bluuebunny/crossref_metadata_2025_split huggingface dataset:
Assessment of the Cold Wire Resistance Thermometer for High Speed Turbomachinery Applications
Authors: Dénos R. , Sieverding C. H. 
Published: February 2015

The paper first describes the fundamentals of cold wire resistance thermometry. The transfer function with and without wire-prong heat conduction effects are discussed and a new method for the description of complicated transfer functions describing both the prongs and wire frequency response is proposed.
The experimental part of the paper starts with an investigation of the transfer function of various probes differing by the wire diameter, the l/d ratio and the wire-prong connection using two simple methods: (1) electrical heating of the wire by a sine current and (2) a temperature step test consisting in injecting the probe into a hot air stream. The first test provides information on the wire response whereas the second serves to study wire prong heat conduction effect.
The tests cover a wide range of velocities and densities. A frequency bandwidth of 2 kHz is obtained with a 2.5 µm wire probe at an air velocity of 200 m/s at atmospheric pressure. A numerical compensation system allows to extend the use of this probe to much higher frequencies. Finally, the probe is mounted onto a wheel in a high speed rotating test rig allowing probe traverses through a stationary hot air jet at rotational speeds up to 5000 RPM with the probe positioned at a radius of 0.380 m. The probe signal is transmitted via an opto electronic data transmission system. It is demonstrated that using the numerical compensation method, it is possible to reconstruct the hot jet temperature profile at frequencies up to 6 kHz.
Experimental Leakage and Rotordynamic Results for Helically Grooved Annular Gas Seals
Authors: Childs Dara W. , Gansle Anthony J. 
Published: February 2015

Rotordynamic-coefficient and leakage test results are presented for three grooved seals with helix angles of 0°, 15°, and 30° against rotation. The seals are 50.8 mm long and 152.4 mm in diameter. Tests were done for two supply pressures (up to 17 bars), three speeds (5000, 12000, and 16000 rpm), four pressure ratios, and three inlet fluid prerotation conditions.
The results showed that increasing the helix angle yields a progressive reduction in the cross-coupled stiffness coefficient k and a progressive increase in leakage. The helically-grooved seals consistently yield negative cross-coupled stiffness coefficients for nonprerotated inlet flow; hence, k in these seals would oppose forward whirl of a rotor. Helically grooved seals become less effective at reducing k with increasing preswirl; hence, for optimum effectiveness they should be used with a swirl brake.
Comparison between helically-grooved and honeycomb-stator seals showed that helically-grooved stators had reduced (negative) whirl-frequency ratios for nonprerotated flows but were no better than honeycomb-stator seals for elevated fluid prerotation. The 15° and 30° helix grooves leaked about 1.6 and 2.2 times, respectively, as much as the honeycomb-stator seals.
A Navier Stokes Analysis of Airfoils in Oscillating Transonic Cascades for the Prediction of Aerodynamic Damping
Authors: Abharl Reza S. , Giles Michael 
Published: February 2015

An unsteady, compressible, two dimensional, thin shear layer Navier Stokes solver is modified to predict the motion-dependent unsteady flow around oscillating airfoils in a cascade. A quasi 3-D formulation is used to account for the streamwise variation of streamtube height. The code uses Ni’s Lax-Wendroff algorithm in the outer region, an implicit ADI method in the inner region, conservative coupling at the interface, and the Baldwin-Lomax turbulence model. Computational mesh consists of an O-grid around each blade plus an unstructured outer grid of quadrilateral or triangular cells. The unstructured computational grid was adapted to the flow to better resolve shocks and wakes. Motion of each airfoil was simulated at each time step by stretching and compressing the mesh within the O-grid. This imposed motion consists of harmonic solid body translation in two directions and rotation, combined with the correct inter-blade phase angles.
Validity of the code is illustrated by comparing its predictions to a number of test cases, including an axially oscillating flat plate in laminar flow, the Aeroelasticity of Turbomachines Symposium Fourth Standard Configuration (a transonic turbine cascade), the Seventh Standard Configuration (a transonic compressor cascade). The overall comparison between the predictions and the test data is reasonably good. A numerical study on a generic transonic compressor rotor was performed in which the impact of varying the amplitude of the airfoil oscillation on the normalized predicted magnitude and phase of the unsteady pressure around the airfoil was studied. It was observed that for this transonic compressor, the non-dimensional aerodynamic damping was influenced by the amplitude of the oscillation.
Development of Shell-and-Tube Type Ceramic Heat Exchanger for CGT301
Authors: Yoshimura Yukihiro , Itoh Katsunori , Ohhori Kunio , Hori Masayoshi , Hattori Mitsuru , Yoshida Toshihiro , Watanabe Keiichiro 
Published: February 2015

