bluuebunny/crossref_metadata_2025 huggingface dataset:
Unified Equation of Motion (UEM) Approach as Applied to S1 Turbomachinery Problems
Authors: Abdallah S. , Smith C. F. , McBride M. W.
Published: March 2015

Incompressible, blade-to-blade (S1 surface) flow solutions for stators and rotors of turbomachines are obtained utilizing an approach which combines the equations of motion into a single elliptic, second-order partial differential equation for the streamline field. This Unified Equation of Motion (UEM) is obtained from the momentum equation which is modified by using a stream function that satisfies the continuity equation identically. The unified equation is solved numerically by use of a finite difference technique. The velocity field is determined by differentiation of the stream function field and use of the computed streamlines. The pressure field is then determined from an energy relation along the streamlines. The present method is similar to the classical Streamline Curvature Method (SLCM) in that a computation grid is not required; however, the ellipticity of the flow field is preserved directly by the unified equation of motion. The UEM solution is substantially more stable than the SLC method and yields the periodic stagnation streamline directly. Body-fitted curvilinear coordinates (quasi-orthogonals and streamlines) are generated naturally by the UEM solution. A number of comparisons of the results of the present method are made with experimental data and results of other numerical methods. These comparisons are made for incompressible two dimensional and quasi-three dimensional stationary and rotating blade sections. There is general agreement with accepted analysis procedures.
Application of Mechanical and Electrical Equipment in a Natural Gas Processing Plant
Authors: Lang R. P. , McCullough B. B.
Published: March 2015

In 1984 the Northwest Pipeline Corporation purchased and installed equipment for their Ignacio, Colorado, gas processing plant to extract ethane and heavier hydrocarbons from the gas arriving at their pipeline system from various natural gas producing sources. In addition to the basic turbo-expander required to achieve the very low gas temperatures in the process, the equipment includes gas turbine driven compressors, heat recovery steam generators, and a steam turbine driven electric power generator. This paper reviews the process itself, the various mechanical and electrical equipment involved, and some of the control system utilized to tie it all together.
A New Method (FTDCDF) for Blade Design of Axial/Mixed-Flow Compressors and its Applications
Authors: Gu Chuan-Gang
Published: March 2015

A new design method with unequal work along the height of the blade in the axial/mixed-flow compressors, called The Flow-Type Design of Controlled Diffusion Factors (FTDCDF), has been developed in this paper. The idea of the method is to control the distribution of the diffusion factors along the height of the blade in the vaneless space in order to design the blade with good aerodynamic properties.

The theoretical basis of FTDCDF and its computational method are studied in detail. The corresponding computer program has been developed and worked out with good results. Comparison between the results of this method and those of other one is made and discussed. It shows that the FTDCDF and program have good accuracy and convergence.

On the basis of the author’s recent works, the practical applications of the FTDCDF for blade design and the choosing of distribution of diffusion factors are described in detail and the matching between the distributions of the diffusion factors and C1u(r1) is discussed.

A better design result of FTDCDF satisfying various design requirements is presented.
Software and Instrumentation to Monitor the Performance of Natural Gas Pipeline Turbine Systems
Authors: Levine Philip , Patanjo Daniel , Lam Wilkie Pak
Published: March 2015

Software for monitoring and evaluating the performance of gas turbines is being developed under the auspices of Gas Research Institute (GRI). Reference [1] provides an overview of the GRI project.

This paper describes the PEGASUS software and monitoring system. PEGASUS is an acronym for Performance Evaluation of GAS Users Systems. Field test results, on multi-shaft turbines used in the gas pipeline industry, have demonstrated the potential of the software. The software and instrumentation, can help identify maintenance and upgrade actions to improve performance.
From Fighter Aircraft to Pipeline: The Development of the First “Third Generation” Aero-Derived Gas Turbine in the 16,000–18,000 HP Class
Authors: Rogers Gordon N. , Mathers William G.
Published: March 2015

Two totally unrelated sources of hot gas energy — the FCCU oil refining process and the aircraft engine — both utilize the same range of basic aerodynamic and machinery design technologies for mechanical drive power recovery. This paper shows how these technologies came together and discusses the development of the Ingersoll-Rand GT-60 gas turbine, the first to use a general Electric LM1600 hot gas generator (from the F404 fighter engine program); it also illustrates how it was possible for the first “third generation” aero-derived gas turbine in the 16,000–18,000 hp class to be developed in a much shorter than normal lead time.
Labyrinth Seal Flow Measurement by Tracer Gas Injection
Authors: McGreehan William F. , Haaser Fred G. , Sherwood Laurence T.
Published: March 2015

