bluuebunny/crossref_metadata_2025_split huggingface dataset:
An Overview of International Electrical and Safety Codes and Standards Governing the Application of Turbomachinery in Hazardous Areas
Authors: Kidd H. Allan , Talabisco George 
Published: February 2015

A plethora of codes, standards, and guidelines exist throughout the world offering a significant amount of input for the design engineer as he attempts to safely apply hydrocarbon processing equipment to hazardous areas. Fire suppression standards generated in and applicable to use in North America are also used throughout Europe. Off shore techniques are more stringent and must be carefully followed to protect the owner’s investment and for the safety of the equipment operators.
This paper is a digest of all internationally recognized codes issued through commonly employed authorities extracting the peculiarities from each and building upon some basic premises to form a design specification that can be modified to suit the specific application or individual company policies.
The discussion will be limited to enclosed and unenclosed gas turbine drivers and hydrocarbon gas processing compressors. Indoor and out door installations of this type equipment will also be considered.
Spa “Mashproekt” Combined Cycle Plants
Authors: Kovalenko A. V. , Belyayev F. F. , Lazarev V. V. , Lupandin V. V. 
Published: February 2015

The paper describes the history of design, development and 15 years’ sea-going experience of the MASHPROEKT combined cycle plants.
Four R060 type ships powered by eight combined cycle plants each rated at. 25.000 h.p. and three naval ships with six cruise combined cycle plants each rated at. 10, 000 h.p. are in service now. Using of combined cycle permitted to increase their thermal efficiency by 20–30 per cent.
To increase efficiency at a speed of 15…18 knots, a special mode of operation is used: the gas turbine and waste heat boiler operate at one board and steam generated by this waste heat boiler is used for a steam turbine of other board. Total operation life of all marine gas turbine units exceeds 330,000 hours.
A Catalytic Combustor for High-Temperature Gas Turbines
Authors: Vortmeyer Nicolas , Valk Martin , Kappler Günter 
Published: February 2015

Catalytic combustion has been the subject of thorough research work for over two decades, mainly in the U.S. and Japan. However, severe material problems in the ceramic or metallic monolith prevented regular operation in most cases. Still, during these two decades, turbine inlet temperatures were raised remarkably, and lean premix combustors have become standard in stationary gas turbines.
In view of these facts, a simple “monolith-in-tube” concept of a catalytic combustor was adapted for the use in high-temperature gas turbines. Its essential feature is the fact that a considerable portion of the homogeneous gas phase reaction is shifted to the thermal reactor, thus lowering the catalyst temperature. This is achieved by the employment of very short catalyst segments. The viability of this concept has been demonstrated for a variety of pure hydrocarbons, alcohols as well as common liquid fuels.
Extensive experimental investigations of the atmospheric combustor lead to the assessment of parameters such as reference velocity, fuel-to-air ratio and fuel properties. The maximum combustor exit temperature was 1,673 K with a corresponding catalyst temperature of less than 1,300 K for Diesel fuel. Boundary conditions were in all cases combustion efficiency (over 99.9%) and pressure loss (less than 6%).
Additionally, a model has been developped to predict the characteristic values of the catalytic combustor such as necessary catalyst length, combustor volume and emission characteristics. The homogeneous reaction in the thermal reactor can be calculated by a one-dimensional reacting flow model.
Dynamic Constraints on HRSG Drum Design
Authors: Galopin J.-F. 
Published: February 2015

Heat Recovery Steam Generator start-ups are most often thought of as being a delicate step in the pressurization of the boiler, as are trips and shutdowns. One reason for this is the so-called swell effect and the problems which can arise when this event occurs while another might be the different controls that have to be monitored at the same time. A dynamic software is actually used by Cockerill Mechanical Industries (C.M.I.) to simulate the behaviour of all significant thermodynamic variables of the system as well as the temperatures of the materials, and typical control variables versus time.
During the development of this software, special care has been given to the study of the influence of the vaporizer pressure drop on the temperature and pressure gradient at the inlet of the drum, where critical thermal and mechanical stresses might appear. The circulation pump specifications have been taken into account. A discussion is presented in order to measure the influence of this pressure drop on the highest observed stresses during the swell effect as well as the pressure gradient used during the pressurization on the fatigue analysis of the drum and its nozzles. Their design is then briefly overviewed using two methods of calculations.
System Optimization of Humid Air Turbine Cycle
Authors: Xiao Yunhan , Lin Rumou , Cai Ruixian 
Published: February 2015