The development of a 300kW-class recuperative ceramic gas turbine (CGT301) for continuous load has been conducted by the New Energy and Industrial Technology Development Organization (NEDO) as one of the programs in the Moonlight Project. In this program, the development of a ceramic heat exchanger has been carried out under the cooperation of Ishikawajima-Harima Heavy Industries, Ltd. (IHI) and NGK Insulators, Ltd. (NGK). since 1988.
In this paper, the process of the development of the ceramic heat exchanger is described. A three pass shell-and-tube type of heat exchanger is considered. As the heat exchanger is to be operated at gas temperature over 825°C, the reliability is expected to be improved by applying high-temperature resistant silicon-nitride ceramics to its hot tube-bundle. In consideration of the limitation in the size of the ceramic tube-bundle, the heat exchanger was designed as the assembly of six identical modules.
Tests of a single module with ceramic tube-bundle were conducted. It was confirmed that the ceramic tube-bundle had reasonable structural reliability, and that the module gave a sufficient performance i.e., temperature effectiveness and pressure drop characteristics.
Combustion Oscillation Control by Cyclic Fuel Injection
Authors: Richards G. A. , Yip M. J. , Robey E. , Cowell L. , Rawlins D. 
Published: February 2015

A number of recent articles have demonstrated the use of active control to mitigate the effects of combustion instability in afterburner and dump combustor applications. In these applications, cyclic injection of small quantities of control fuel has been proposed to counteract the periodic heat release that contributes to undesired pressure oscillations. This same technique may also be useful to mitigate oscillations in gas turbine combustors, especially in test rig combustors characterized by acoustic modes that do not exist in the final engine configuration.
To address this issue, the present paper reports on active control of a subscale, atmospheric pressure nozzle/combustor arrangement. The fuel is natural gas. Cyclic injection of 14% control fuel in a premix fuel nozzle is shown to reduce oscillating pressure amplitude by a factor of 0.30 (i.e., −10 dB) at 300 Hz. Measurement of the oscillating heat release is also reported.
Subcritical Crack Growth Life Prediction for Ceramic Components of Advanced Heat Engines
Authors: Wu D. C. , Peralta A. D. , Menon M. N. , Cuccio J. C. 
Published: February 2015

Advanced, high-strength ceramics are finding increasing application in advanced heat engines. To ensure the long-term reliability of components made from these materials, subcritical crack growth (SCG) from inherent flaws has to be taken into account, as this has been identified as the primary failure mode under sustained loading.
In analyzing fast fracture data, data censoring is necessary to obtain estimates of the inherent strength distributions for competing failure-causing flaw populations. This is particularly important for ceramic designs, where size scaling is a necessary part of the design analysis. While data censoring has become common for fast fracture data, data censoring involving stress rupture data has yet to be widely applied. This paper describes fast fracture and stress rupture tests performed on an advanced silicon nitride ceramic, the test data and fractography results, censored data analysis for both types of data, derivation of the subcritical crack growth parameters, and application of these parameters to verification specimens. Implications of the findings and recommendations for future studies are also presented.
Flow and Heat Transfer in a Pre-Swirl Rotor-Stator System
Authors: Wilson Michael , Pilbrow Robert , Owen J. Michael 
Published: February 2015