A practical system for flow measurement in rotating seals using the injection and sampling of a tracer gas is presented. Carbon dioxide or helium is injected as a tracer into a labyrinth seal at a controlled rate and gas samples are extracted downstream for concentration measurement. Test results from a rotating labyrinth seal rig were obtained over a range of seal pressure ratios and rotor speeds in order to determine the conditions which assure optimum tracer gas mixing. Seal leakage rates calculated by tracer gas concentration are compared to venturi flow measurements.
Numerical Predictions and Measurements of Discharge Coefficients in Labyrinth Seals
Authors: Wittig S. , Schelling U. , Kim S. , Jacobsen K.
Published: March 2015

The present paper illustrates the possibilities and limitations in applying advanced numerical codes for the description of the flow through labyrinth seals to evaluate the discharge coefficient. Comparison with data derived from detailed measurements in a newly developed test facility are reported. Pressure ratios and geometrical parameters are varied in wide ranges, reflecting engine conditions. The two-dimensional, elliptic finite difference code is applied to the compressible, turbulent flow in straight and stepped seals utilizing the standard k-ε-model. Good agreement of the predictions with the measurements is achieved for pressure ratios up to 2.5.
The Aeromechanical Response of an Advanced Transonic Compressor to Inlet Distortion
Authors: Datko J. T. , O’Hara J. A.
Published: March 2015

An advanced transonic compressor was tested in the Compressor Research Facility at the Aero Propulsion Laboratory, Wright-Patterson Air Force Base, Ohio. This compressor was designed, built, and instrumented by the General Electric Company under Air Force contract. During this test, the compressor was operated with seven different total pressure distortion screens located at the inlet, along with baseline testing of two “clean” inlet configurations. Of particular interest was the forced vibratory response of the compressor first stage integrally bladed disk (blisk) to the various distortions. This paper presents a summary of the blisk vibratory responses to each of the distortion screens. Effects of instrumentation on the dynamic response of the blisk are illustrated. In addition, the measured steady total pressure inlet distortion profiles for each screen are shown with a summary of the instrumentation used to make the various steady and dynamic measurements.
Applications of Ceramic Coating on the Turbine Blades of the AGTJ-100B
Authors: Uchida Kazuo , Koga Akinori , Teshima Kiyomi , Arai Masashi
Published: March 2015

In 1978, the Japanese government started a national project for energy conservation called the Moonlight Project. The Engineering Research Association for Advanced Gas Turbines was selected to research and develop an advanced gas turbine for this project.

The development stages were planned as follows: First, the development of a reheat gas turbine for a pilot plant (AGTJ-100A), and second, a prototype plant (AGTJ-100B). The AGTJ-100A has been undergoing performance tests since 1984 at the Sodegaura Power Station of the Tokyo Electric Power Co., Inc. (TEPCO).

The inlet gas temperature of the high pressure turbine (HPT) of the AGTJ-100A is 1573K, while that of the AGTJ-100B is 100K higher. Therefore, various advanced technologies have to be applied to the AGTJ-100B HPT. Ceramic coating on the HPT blades is the most desirable of these technologies.

In this paper, the present situation of development, as well as future R & D plans for ceramic coating will be described.
Flow Investigations on Swirling Compressible Flow Through a Vaneless Radial Diffuser
Authors: Agrawal D. P. , Yahya S. M. , Reddy D. N.
Published: March 2015

The present study deals with the experimental investigation of Swirling compressible flow through a parallel walled vaneless radial diffuser. Swirl generator of vortex nozzle type is used for supplying swirling compressible flow at the diffuser inlet up to a Mach number of 0.8. The desired flow angles are achieved by adjusting inlet swirl vane setting angles from 2.5° to 12.5°. The results are presented in terms of performance parameters such as pressure recovery and loss coefficient for various diffuser inlet Mach numbers from 0.3 to 0.8 and flow angle range from 20° to 35°. The effect of Mach number and swirl angle on the performance of the vaneless radial diffuser are discussed.
Labyrinth Seal Force Coefficients for Small Motion of the Rotor About an Arbitrary Eccentricity Position
Authors: Rajakumar C. , Sisto F.
Published: March 2015

