic correlations is located between the nozzle trailing edge and the rotor leading edge, as a consequence of nozzle wakes. Conversely, temporal deterministic correlations are located within the rotor blade row.
We also establish that entropy accumulations in the stator wake near the end-wall regions generate high fluctuations of the rotor passage vortices. Such a phenomenon may have great repercussions on the radial loss distribution in the stage.
Development of the Ceramic Gas Turbine Engine System (CGT301)
Authors: Sakida Takeshi , Tanaka Shinya , Mikami Takao , Tatsuzawa Masashi , Taoka Tomoki 
Published: December 2014

The CGT301 ceramic gas turbine has been developed under a contract from NEDO as a part of the New Sunshine Program of MITI since 1988 to 1998.
The CGT301 is a recuperated, single-shaft ceramic gas turbine. Ceramic parts are used in the hot section of the engine, such as turbine blades, nozzle vanes, combustion liners and so on. As a primary feature of this turbine, the rotors are composed of ceramic blades inserted into metallic disks (“hybrid rotor”) for the future applicability to the large gas turbine.
The R & D program consists of three phases, the model metal gas turbine, the primary type ceramic gas turbine and the pilot ceramic gas turbine. The pilot ceramic gas turbine showed etable operation at TIT of 1,350°C.
This paper presents the progress in the development of the pilot ceramic gas turbine of CGT301.
A Comparative Exergy Analysis of Advanced Power Cycles Using Biomass Fuel
Authors: Codeceira Neto Alcides , Pilidis Pericles 
Published: December 2014

This paper describes a design point study of different power generation systems using the gasification of sugar cane bagasse, which produces a low calorific value fuel.
The biomass gasification is viewed as a process of drying the solid fuel and heating it up before the gasification reactions take place. The process is represented by equilibrium conditions. Varying pressure, temperature and feed composition in the gasifier controls the fuel gas composition.
Five alternative arrangements of an integrated gasification combined cycle (IGCC) power plant have been analysed using the exergy method. These alternatives comprise a combined gas / steam cycle using a simple gas turbine and also a reheat gas turbine, a combined gas / air cycle using a simple gas turbine and also a reheat gas turbine, and a combined gas / air / freon cycle using a reheat gas turbine.
The combined gas / steam cycles are more efficient rather than the combined gas / air cycles. Using a reheat gas turbine at the topping cycle of the combined cycles analysed contribute to increase the overall plant exergetic efficiency.
The exergy analysis has been carried out along with the performance assessment of power plants and takes into account the irreversibility of their components and the exhaust losses. The gasifier is the component of the power plant that destroys maximum exergy.
Three computer codes have been developed. One of them has the ability of simulating the thermodynamic properties of the low calorific value fuel in the gasification process and the other two are related to the performance analysis of the different power cycles using the exergy method.
The production of energy from the gasification of sugar cane bagasse has been of increasing importance to the Brazilian energetic matrix. This paper has been focused on the GEOPHILES - αlfa Programme, a project to train Latin America engineers on biomass gasification for power generation. The Commission of Energy of the European Community has supported this project.
Engine Condition Assessment Technology
Authors: Taylor Barry , Pagotto Ivano , Stewart Jeff 
Published: December 2014

The OEM, using a set of planned maintenance schedules that are based upon running hours or inspections, has traditionally formulated gas turbine maintenance practice. This maintenance concept has been reasonably successful, but it fails to take into account the introduction of new technologies than can provide the operator with a more meaningful insight into the condition of the turbine, perhaps even in a prognostic manner.
The application of computer based technology to gas turbine condition monitoring can provide a significant reduction in maintenance costs. At the same time, condition-monitoring technology can provide an improvement in reliability and availability by extending the maintenance intervals and reducing the number of unplanned outages.
This paper will discuss the introduction of an integrated approach to gas turbine control and engine condition assessment. This integrated approach enables the control to turn engine data into useful information and knowledge that assists the operator with trouble shooting and maintenance condition assessments thus lowering the overall engine maintenance costs.
Effects of Orientation Angles on Film Cooling Over a Flat Plate: Boundary Layer Temperature Distributions and Adiabatic Film Cooling Effectiveness
Authors: Jung In Sung , Lee Joon Sik 
Published: December 2014