The humid air turbine (HAT) cycle, proposed by Mori et al. and recently developed by Rao et al. at Flour Daniel, has been identified as a promising way to generate electric power at high efficiency, low cost and simple system relative to combined cycle and steam injection gas turbine cycle. It has aroused considerable interest.
Thermodynamic means, such as intercooling, regeneration, heat recovery at low temperature and especially non-isothermal vaporisation by multi-phase and multi-component, are adopted in HAT cycle to reduce the external and internal exergy losses relative to the energy conversion system. In addition to the parameter analysis and the technical aspect of HAT cycle, there is also a strong need for “systems” research to identify the best ways, of configuring HAT cycle to integrate all the thermodynamic advantages more efficiently to achieve high performance.
The key units in HAT cycle are analyzed thermodynamically and modelled in this paper. The superstructure containing all potentially highly efficient flowsheeting alternatives is also proposed. The system optimization of the HAT cycle is thus represented by a nonlinear programming problem. The problem is solved automatically by a successive quadratic algorithm to select the optimal configuration and optimal design parameters for the HAT cycle.
The results have shown that the configuration of the HAT cycle currently adopted is not optimal for efficiency and/or specific power, and the current pressure ratio are too high to be favorable for highest performance. Based on the current technical practice, the optimal flowsheeting for thermal efficiency can reach 60.33% when TIT=1533K, while the optimal flowsheeting for specific power can achieve 1300kW/kg/s air for TIT at 1533K. The optimal flowsheeting configuration is compared favorably with the other existing ones.
Experimental Investigation of Rotor/Rotor Interaction in a Hydrodynamic Torque Converter Using Hot-Film Anemometry
Authors: Browarzik Volker 
Published: February 2015

Unsteady flow measurements were performed to investigate the internal flow field of a torque converter, especially unsteady rotor/rotor-interaction in the region between pump exit and turbine inlet.
Instantaneous flow data were measured with hot-film probes and a computer based data acquisition system. The commonly used ensemble averaging method was adapted to this special case with two independently rotating impellers.
Velocity profiles of the flow in the relative frame of reference of the pump impeller were evaluated and they were used to generate a computer animation.
The paper gives an overview over the test facilities and the background of the present investigations. It follows a discussion of some essential aspects concerning the use of hot-film anemometry. The methods used to evaluate the data are described in detail and measuring results of the region between pump exit and turbine inlet are presented.
Use of Computer Simulation Techniques to Assess Thrust Rating as a Means of Reducing Turbo-Jet Life Cycle Costs
Authors: Devereux B. , Singh R. 
Published: February 2015

This paper investigates the concept of thrust rating as a means towards reducing the life cycle costs of turbo-jet engine ownership. Towards this end, the concepts of life usage and thrust rating will be discussed to provide a clear understanding of the goals and methods involved in this investigation. In general, all “serviceable” engines will experience varying levels of performance above baseline values. Thrust rating ideally seeks to limit engine performance to baseline values, thereby converting performance into life.
In particular, this paper will present a general computer simulation technique that may be applied to any turbo-jet engine to quantify the life cycle savings resulting from the adoption of thrust rating techniques. The inter-relationships that exist between thrust rating and many practical in-service aspects of turbo-jet usage including performance degradation, operational roles and maintenance practices and policies will be investigated. Some strengths and limitations of the simulation technique will also be identified. This paper will discuss general guidelines for investigating the feasibility of performing thrust rating on various turbo-jet engines. While this technique is likely to be of greatest interest to users of high performance military turbo-jet engines, its principles can be adapted for other gas turbine uses.
Influence of Inlet Conditions on Flow and Combustion Characteristics of a Model Annular Combustor
Authors: Baron F. , Kanniche M. , Mechitoua N. 
Published: February 2015

