bluuebunny/crossref_metadata_2025_split huggingface dataset:
Heat Transfer Measurements on Turbine Airfoils Using the Naphthalene Sublimation Technique
Authors: Häring M. , Bölcs A. , Harasgama S. P. , Richter J. 
Published: February 2015

Results of heat transfer measurements on a typical turbine blade and a vane in a linear cascade have been obtained using the naphthalene sublimation technique. The tests on the vane were performed at the nominal flow angle, whereas for the turbine blade an off-design angle was chosen to study the influence of a separation bubble on the heat transfer. The exit Mach number was varied from M2=0.2 to 0.4 and the exit Reynolds number ranged from Re2= 300000 to 700000. Comparisons with numerical codes have been conducted.
The measurements were performed in a linear test facility containing five airfoils. Two tailboards and two bypass vanes allowed to achieve a good periodicity of the flow. The aerodynamic flow conditions were measured using pressure taps and Laser-Two-Focus (L2F) anemometry. About forty static pressure taps gave a precise Mach number distribution over the suction and the pressure side of the airfoil. L2F measurements were used to determine the downstream flow angles.
The heat transfer coefficient was measured using the naphthalene sublimation technique. This method is based on the heat and mass transfer analogy for incompressible flow. A 0.5 mm thin naphthalene layer was applied to the middle airfoil and exposed to the flow for about 45 minutes. The sublimation was then measured in over 500 points on the airfoil, which allowed a high resolution of the heat transfer coefficient. Due to its high resolution, the sublimation technique shows the presence of and the precise location of the laminar-to-turbulent transition point and the separation bubble.
The measurements on the vane were compared with two separate two-dimensional boundary layer programs, which were TEXSTAN (Texas University) and TEN (Sussex University). The programs incorporate the k-epsilon turbulence model with several different formulations. The laminar-turbulent transition was predicted quite well with TEN, which slightly damps out the production of turbulent kinetic energy in order to ensure a smooth transition zone. In the case of the blade, the naphthalene sublimation technique was able to predict the size and the location of the separation bubble as well as the reattachment with a very high precision.
The Highly Nonlinear Thermal Behavior of Film Cooling
Authors: Adiutori Eugene F. 
Published: February 2015

The current view of film cooling/heating behavior is largely the result of room temperature experiments in which the high temperatures typical of gas turbines were only simulated. The simulation rests on the assumption/deduction that the effect of temperature on film cooling behavior is due solely to the effect of temperature on fluid density.
A few experiments reported in the literature have included wide variation in temperature. In this article, the data from several of these are examined in order to determine the actual, observed effect of temperature on film cooling behavior.
Literature data exhibit a highly linear relationship between Taw and Tfc when the film is injected through a slot, and Tfc/Tms lies in the range 0.8 to 1.27. The data also indicate that this relationship is highly nonlinear when Tfc/Tms is less than approximately 0.8. The nonlinearity is so pronounced that Taw may not decrease even though (Tfc/Tms) is decreased from 0.57 to 0.35.
Nonlinearity in the relationship between Taw and Tfc has a major impact on optimum system design whenever the thermal designer has design control over the film coolant temperature.
Marinized Industrial Gas Turbine for HSLC Marine Propulsion
Authors: Waldhelm Chris M. 
Published: February 2015

Advancements in high speed, light craft (HSLC) sea transportation require a main propulsion system that provides relatively high specific power with a minimum of weight/space. For commercial operations, the economics of the propulsion system are considered a key criterion in power plant selection. Marinizing a durable second generation industrial gas turbine, like the Solar Taurus® marine gas turbine, is ideally suited to satisfy the combination of the high vessel speed objective and the operating cost economic justification of commercial HSLC.
Since the Taurus gas turbine has evolved from an earlier marine propulsion gas turbine and is in offshore platform service using materials and coatings resistant to marine environments, certification for marine prime propulsion concentrated primarily on operating inclination dynamic loading and the interfaces with the auxiliary support systems.
With its high power to weight ratio, reliable performance, competitive first cost, and low operating costs, the Taurus marine industrial gas turbine can be further enhanced by recuperation and variable nozzle designs improving specific fuel consumption and part load efficiencies beyond other alternatives.
Mars SoLoNOx: Lean Premix Combustion Technology in Production
Authors: Etheridge C. J. 
Published: February 2015