Presented are experimental results describing the effects of orientation angle of film cooling holes on boundary layer temperature distributions and film cooling effectiveness. Film flow data were obtained from a row of five film cooling holes on a flat test plate. The inclination angle of the hole was fixed at 35° and four orientation angles of 0°, 30°, 60°, and 90° were investigated. The surveyed velocity ratios were 0.5, 1.0, and 2.0. The boundary layer temperature distributions were measured at three downstream locations using turn platinum wire. Detailed adiabatic film cooling effectiveness distributions were measured using thermochromic liquid crystal.
Results show that the increased lateral momentum in the case of large orientation angle injection strongly affects boundary layer temperature distributions. Temperature distribution characteristics are, in general, explained in the context of the interactions between injectant and free-stream fluid and between injectants issued from adjacent holes. The adiabatic film cooling effectiveness distributions are discussed in connection with the boundary layer temperature distributions. Spanwise-averaged effectiveness distributions and space-averaged effectiveness distributions are also presented with respect to the velocity ratios and the orientation angles.
On the Development and Application of the FRAP® (Fast-Response Aerodynamic Probe) System for Turbomachines: Part 1 — The Measurement System
Authors: Kupferschmied Peter , Köppel Pascal , Roduner Christian , Gyarmathy George 
Published: December 2014

This contribution gives an overview of the current state, performance and limitations of the fast-response aerodynamic probe measurement system (FRAP® System) developed at the Turbomachinery Lab of the ETH Zurich. In particular, the following topics are addressed:
• Probe technology: Miniature probes with tip diameter ranging from 0.84 to 1.80 mm (1-sensor and 3-sensor probes respectively) have been developed. New technologies derived from microelectronics and micromechanics have been used to achieve an adequate packaging of the microsensor chips used. Both the sensor packaging and the sensor calibration (time-independent and time-dependent) are crucial issues for the DC accuracy of any measurement.
• Aerodynamic probe calibration: The methods used for the sensor calibration and the aerodynamic probe calibration, the pertinent automated test facilities and the processing of the output data are briefly presented. Since these miniature probes are also capable of measuring the mean flow temperature, aspects related to the recovery factor and the self-heating of the probe tip are treated and some recommendations related to sensor selection are given.
• Measurement system and data evaluation: The early measurement chain described in Gossweiler, Kupferschmied and Gyarmathy 1995 has evolved into the FRAP® System. This automatic system incorporates dedicated measurement concepts for a higher accuracy and a more efficient operation in terms of time and failures. An overview of the data evaluation process is given.
The FRAP® System has been tested in real-sized turbomachines under industrial conditions within the temperature limits of 140°C imposed by the sensor technology (axial-flow turbofan compressor, axial-flow turbine, centrifugal compressor). These applications confirmed the potential of the system and encouraged its further development. Now, the system is routinely used in the facilities of the Turbomachinery Lab and in occasional measurement campaigns in other laboratories.
Part 2 of this contribution (Roduner et al.) will focus on the application of the FRAP® System in a transonic centri fugal compressor of the ETH Turbomachinery Laboratory, while Part 3 (Köppel et al.) treats more sophisticated data analysis methods.
Self-Sensing in Fault Tolerant Magnetic Bearings
Authors: Montie Dominick , Maslen Eric 
Published: December 2014

Several schemes have recently been proposed for achieving either fault tolerance or self-sensing in magnetic bearings. The present work describes the fundamental connection between ability to actuate and ability to sense in a partially failed magnetic bearing system. This relationship is then exploited to construct a self-sensing scheme which operates in the presence of detectable actuator or amplifier faults. Such an approach is advantageous in fault tolerant systems because it reduces or eliminates the need to address potential independent failure mechanisms in sensors and actuators.
Based on a model reference parameter estimation mechanism, the self-sensing scheme is shown to provide acceptable position measurement accuracy and bandwidth under various actuator/amplifier faults which are actuator tolerable. Estimates of increase in noise floor and loss of bandwidth under fault conditions are provided. The issue of estimator convergence under fault conditions is examined in detail with comments on implementation complexity arising from scheduling convergence control on fault state.
Unsteady Boundary Layer Transition on a High Pressure Turbine Rotor Blade
Authors: Tiedemann Maik , Kost Friedrich 
Published: December 2014