k-ε model coupled with chemical equilibrium hypothesis is applied to a sector of an annular gas turbine combustion chamber similar to the one used in small gas turbine engines. The β-function is used as probability-density-function (pdf) of the distribution of a mixing rate scalar. The computation results are compared with velocity, temperature and species concentration measurements with air-to-fuel ratio of 29 and two inlet air temperatures of 315 K and 515 K. The measurements are reported in the PhD thesis of Tse [2] and in Bicen et al. [1].
Computed velocity and temperature are in good agreement with measurements, except close to primary injection holes where the normal impacts of air jets with the bulk flow involve strong streamline curvature which cannot be well predicted by standard k-ε model.
Computed species concentrations are in good agreement with measurements, except (as expected) for CO concentration which is overestimated. Since the kinetic of CO burn-up is limited, the overestimation of CO concentration is a consequence of the simplified chemical reaction step.
Aerodynamic Performance of a Transonic Turbine Guide Vane With Trailing Edge Coolant Ejection: Part I — Experimental Approach
Authors: Kapteijn Cornelis , Amecke Jochen , Michelassi Vittorio 
Published: February 2015

Inlet guide vanes (IGV) of high temperature gas turbines require an effective trailing edge cooling. But this cooling influences significantly the aerodynamic performance caused by the unavoidable thickening of the trailing edge and the interference of the cooling flow with the main flow.
As part of a comprehensive research programme an inlet guide vane was designed and manufactured with two different trailing edge shapes. As a general result turns out from the cascade tests, that the flow behaviour upstream of the trailing edge remains unchanged. The homogeneous values downstream show higher turning and higher losses for the cut-back blade, especially in the supersonic range. Additional test were conducted with carbon dioxide ejection, in order to analyse the mixing process downstream of the cascade.
High-Performance Power Systems for the Near-Term and Beyond
Authors: Klara Julianne M. 
Published: February 2015

Demand for electricity in the United States is expected to grow in the foreseeable future, requiring approximately 200 gigawatts of new generating capacity by 2010. Coal-based power plants built to supply this additional baseload capacity will be required to perform at high thermal efficiency and meet tough environmental regulations, all at competitive electric generating costs. The Department of Energy (DOE) / Pittsburgh Energy Technology Center (PETC) is managing a program called Combustion 2000 that is aimed at developing technologies that will assure the continued use of coal to meet the Nation’s power generating needs well into the 21st century. The High-Performance Power System (HIPPS) element of Combustion 2000 is based on an indirectly fired combined cycle. By using an indirectly fired gas turbine and a conventional steam cycle, HIPPS cleanly produces electricity from coal at a thermal efficiency that is about one-third higher than that of today’s conventional coal-based power plants.
DOE/PETC’s HIPPS program, which is described in this paper, aims to demonstrate a commercial-scale prototype plant by 2004. An engineering analysis was performed to assess the feasibility of accelerating the demonstration of HIPPS by using only those materials available today. Results predict attractive efficiencies and competitive electric generating costs for a near-term design. The feasibility of HIPPS as a repowering option has also been examined. Preliminary projections reveal that added generating capacity and reduced emissions can be accomplished at an increased overall plant efficiency and with the potential to minimize capital expenditure.
Turbine Engine Icing Spray Bar Design Issues
Authors: Bartlett C. Scott 
Published: February 2015