Solar Turbines has applied it’s SoLoNOx lean premix combustion technology to the Mars 100S (10.5 MW, 14,100 hp ISO) and Mars 90S (9.4 MW, 12600 hp ISO) gas turbine engines and now offers engines with guaranteed NOx and CO emissions less than 42 and 50 ppmv respectively and with near term expectations of offering NOx emissions below 25 ppmv when operating on natural gas fuels. The development has been ongoing since January 1990 and includes a field demonstrator engine which is running on a gas pipeline in the North West of USA.
This paper introduces the basic design of the Mars SoLoNOx combustion system and presents some of the unique characteristics found with this lean premix technology during the program.
The Capability of Different Semianalytical Equations for Estimation of NOx Emissions of Gas Turbines
Authors: Becker T. , Perkavec M. A. 
Published: February 2015

The NOx emissions of gas turbines are depending on different influences. On the one side there are the effects fixed by the gas turbine design and on the other side the ambient effects, the fuel properties and the operational conditions.
Because the NOx emissions are difficult to calculate by chemical reactions and flow calculations, some investigators developed semianalytical equations, which in their opinion contained the most important influencing factors together with some tuning factors for the actual gas turbine design and application.
This paper shows the capability of those procedures, including a new one. It compares the calculated NOx emission with measured data. The comparisons were made for one gas turbine fired with different fuels (natural gas, propane, butane, coke oven gas), as well as for different combustor inlet conditions in case of simple and regenerative cycle operation. Reference is made also for some other gas turbine models. Also full and part load operation as well as the steam injection effects are included.
A Numerical Method for the Prediction of Bladed Disk Forced Response
Authors: Berthillier Marc , Dhainaut Marc , Burgaud Franck , Garnier Vincent 
Published: February 2015

A numerical method has been developed to predict the forced response of bladed disks due to a wake excitation from upstream blade rows. The structure is modelled by a 3D finite element mesh of a bladed disk segment. Using cyclic symmetry, this model provides a modal base for the rotating structure. The aerodynamic damping of the vibratory modes and the excitation pressures on the blades due to the propagation of upstream flow defects are computed separately using the same 3D unsteady Euler analysis software. A modal response solution of the aeromechanical system is then performed.
This analytical methodology has been used to study the forced response of an experimental high pressure compressor blisk. The results are analysed and compared with actual rig tests.
The Feasibility of Heat Pipe Turbine Vane Cooling
Authors: Silverstein Calvin C. , Gottschlich Joseph M. , Meininger Matthew 
Published: February 2015

This paper evaluates the basic feasibility and anticipated benefits to using heat pipe technology to cool the turbine vanes of gas turbine engines.
This concept involves fitting out the vane interior as a heat pipe, extending the vane into an adjacent heat sink and then transferring the vane incident heat through the vane to the heat sink. The baseline is an advanced military fighter engine and the bypass air is the chosen heat sink. The results of this study show a 7.2% increase in engine thrust, a 0.2% decrease in specific fuel consumption with engine weight increased by less than 1% by using this technology.
FT8-55 Mechanical Drive Aeroderivative Gas Turbine: Design of Power Turbine and Full-Load Test Results
Authors: Aschenbruck E. , Blessing R. , Turanskyj L. 
Published: February 2015