This investigation is aimed at the experimental determination of the location, the extent, and the modes of the laminar-to-turbulent transition processes in the boundary layers of a high pressure turbine rotor blade. The results are based on time-resolved, qualitative wall shear stress data which was derived from surface hotfilm measurements. The tests were conducted in the “Windtunnel for Rotating Cascades” of the DLR in Göttingen. For the evaluation of the influence of passing wakes and shocks on the unsteady boundary layer transition, a test with undisturbed rotor inlet flow was conducted in addition to full stage tests.
Two different transition modes led to a periodic-unsteady, multi-moded transition on the suction side. In between two wakes, transition started in the bypass mode and terminated as separated-flow transition. Underneath the wakes, plain bypass transition occurred. The weak periodic boundary layer features on the pressure side indicate that this surface was not significantly affected by passing wakes or shocks.
The acquired data reveals that the periodically disturbed suction side boundary layer is less susceptible to bubble bursting than the undisturbed flowfield. Thus, these blades may be subjected to higher aerodynamic loads. Accordingly, as in low pressure turbines, the unsteady effects in high pressure turbines may allow for a reduction of the number of rotor blades, with respect to the original design.
On the Development of Oxygen Scavenger Additives for Future Jet Fuels
Authors: Beaver B. , Sharief V. , Teng Y. , DeMunshi R. , Guo J. P. , Katondo E. 
Published: December 2014

The need for the development of jet fuels that are oxidatively and thermally stable to 480°C (900°F) has been previously detailed (Edwards and Liberio, 1996). Such a fuel is commonly referred to as JP-900. It is our belief that a new class of additives can be developed which, when added to JP-8, will provide both the oxidative and thermal stability requirements of JP-900.
Our most recent data is presented which explores the potential of 1,2,5-trimethylpyrrole (TMP) as a potential oxygen scavenger.
Deposit Formation and Mitigation in Aircraft Fuels
Authors: Spadaccini Louis J. , Sobel David R. , Huang He 
Published: December 2014

The development of a viable strategy for limiting coke deposition involves combining synergistic approaches for suppressing deposit buildup and reducing its impact on performance. Candidate approaches, including selection of favorable operating conditions (viz., pressure, temperature, heat flux, residence time and passage size) and coke-tolerant heat exchanger designs, were investigated to evaluate their effectiveness and provide a basis for combining them into a single design philosophy. These approaches were evaluated through testing of current jet fuels in single-tubes and segments of heat exchanger configurations at temperatures up to 1000 F, pressures up to 1200 psi and liquid hourly space velocities up to 40,000/h.
A key result of this work is the ranking of the importance of heat exchanger operating conditions on carbon deposition, with fuel temperature and those parameters that control species diffusion having the most pronounced impact. Residence time and pressure are of lesser importance. Alternative coke-tolerant heat exchanger designs featuring inter-channel communication were evaluated and ranked, with several of these concepts demonstrating improvement over continuous passages.
USN Land Based Testing of the WR21 ICR Gas Turbine
Authors: Parry Robin W. , House Edward , Stauffer Matthew , Iacovelli Michael , Higgins William J. 
Published: December 2014

Development of the Northrop Grumman / Rolls-Royce WR21 Intercooled Recuperated (ICR) Gas Turbine, begun in 1992, is now well advanced and system testing has been completed on eight engine builds at the Royal Navy’s Admiralty Test House located at the Defence Evaluation and Research Agency, Pyestock in the United Kingdom. Test activity is shortly to move to the US Navy’s Test Site at the Naval Surface Warfare Center, Carderock Division – Ship Systems Engineering Station in Philadelphia, PA, where a new test facility has been built to carry out some final development testing and an endurance test. A previous paper on this subject (94-GT-186) defined a test program leading to a design review and the beginning of Qualification Testing.
The development program has since evolved and it is the aim of this paper to summarize engine testing to date and set out the plan for conclusion of development testing. The paper will describe the development of the Philadelphia Test Site, as a combined site for the US Navy’s Integrated Power System (IPS) and ICR testing. This will include a description of the advanced, high-accuracy Data Acquisition System (DAS). Finally, the test program and the development and endurance test objectives will be outlined.
Compressor Exit Conditions and Their Impact on Flame Tube Fuel Injector Flows
Authors: Barker A. G. , Carrotte J. F. 
Published: December 2014