Techniques have been developed at the Engine Test Facility (ETF) of the Arnold Engineering Development Center (AEOC) to simulate flight through atmospheric icing conditions of supercooled liquid water droplets. Ice formed on aircraft and propulsion system surfaces during flight through icing conditions can, even in small amounts, be extremely hazardous. The effects of ice are dependent on many variables and are still unpredictable. Often, experiments are conducted to determine the characteristics of the aircraft and its propulsion system in an icing environment. Facilities at the ETF provide the capability to conduct icing testing in either the direct-connect (connected pipe) or the free-jet mode.
The requirements of a spray system for turbine engine icing testing are described, as are the techniques used at the AEDC ETF to simulate flight in icing conditions. Some of the key issues facing the designer of a spray system for use in an altitude facility are identified and discussed, and validation testing of the design of a new spray system for the AEDC ETF is detailed. This spray system enables testing of the newest generation of high-thrust turbofan engines in simulated icing conditions.
Rotational Noise Analysis and Prediction for an Axial Fan With Unequal Blade Pitches
Authors: Akaike S. , Kikuyama K. , Kitada M. , Kuwayama K. 
Published: February 2015

The rotational noise is one of the main sources of the noise emitted from a fan. This type of noise has discrete frequency components, which is so harsh that many methods have been developed to reduce the noise. Studies on the rotational noise, however, have hardly been made to clarify the generation mechanism and find concrete methods to reduce the noise.
In order to suppress the discrete frequency components of the rotational noise, the spacing of the blades were changed and the comparison was made with a fan having equally spaced blades. The discrete frequency components were found to be suppressed in the unequally spaced fan and the noise tended to have a nature of whitenoise if the blade spacing and blade setting angles were properly chosen.
The instantaneous pressure change on the shroud was measured in order that the pressure change was related to the discrete frequency noise was closely related to the pressure changes on the blade surfaces. By expressing the pressure change due to the blade passing in terms of the blade spacing and decomposing it into Fourier series, the noise characteristics was analyzed. The prediction result for the rotational noise emitted by an equally spaced fan was presented and found to agree well with the experiment.
The Flow Through an Annular Turbine Nozzle With Nonuniform Pitch
Authors: Kurz Rainer 
Published: February 2015

This paper discusses flow measurement results both upstream and downstream of a transonic annular turbine nozzle with a nonuniform pitch. The downstream measurements are performed in the plane, where the leading edge of the rotor is located in the gas turbine.
The experiments were performed using total pressure probes and static wall pressure taps.
This type of nonuniformity creates a different behavior of the flow field both upstream and downstream of the blades. The effects on the wakes and on the inviscid flow are discussed separately.
The mean velocities show a strong sensitivity to the changes of the pitch, which is identified as a potential flow effect by using a simple vortex model.
Numerical Simulation for Aeroelasticity in Turbomachines With Vortex Method
Authors: Wu Wenquan , Sisto F. 
Published: February 2015

A new method for quantitatively predicting the interaction between the unsteady aerodynamics and structural dynamics was developed. The unsteady flow with large scale separation is simulated numerically with the developed Discrete Vortex Method. In this calculation process, the instantaneous unsteady force and moment of force acting on the blades can be obtained at each time step. On other hand, the cascade is considered as an elasticity system with damping including the effects of the interblade phase angle. The blades are excited to vibrate by the unsteady force and moment. To deal with the above two respects, the resulting code consists of two basic subprograms which exchange their data between each other at every computational time step and the non-linear problem is then solved in a time-marching discrete continuation fashion.
A series of numerical tests are presented including the parameters studies, such as: effects of the damping, incidence etc. For each case, a large number of computational steps is intended to provide sufficient information about the non-linear behavior of the stall flutter. The applicability of the method is demonstrated numerically.
Nuclear Gas Turbine Plant (GT-MHR) Performance Potential
Authors: McDonald Colin F. , Etzel Klaus T. 
Published: February 2015