A new, highly efficient 25-MW aero-derivative gas turbine, model FT8-55, has been developed for mechanical drive applications as a member of the FT8 gas turbine family which also includes two generator drive gas turbines, models FT8-30 and FT8-36, with power turbine speeds of 3000 rpm and 3600 rpm, respectively. For the new mechanical drive version FT8-55, the power turbine can be operated up to 5775 rpm at maximum continuous speed. All power turbines are equipped with gas generators, model GG8-1, which are derived from the most popular aero-engine in civil aviation, the JT8D.
The first part of this paper describes design features, rotor dynamics, and material selection for the three-stage power turbine PT8-55. Rotor design permits unrestricted operation in the speed range from 2500 rpm up to maximum continuous speed.
The first FT8-55 gas turbine was subjected to mechanical and performance workshop tests at different speeds and power outputs up to full-load.
The second part of the paper deals with the description of the test stand arrangement for testing complete gas turbine packages as well as measurement techniques and data evaluation. Power was absorbed by a two-stage pipeline compressor, equipped with magnetic bearings and dry gas seals, which was operated in a closed loop. Thermodynamic and mechanical test results at various speeds and loads provide evidence of a highly efficient and mechanically robust gas turbine for mechanical drive applications.
Low NOx Premixed Combustion of MBTU Fuels Using the ABB Double Cone Burner (EV Burner)
Authors: Döbbeling K. , Knöpfel H. P. , Polifke W. , Winkler D. , Steinbach C. , Sattelmayer T. 
Published: February 2015

A novel combustion technique, based on the Double Cone Burner, has been developed and tested. NOx emissions down to very low levels are reached without the usual strong dilution of the fuel for MBtu syngases from oxygen blown gasification of coal or residual oil. A limited amount of dilution is necessary in order to prevent ignition during the mixing of fuel and combustion air.
The relevant properties of the fuel are reviewed in relation to the goal of achieving premixed combustion. The basic considerations lead to a fuel injection strategy which is completely different from that for natural gas. A high speed premixing system is necessary due to the very short chemical reaction times of MBtu fuel. Fuel must be prevented from forming ignitable mixtures inside the burner for reliability reasons. A suitable fuel injection method, which can be easily added to the ABB double cone burner, is described. In common with the design of the standard EV burner, the MBtu EV burner with this fuel injection method is inherently safe against flashback.
Three dimensional flow field and combustion modelling is used to investigate the mixing patterns and the location of the reaction front. Two burner test facilities, one operating at ambient and the other at full gas turbine pressure, have been used for the evaluation of different burner designs. The full pressure tests were carried out with the original gas turbine burner size and geometry. Combing the presented numerical predictive capabilities and the experimental test facilities, burner performance can be reliably assessed for a wide range of MBtu and LBtu fuels (residue oil gasification, waste gasification, coal gasification etc.).
The atmospheric tests of the burner show NOx values below 2 ppm at an equivalence ratio equal to full load gas turbine operation. The NOx increase with pressure was found to be very high. Nevertheless, NOx levels of 25 vppmd (@ 15% O2) have been measured at full gas turbine pressure. Implemented into ABB’s recently introduced gas turbine GT13E2 the new combustion technique will allow a more straightforward IGCC plant configuration without air extraction from the gas turbine to be used.
New Machining Method for Nickel Based Thermal Sprays
Authors: Cohen Joel H. , Dailey James H. 
Published: February 2015

The routine overhaul and repair of gas turbine components requires dimensional restoration of many components. This process is usually accomplished by using various thermal sprays to build up the worn part surface and then machining or grinding the thermal sprays to correct part tolerances and dimensions. These surfaces usually contain numerous holes that generate heavily interrupted surfaces to be machined. The combination of interrupted cuts and a very wear resistant thermal spray causes rapid tool wear on conventional carbide cutting tools. This rapid tool wear also produces poor surface finish, part taper, chipping around the hole edges, and increased tool pressure that could result in lifting or peeling of the sprayed material from the parent metal.
This paper summarizes the results of machining nickel based thermal sprays with polycrystalline cubic boron nitride (PCBN) cutting tools. The tests have shown a minimum 2–5x improvement in surface finish, dimensional control, part taper and up to 10x increase in productivity. The PCBN tools also generated lower cutting forces resulting in reduced stress and higher bond strengths in the part.
This paper presents the data collected and the recommended machining parameters developed under controlled conditions for machining air plasma sprayed Metco 443, Metco 450, Inconel 718, two wire arc applied TAFA 75B, TAFA 73MXC, and high velocity oxygen fuel applied Inconel 718.
Development of a Custom Ambient NOx Correction Equation for a Mars SoLoNOx Gas Turbine
Authors: Hung W. S. Y. , Fahme A. , Kubasco A. 
Published: February 2015