Conditions in the internal-air system of a high-pressure turbine stage are modelled using a rig comprising an outer pre-swirl chamber separated by a seal from an inner rotor-stator system. Pre-swirl nozzles in the stator supply the “blade-cooling” air, which leaves the system via holes in the rotor, and disc-cooling air enters at the centre of the system and leaves through clearances in the peripheral seals. The experimental rig is instrumented with thermocouples, fluxmeters, pitot tubes and pressure taps enabling temperatures, heat fluxes, velocities and pressures to be measured at a number of radial locations.
For rotational Reynolds numbers of Reϕ ≃ 1.2 × 106, the swirl ratio and the ratios of disc-cooling and blade-cooling flow rates are chosen to be representative of those found inside gas turbines. Measured radial distributions of velocity, temperature and Nusselt number are compared with computations obtained from an axisymmetric elliptic solver, featuring a low-Reynolds-number k-ε turbulence model. For the inner rotor-stator system, the computed core temperatures and velocities are in good agreement with measured values, but the Nusselt numbers are underpredicted. For the outer pre-swirl chamber, it was possible to make comparisons between the measured and computed values for cooling-air temperatures but not for the Nusselt numbers. As expected, the temperature of the blade-cooling air decreases as the swirl ratio increases, but the computed air temperatures are significantly lower than the measured ones. Overall, the results give valuable insight into some of the heat transfer characteristics of this complex system.
Initial Operating Experience and Test Results of ABB’s Gas Turbine GT13E2
Authors: Klohr M. , Schmidtke J. , Tschirren S. , Rihak P. 
Published: February 2015

On 20 October 1993, the first ABB GT13E2 gas turbine was put into operation. This 165 MW class gas turbine achieves 35,7% thermal efficiency in single cycle application and up to 54,3% (according ISO standard 3977, Annexe F) in a three pressure system. An optimised turbine and compressor design along with the increased turbine inlet temperature, lead to improved efficiency and electrical output.
A new concept for the combustor aimed at meeting the increasing demands on gas turbine emissions. The GT13E2 is equipped with the new single annular combustor and 72 of the ABB EV double cone burners.
The commissioning and testing of the first GT13E2 was carried out at the Kawasaki Gas Turbine Research Center (KGRC) in Sodegaura City near Tokyo, Japan. The gas turbine was assembled with various measurement systems to monitor static and dynamic pressure, gas and metal temperature, expansion, vibration, velocity and emissions. The facility will be used during a 15 year joint test program by ABB and Kawasaki Heavy Industries (KHI) to obtain a sound database of operating experience for further improvements of the GT13E2 gas turbine. Therefore, mid 1994 a second test phase was conducted and early 1995 a third test period is scheduled.
In parallel, the 2nd and 3rd GT13E2’s were commissioned and tested at the Deeside Combined Cycle Power Plant near Chester, Great Britain.
In November 1994, the 4th GT13E2 at Lage Weide was successfully commissioned.
This paper describes the operating experience with the GT13E2 during the first commissioning and test phases at KGRC and Deeside. The design features, the test facility, the instrumentation, the commissioning and test results are presented and discussed.
Dynamic Characteristics Analysis of Complex Rotor–Support–Case System
Authors: Hua Mingda , Li Qihan , Mao Jinxin 
Published: February 2015

The paper presents an analysis of the steady–state and transient dynamic characteristics of complex rotor system based on Transfer Matrix–Modal Synthetic Method. Critical speeds and modes are calculated using substructure transfer matrix method. The transient response is calculated using modal synthetic method respectively. The effects on the transient response of rotor system under the cases of various sudden unbalance levels, radial oil film clearances of damper and different rotor speeds are also investigated. The effectiveness and the capability of squeeze film damper (SFD) for suppressing instability are analyzed and it is found that in order to reduce the vibration of rotor system effectively, the damper parameters must be designed properly.
The Transfer Matrix–Modal Synthetic Method discussed in the paper is valuable in theory and practice. The method and results are very useful both in the design and development of complex rotor system.
Advanced Power Generation: The Potential of Indirectly-Fired Combined Cycles
Authors: Klara Julianne M. , Izsak Michael S. , Wherley Michael R. 
Published: February 2015