Within a gas turbine engine the flow field issuing from the compression system is non-uniform containing, for example, circumferential and radial variations in the flow field due to wakes from the upstream compressor outlet guide vanes (OGVs). In addition, variations can arise due to the presence of radial load bearing struts within the pre-diffuser. This paper is concerned with the characterisation of this non-uniform flow field, prior to the combustion system, and the subsequent effect on the flame tube fuel injector flows and hence combustion processes.
A mainly experimental investigation has been undertaken using a fully annular test facility which incorporates a single stage axial flow compressor, diffuser and flame tube. Measurements have been made of the flow field, and its frequency content, within the dump cavity. Furthermore, the stagnation pressure presented to the core, outer and dome swirler passages of a fuel injector has been obtained for different circumferential positions of the upstream OGV/pre-diffuser assembly. These pressure variations, amounting to as much as 20% of the pressure drop across the fuel injector, also affect the flow field immediately downstream of the injector. In addition, general variations in pressure around the fuel injector have also been observed due to, for example, the fuel injector position relative to pre-diffuser exit and the flame tube cowl.
Ingress Determination by Means of Laser Light Scattering Inside a Rotor-Stator System
Authors: Geis T. , Wiebelt A. , Kim S. , Wittig S. 
Published: December 2014

A new method based on laser light scattering was developed to detect a radial inflow of gas inside a rotating-disk system. Ambient air was seeded with small particles that followed the flow. Once entering the wheel space between rotor and stator, these particles crossed a laserbeam emitted by an At+-Laser. The scattered light was detected by a photomultiplier whose electrical output signal was finally processed in a data acquisition system. The signal intensity thereby indicated the strength of ingress.
The measuring technique was adapted to a shrouded rotor-stator system in a quiescent environment and an experimental investigation was conducted to determine the minimum cooling flow rate necessary to just prevent ingress (Cw,min) for several seal clearance ratios and two different rotor disk geometries. The results were correlated to the disk rotational Reynolds number and compared with data yielded by applying a pressure criterion. With the rotating disk being 0.5m in diameter and spinning at max. 10000rpm, rotational Reynolds numbers up to 3.8×106 were achieved. The results show an expected behaviour for the seal clearance variation and an unexpected behaviour for the two disk geometries. Compared to the new technique, the pressure criterion underestimates the minimum purge flow. Additional experiments were conducted for a single seal configuration to demonstrate the new method’s capability to acquire the sealing effectiveness. The results are intriguing but also show that further investigations must be conducted to establish this new technique.
Influence of Internal Flow on Film Cooling Effectiveness
Authors: Wilfert Günter , Wolff Stefan 
Published: December 2014

Film cooling experiments were conducted to investigate the effects of internal flow conditions and plenum geometry on the film cooling effectiveness. The film cooling measurements show a strong influence of the coolant inlet conditions on film cooling performance. The present experiments were carried out on a flat plate with a row of cylindrical holes oriented at 30 degrees with respect to a constant-velocity external flow, systematically varying the plenum geometry and blowing rates (0.5≤M≤1.25). Adiabatic film cooling measurements using the multiple narrow-banded Thermochromic Liquid Crystal-technique (TLC) were carried out simulating a flow parallel to the main stream flow with and without cross flow at the coolant hole entry compared with a standard plenum configuration. An impingement in front of the cooling hole entry with and without cross flow was also investigated. For all parallel flow configurations ribs were installed at the top and bottom coolant channel wall. As the hole length-to-diameter ratio has an influence on the film cooling effectiveness, the wall thickness has also been varied. In order to optimise the benefit of the geometry effects with ribs, a vortex generator was designed and tested.
Results from these experiments show in a region 5≤X/D≤80 downstream of the coolant injection location differences in adiabatic film cooling effectiveness between +5% and +65% compared with a standard plenum configuration.