The United States federal new source performance standards (NSPS) for stationary gas turbines contain NOx limits that are standardized based on the International Standards Organization (ISO) standard for ambient conditions. The measured NOx emissions from stationary gas turbines at test conditions are to be corrected to ISO standard ambient conditions using a recommended equation, which was developed using data from conventional (diffusion flame) combustion systems. It is genearlly expected that this correction equation will require a revision when advanced lean premixed or hybrid combustion system is utilized.
At the site of the first Mars 100S SoLoNOx gas turbine, a continuous emissions and gas turbine performance data gathering system has been installed. From the data gathered, the non-applicability of this NOx ambient correction equation is demonstrated. This points to the need to develop a custom NOx ambient correction equation for gas turbines with an advanced lean premixed system.
Using a proven NOx model, the humidity effect on NOx emissions from an advanced lean premixed system is determined to be much stronger than that for a conventional combustion system. The humidity effect was determined based on an engineering application of the NOx model. Through statistical analyses, this stronger humidity effect is supported by more than one thousand five hundred data points gathered over a eight-month period at the above customer’s site, covering an ambient temperature range over 100°F (56°C). Using this newly determined humidity effect and a least-square curve fit of the data, a custom NOx ambient correction equation has been developed for this prototype Mars SoLoNOx gas turbine.
The European Transonic Wind Tunnel: ETW High Quality Performance With High Productivity
Authors: Tizard J. A. , Bouis X. 
Published: February 2015

The paper reviews the design for performance of this new high Reynolds number facility, which aims at achieving the two, sometimes conflicting, requirements of high testing quality as well as high productivity. As far as productivity is concerned, specific related features include the modular multiple model cart concept, the capability to work on cold models, the sequencing of model handling activities and the “fast” control of all wind tunnel and model handling operations. The plans for the future incorporation of a half model test rig and the possible use of turbine powered simulators in ETW are addressed.
An assessment of the anticipated productivity of the facility is presented. The self supporting nature of ETW GmbH is also taken into account. Over the initial operating phase, important commercial parameters such as nitrogen and energy consumption, staffing levels, occupancy etc. will be under close scrutiny, in order to optimize cost-effectiveness. Data from the early commissioning and calibration tests indicate that testing charges for ETW should remain at a level comparable to those for conventional wind tunnel testing, all things being equal.
Benefits of MS 6001B Gas Turbine in Cogeneration: The UEM Power Plant Case
Authors: Remy Pierre M. , Bolssenin Yves M. , Molière Michel M. 
Published: February 2015

Long before the neologism “Cogeneration” was coined (around 1978), UEM’s Chambière Power Plant — which dates back to the turn of the century — was already supplying the city of Metz, east of France, with combined heat and power.
In 1992, Chambière experienced a major turning point in its history with the installation of a new unit based on one MS 6001B “Heavy Duty” gas turbine. This model, rated 38 MWe - ISO and burning natural gas or fuel oil has become the core of a new cogeneration unit exhibiting an outstanding performance:
- efficiency higher than 80% (LHV) providing a 20% energy saving in comparison to a conventional plant,
- low pollutant emissions (NOx, CO, HC) and low contribution to the greenhouse-effect (CO2).
The gas turbine has been equipped with two steam injection devices, for DeNOx and power augmentation respectively, resulting in a very flexible system.
After describing the power plant and giving its main achievements in the fields of energy and emissions, the paper briefly presents several improvements intended to protect both the turbine and the environment.
Forging of Compressor Blades: Temperature and Ram Velocity Effects
Authors: Zhen K. , Saigal A. , Chan T. S. 
Published: February 2015