The next generation of coal-fueled power plants must be efficient, clean, and cost-effective. The U.S. Department of Energy (DOE) sponsors a program to develop an advanced, coal-based power system called HIPPS, or High Performance Power System, to meet these requirements. In the HIPPS cycle, air from a gas turbine compressor is indirectly heated in a coal-fueled furnace and then further heated directly with natural gas to power a gas turbine. Indirect heating of the gas turbine working fluid avoids the problems associated with expansion of a corrosive, coal-derived gas through a turbine. Steam is also generated to power a bottoming Rankine cycle.
This paper presents an analysis of the performance of HIPPS that is achievable using current technology and projects the level of performance as technology advances. The HIPPS cycle using current technology produces electricity from coal at a thermal efficiency that is more than 40 percent higher than that of today’s average coal-based power plants. The effect of advanced gas turbines, a novel gas turbine cycle, high performance steam cycles, and advanced coal-fueled furnace materials/designs is estimated with the use of computer-based engineering tools. Promising system configurations for future generations of HIPPS are identified with cycle efficiencies as high as 49.3 percent on a higher heating value basis.
Helium and Combustion Gas Turbine Power Conversion Systems Comparison
Authors: McDonald Colin F. 
Published: February 2015

For closed-cycle gas turbines, in a size to meet utility power generation needs, the selection of helium as the working fluid represents the best solution in terms of the overall power conversion system considering the differing requirements of the turbomachinery and heat exchangers. Helium is well suited for the nuclear Brayton cycle because it is neutronically inert.
The impact of helium’s unique properties on the performance and size of the power conversion system components is discussed in this paper. The helium gas turbine plants, that have operated were based on 1950s and 1960s technology, represent a valuable technology base in terms of practical experience gained. However, the design of the Gas Turbine Modular Helium Reactor (GT-MHR), which could see utility service in the first decade of the 21st century will utilize turbomachinery and heat exchanger technologies from the combustion gas turbine and aerospace industries. An understanding of how the design of power conversion systems for closed-cycle plants and combustion gas turbines are affected by the working fluids (i.e., helium and air, respectively) is the major theme of this paper.
Development of 300 kW Class Ceramic Gas Turbine (CGT302)
Authors: Nishio Kozi , Fujioka Junzo , Tatsumi Tetsuo , Takehara Isashi 
Published: February 2015

With the aim of achieving higher efficiency, lower pollutant emissions, and multi-fuel capability for small to medium-sized gas turbine engines for use in co-generation systems, a ceramic gas turbine (CGT) research and development program is being promoted by the Japanese Ministry of International Trade and Industry (MITI) as a part of its “New Sunshine Project”. Kawasaki Heavy Industries (KHI) is participating in this program and developing a regenerative two-shaft CGT (CGT302).
In 1993, KHI conducted the first test run of an engine with full ceramic components. At present, the CGT302 achieves 28.8% thermal efficiency at a turbine inlet temperature (TIT) of 1117°C under ISO standard conditions and an actual TIT of 1250°C has been confirmed at the rated speed of the basic CGT.
This paper consists of the current state of development of the CGT302 and how ceramic components are applied.
A Numerical Method for Power Plant Simulations
Authors: Carcasci Carlo , Facchini Bruno 
Published: February 2015

The continual increase in both efficiency and specific power of power plants determines the complexity of power generation units. Therefore, thermodynamic calculations with a high degree of accuracy and flexibility are required.
This paper describes a highly flexible computerized method of calculating thermodynamics in a power cycle. The computerized method analyzed here permits the study of steam, gas and combined plants. Its flexibility is not restricted by any defined cycle scheme.
A power plant consists of simple elements (turbine, compressor, combustor chamber, pump, etc.). Each power plant component is represented by its typical equations relating to fundamental mechanical and thermodynamic laws, so a power plant system is represented by algebraic equations, which are the typical equations of components, continuity equations, and data concerning plant conditions. This equation system is not linear, but can be reduced to a linear equation system with variable coefficients. The solution is determined by an iterative process.
An example of a simple gas turbine cycle demonstrates the applied technique. This paper also presents the user interface based on MS-Windows.
The input data, the results, and any characteristic parameters of a complex cycle scheme are also shown.
Full Coverage Effusion Film Cooling With Inclined Holes
Authors: Andrews G. E. , Khalifa I. M. , Asere A. A. , Bazdidi-Tehrani F. 
Published: February 2015