Labyrinth seal force coefficients have been calculated for arbitrary eccentricity position of the rotor center with respect to the seal center. By solving the steady seal flow governing equations for known eccentricities, the circumferential pressure and velocity distributions are obtained. For a perturbation motion of the rotor about the steady eccentric position, the momentum and continuity equations of the seal flow are linearized. The resulting linear partial differential equations have been solved to get the perturbation pressures that are proportional to the rotor center motion along two orthogonal coordinate directions, which when integrated over the rotor surface yield the required force coefficients. Comparison of the stiffness coefficients obtained were made with published experimental results. In addition, the stiffness coefficients have been verified by comparing with the seal forces calculated for large eccentricity ratios. The results also include the damping coefficients that result due to the rotor center motion.
Three Component Velocity Measurements in the Interblade Region of a Fan
Authors: Menon Rajan K.
Published: March 2015

Optimizing aerodynamics and improving blade designs to make efficient power-generating machinery requires a good understanding of the rotor flow field. Swirl, flow instabilities, and high turbulence highlight the need for understanding the three-dimensional nature of the flow. Dynamic interaction between fluid and structural aspects in fluid machinery, impact of unsteady flows or loads, and enhancement of property transport can be studied through simultaneous measurement of three components of velocity.

A three color, three component Laser Velocimeter System is used to simultaneously measure the three orthogonal components of velocity in the interblade region of a fan. The non-invasive nature of the technique combined with the very small measuring volume of the system provides detailed mapping of the flow field in the interblade region. The data acquisition package collects all the data available while the machine is running and sorts the raw data into bins corresponding to the various circumferential positions. Each velocity measurement — all three components — along with the circumferential position information is collected by a DEC PDP 11/23 Computer. The analysis package allows the user to examine a portion of the interblade region, look at alternate interblade gaps, omit data during blade passage, etc.

Statistical properties such as mean, turbulence, skewness, flatness, Reynolds stress values, and projections in cross sectional planes are obtained and displayed as a function of circumferential position. Thus, the detailed properties of the three dimensional flow field are obtained from the three component LDV measurements.
Comparison of Predicted and Measured Velocities in a Compressor Disk Drum Model
Authors: Alberga D. G. , Stephens G. E. , Johnson B. V.
Published: March 2015

The tangential velocity distributions in the bleed and the trapped cavities of an eleven-cavity, compresor drum model were measured and predicted. The measurements were obtained with a Laser Doppler Velocimeter (LDV) in experiments using Freon-113 as the working fluid. The experiments were conducted at disk tangential Reynolds numbers of approximately 2 × 106 over a range of inward bleed flow rates through the center cavity. The experimental results show that the tangential velocity profiles in the bleed cavity vary from near-solid-body at low flow rates to near-free-vortex at the highest flow rate. The experimental results also showed a decrease in tangential velocity strength in the trapped flow cavities with distance from the bleed cavity. The flow in the bleed and trapped cavities were predicted using an analysis coupling the flow in a core region with the flow in the disk boundary layers. The secondary flow in the boundary layer was modeled using momentum integral equations. The core flow was determined by coupling the total flow with the boundary layer flow through the continuity equation, and the core tangential velocity was modeled with one dimensional viscous flow equations. Predicted results are presented for a range of flow conditions and cavity locations. The analytical model accurately predicted the tangential velocity distribution, and hence pressure drop, in both classes of cavities when the appropriate core turbulence model and boundary conditions were applied.
Velocity Scaled Aeroelastic Testing of Advanced Turboprops
Authors: Crawley Edward F. , Ducharme Eric H.
Published: March 2015

An innovative experimental procedure for the sub-velocity scale testing of anisotropic aeroelastic models is developed and applied to the Advanced Turboprop. The scaling laws for an anisotropic, rotating model are developed. These scaling laws indicate that by proper choice of model geometry, stiffness, and density, all of the important aeroelastic similarity parameters can be satisfied in a full-velocity scaled test. In a sub-velocity scaled test, all the similarity parameters except for the Mach number can be matched. The development of the model building technology to construct reduced stiffness anisotropic models for sub-velocity scaled testing is then reviewed. In order to experimentally verify the sub-velocity scaled procedure, a propeller model was constructed based on the G.E. UDF MPS model, and the aeroelastic and performance data are favorably compared. Finally, as an illustration of the versatility of the sub-velocity scaled approach, the model is used to demonstrate the sensitivity of ATP blade flutter to mass distribution.
A Triplex Fault Tolerant Digital Control
Authors: Slagle John L.
Published: March 2015