Forging is one of the most widely used manufacturing process for making high strength, structurally integrative, impact and creep resistant Ti-6A1-4V compressor blades for jet engines. In addition, in modern metal forming technology, finite element analysis method and computer modeling are being extensively employed for initial evaluation and optimization of various processes, including forging.
In this study, DEFORM, a rigid viscoplastic two-dimensional finite element code, was used to study the effects of initial die temperature and initial ram velocity on the forging process. For a given billet, die temperature and ram velocity influence the strain rate, temperature distribution, and thus the flow stress of the material. The die temperature and the ram velocity were varied over the range 300–700°F and 15–25 in/sec, respectively, to estimate the maximum forging load and the total energy required to forge compressor blades. The ram velocity was assumed to vary linearly as a function of stroke.
Based on the analysis, it was found that increasing the die temperature from 300–700°F decreases the forging loads by 19.9% and increases the average temperature of the workpiece by 43°F. Similarly, increasing the initial ram velocity from 15–25 in/sec decreases the forging loads by 25.2% and increases the average temperature of the workpiece by 36°F. The nodal temperature distribution is bimodal in each ease. The forging energy required to forge the blades is approximately 18 kips*in/in.
Development of the Trent Econopac
Authors: Myers Gerry A. , Jackson Anthony J. B. 
Published: February 2015

Through an alliance established in 1992 between Westinghouse Electric Corporation and Rolls-Royce plc, a program has been implemented that will bring the industrial Trent aero engine to the power generation marketplace. The Rolls-Royce Trent has been initially sized at 50 MW, with a development potential to higher power ratings, and is offered by Westinghouse as a complete power generation package, the “Trent EconoPac”.
The Trent EconoPac sets a new performance standard in the industry with a nominal simple cycle efficiency of 42 percent. It is also ideal for combined cycle and cogeneration applications; a net combined cycle power of 63 MW at 52 percent efficiency can be developed. This paper describes the Trent industrial engine and EconoPac and reviews the development program with emphasis on unique features that benefit the power plant operator.
Advances in Abradable Coatings for Gas Turbines
Authors: Schmid R. , Nicoll A. R. 
Published: February 2015

Gas turbine engine development continues to accelerate, creating more demanding requirements for abradable seal coatings. These coatings are necessary to provide very small clearances between the rotating and stationary parts in order to minimize gap losses and so Increase efficiency. The relatively few abradable coating materials developed over the last 20 years still perform well in many blade tip seal and labyrinth seal applications. However, rising operating temperatures, corrosion and other environmental changes, longer overhaul times and even better tip clearances are dictating the design of new coating materials which requires a strong scientific approach. For example, ways are being Investigated to replace Nickel-Graphite and other flame sprayed coatings being used between 450 and 700°C respectively because of steady state/corrosion/oxidation/erosion and wear problems respectively.
New plasma and HVOF sprayed coatings have been developed using a systematic approach based on material response to operating conditions, minimizing trial and error. The major steps in the programme were:
1. Selection of constituent materials able to withstand service temperatures up to 325 (AISI-Polyester or Polyimide), 450 (AISI base), 700 (MCrAlY base) and 1100°C (ceramic base) respectively.
2. Powder particle manufacture and coating deposition to guarantee highly reproducible coatings.
3. Coating optimization based on wear tests carried out using a fully instrumented abradability test rig and wear mechanism analysis.
4. An investigation of blade tipping systems for high temperature applications.
This paper discusses the results of plasma sprayed coatings developed for use at 450 and 700°C.
Gas Turbine Model With Intensive Cooling
Authors: Khodak Evgeni A. , Romakhova Gallna A. 
Published: February 2015

A method of calculation of cooled gas turbine parameters is proposed. The method is based on the solution of the expansion process equation, heat transfer equations for cooled elements and on the results of the statistic processing of the parameters.
The method is valid for the turbine with any cooling system and gaseous heat carrier. Turbine output determination error does not exceed 0,5–1,0%.
The method allows to obtain the characteristics of gas turbines and gas turbine units (GTU) with open and closed air and steam cooling systems and to carry out an efficiency analysis of their performance in power generating units of various structure.