Effusion cooling with 15 film cooling rows of holes was investigated and a comparison of normal and inclined holes was undertaken for laser drilled holes. Overall and adiabatic cooling effectiveness data are presented for a density ratio of 2.5 for N=9688 holes per square metre and an X/D of 11. The main variable studied was the angle of inclination of the 30° film holes to the crossflow, 30°, 90° and 150°.
Comparison was made with 90° holes of similar X/D and a smaller X/D of 4.5, which was shown to be as effective as inclining the holes for improving the cooling effectiveness.
The opposed film cooling flow of the 150° inclined hole was very effective in providing a good film protection at the leading rows of holes. A cooling effectiveness of 0.7 was demonstrated at a mass flow per unit surface area G of 0.35–0.4 kg/sm2 bar with both 30° and 150° holes. This was equivalent to 15–20% of the combustor air flow for a typical gas turbine combustor. Comparison with previous work on effusion cooling showed reasonable agreement for similar geometries, although very few previous workers have reported overall cooling effectiveness results. Also the present work covered a much wider range of film cooling mass flow, a larger number of rows of holes and a more practical density ratio than in previous work.
Research and Development Status of Advanced Material Gas-Generator (AMG) Project
Authors: Hiromatsu M. , Yamamura T. , Chikata T. , Sekido T. , Ohama S. , Miyagawa H. , Murakami I. , Seki S. 
Published: February 2015

Advanced Material Gas-Generator (AMG) R&D Project was initiated in 1993 as a ten year’s program with a joint investment from Japan Key Technology Center and fourteen participating domestic companies.
The program objective is to establish basic key technologies for next generation gas-generator using advanced materials, which should have the features of significantly low fuel consumption with reduced weight and size, and should be environmentally acceptable, toward the realization of future industrial, marine and aerospace gas-turbine.
The R&D themes in this project cover advanced gas-generator conceptual study, advanced material and structures, innovative system and control, and advanced components technologies such as low NOx combustor.
Each R&D theme is underway toward achieving the program goal.
The 1st conceptual drawing of the advanced material gas-generator is completed as the result of the conceptual study.
PMC (Polymer Matrix Composites), MMC (Metal Matrix Composites), CMC (Ceramic Matrix Composites) and TiAl (Titanium-Aluminide) are considered as the candidate material for the advanced material gas-generator.
This paper introduces the outline of this project, and describes the status of conceptual study and each R&D themes.
Combined Helium and Combustion Gas Turbine Plant Exploiting Liquid Hydrogen (LH2) Physical Exergy
Authors: Bisio Giacomo , Massardo Aristide , Agazzani Alessio 
Published: February 2015

The aim of this work is the energy and exergy analysis of a combined plant made up of a conventional gas turbine (heavy-duty or aeroderivative) and a closed helium turbine cycle which exploits liquid hydrogen (LH2) as a lower exergy source.
A helium turbine with the characteristics of the fluid allows us to operate between the usual temperatures of the top turbine waste gas and those of the liquid hydrogen available. In this way the combined system reaches efficiency values greater than every combined system proposed to date.
The work contains a detailed analysis of the relative entropy productions of the helium cycle and considerations about the realization and technological aspects of helium turbines.
Feasibility of Utilizing a Bio-Mass Derived Fuel for Industrial Gas Turbine Applications
Authors: Andrews R. G. , Patnaik P. C. , Michniewicz J. W. , Jankowski L. J. , Romanov V. I. , Lupandin V. V. , Ravich A. V. 
Published: February 2015

This paper describes a development program aimed at determining the technical feasibility of utilizing a bio-mass derived fuel in an industrial gas turbine engine. The fuel addressed is a flammable bio-fuel oil derived from wood waste through flash pyrolysis. The fuel has a heating value of approximately 18 MJ/kg, a density of 1.2 kg/l and specialized wet filtration techniques are used to minimize the particulate matter in the fuel.
The turbine engine selected, as the test vehicle, is a 2.5 MW class-GT2500 engine designed and built by Mashproekt in the Ukraine. The standard operating conditions and layout of this engine provide flexibility in optimization of the combustion system to accept lower than conventional grade fuels.
The characteristics of the fuel, the fuel handling system, and the considerations with respect to igniting and maintaining combustion with a fuel of this nature are discussed.