With the current hiatus in the U.S. nuclear industry it is projected that by the year 2010 combustion gas turbines will be generating more electrical power than light water reactors. These units, operating at high firing temperature, and with advanced thermodynamic cycles, will have efficiencies of over 60%. In this era these gas turbines will operate with fossil-fuels (i.e., natural gas and gasified coal), but as environmental concerns intensisy there will be a quest for “greener technologies,” and this is where the gas turbine modular helium reactor (GT-MHR) will play a major role.
Utilizing a high temperature gas-cooled reactor and a closed helium Brayton cycle, a plant efficiency of 47% is projected based on the use of proven technology, and the initial unit could be in utility service by the year 2005. Following penetration of the market place, efforts will be expended to exploit the performance potential of the GT-MHR. In this paper the potential for efficiency advancement to 60% or higher is discussed, together with the technologies necessary for this to be realized, perhaps two decades after the operation of the pioneer plant. Such a power plant, that is compatible with the environment, and operating with an indigenous fuel source (i.e., uranium) could be in service through the first century of the next millennium.
Performance Analysis of Combined Cycles: Steam Recompression vs Conventional Bottoming Cycles
Authors: Grimaldi Carlo N. , Desideri Umberto 
Published: February 2015

A performance analysis was fulfilled to compare the steam recompression with the conventional single- and dual-pressure bottoming cycles. The optimal parameters for each cycle were found in order to maximize the exergetic efficiency. Heat transfer surface was also calculated to show the differences in the size of the heat recovery steam generator which have a direct influence on the plant’s costs.
The optimal configurations for each cycle were also studied when steam injection is employed. The relative performance when steam extraction is varied between 0 and 20% of the gas turbine’s compressor inlet mass flow rate, was also examined.
An Alternative Thermal Spray Process to Plasma Spray in the Aircraft and Stationary Gas Turbine Industry
Authors: Zwetsloot Menno P. , Sampson Elliott R. 
Published: February 2015

Technological advances in arc spray have produced an arc spray system that competes very favorably with other thermal spray processes. In the past arc spray was thought of as a process for very large parts that need thick buildups. However, an attachment device has been developed which focuses the pattern and accelerates the particles and is known as the Arc Jet system. The advantages of this device were discussed by Zwetloot, Sampson and Thorpe (1993), Reference 4.
This attachment device coupled with the introduction of metal cored wires that provide the same chemistries as plasma sprayed powders, provides application engineers with a viable economic alternative to existing spray methods.
A comparative evaluation of a standard production plasma spray system was conducted with the arc spray process utilizing the device mentioned above. This evaluation was conducted by an airline company on four major parts coated with nickel aluminum and results show that, for those applications, the arc spray process demonstrated significant benefit. It is expected that other applications may benefit from the use of the arc spray process as well.
Design Point Simulation of Multispool Industrial Compressor Trains
Authors: Blendulf Lars J. , Smith Graham D. 
Published: February 2015

Software commonly used to predict Aeroengine performance has been adapted for the design point simulation of two large industrial compressor sets. A NOx gas compressor and an air compressor on a common shaft driven by a steam turbine and a tail gas turbine are modelled accurately after the inclusion of both exothermic and endothermic reactions in the NOx gas compressor. Experiment and theory agree to within 1.5%.
Results for the simulation of a three spool Ammonia Synthesis compressor with a deliver pressure of 207 bar agree to within 1% of experimental data. Since complex gas mixtures were used, Mollier diagrams or Compressibility factor techniques were not used and, instead, Departure Function theory was adopted to accommodate the real gas behaviour found at the high pressure.
Current and Future Materials in Advanced Gas Turbine Engines
Authors: Kool G. A. 
Published: February 2015

Gas turbine engines are constructed of components with excellent strength and stiffness, a minimum density, a high temperature capability for long times, and at affordable cost. Metallic materials are the centrepiece in fulfilling these requirements. Future gas turbine engines will have to have higher thrust-to-weight ratios, better fuel efficiencies and still lower costs. This will require new and advanced lightweight materials with higher temperature capabilities.
This paper discusses some of the presently applied materials in the fan, compressor and turbine sections of gas turbines, and reviews the material developments that are occurring and will be necessary for the near and long term futures.