Reliability is becoming more important as turbomachinery applications become more complex and as competition becomes more intense. This paper describes a fault tolerant control system that offers the needed reliability. Both the hardware and software are discussed. An application of the control on a Westinghouse 501 gas turbine is noted.
An Effective System for Sealing Toxic Gases in Centrifugal Compressors
Authors: Ronsky N. Daryl , Conquergood C. Peter , Harris Tim , Davies Islwyn
Published: March 2015

Maintaining seal oil systems has traditionally been one of the biggest problems faced by operators of centrifugal compression equipment. This problem is compounded when highly toxic gases are being compressed. This paper describes the retrofit of a simple, effective, mechanical dry seal system which eliminated one sour gas operator’s problems. The retrofit resulted in a safe, easy-to-operate system, which vents no toxic gases into the environment.

The retrofit was completed on a gas gathering compressor operating with hydrogen sulphide at a discharge pressure of 10,000 kPa (1500 psig), a discharge temperature of 150° C (300° F) and an operating speed of 23 500 rpm.

This paper describes the operating problems encountered with the traditional seal oil system, the successful resolution of the problems with the mechanical dry seal system and operational data of the successful retrofit.
Turbine Disposition, Erosion and Corrosion Evaluations Using a Simplified Test Approach
Authors: Wenglarz Richard A.
Published: March 2015

New applications and fuels (such as coal) that increase the potential for flow path degradation due to deposition, erosion, and corrosion (DEC) are being considered for gas turbines. Cascade and turbine DEC tests representing the flow paths of the specific turbines of concern will eventually be necessary for final verification of fuels and DEC control approaches. However, these tests are expensive and are not readily interpretable for other conditions (e.g., fuels and flow passage variations) than those tested. Consequently, relatively inexpensive simplified tests that provide an understanding of the DEC degradation processes are needed to screen the numerous possible candidate fuels and DEC control approaches. The most promising alternatives determined from simplified tests could then be verified in more expensive cascade and turbine tests. This paper discusses simplified DEC tests and complementary data extrapolation approaches that provide and interpret data in a manner that enhances understanding of DEC processes and that can be used to estimate DEC in operating turbines. A new test facility that has been designed for relatively inexpensive turbine DEC evaluations using these approaches is described.
The Turbomachine Blading Design Achieved by Solving the Inverse Field Problem
Authors: Luu T. S. , Viney B.
Published: March 2015

This paper describes a design procedure for the determination of the geometry of the blading of the turbomachine with prescribed thickness and bound vorticity distribution. The boundary conditions are discussed in order to have a properly posed field problem. Optimised 2D cascade design example is shown. The quasi 3D “S2” - “S1” stream function formulation is developed. The design of guide vanes downstream of a lateral inlet casing is described. A new approach by introducing a potential like function to treat the 3D rotational flow is also formulated.
Development and Application of a High Frequency Wedge Probe
Authors: Bubeck H. , Wachter J.
Published: March 2015

To investigate the three dimensional unsteady flow behind rotating blade rows of turbomachines, a high response pressure probe has been developed. Surface mounted miniature pressure transducers are used to measure the flow fluctuations, while the mean pressures are measured simultaneously with adjacent conventional pressure lead tubes. The steady state and the dynamic behaviour of the probe were investigated. The application of the probe to the rotor exit flow of an axial compressor is described and results are presented.
Initial User Experience With an Artificial Intelligence Program for the Preliminary Design of Centrifugal Compressors
Authors: Russo Carol J. , Nicklaus Dennis J. , Tong Siu S.
Published: March 2015

A new approach is evaluated for the design of turbomachinery components using existing analysis codes coupled to a generic Artificial Intelligence (AI) software framework called ENGINEOUS. This AI framework uses intelligent search techniques with a small set of basic component design rules to iterate to an optimized solution and to quantify parameter trade-offs. Initial experience with ENGINEOUS indicates that it is a powerful design tool which quickly identifies non-obvious solutions balanced for conflicting multiple goals in a small number of iterations which vary linearly with the number of variables. The solution path and driving logic are easily visible to the designer and a parameter study option can rapidly quantify potential design trade-offs which together allow a critique of the selected design to balance performance against development risks. Because this AI design approach fosters intelligent interface with the designer and is generic, the potential application areas and productivity benefits appear enormous.
Noise Level Evaluation for a Natural Gas Compressor Station Driven by Gas Turbines at the Planning Stage After Four Years of Operation
Authors: Fleischer Friedrich , Hiemer Heiko , Mann Jürgen
Published: March 2015

For a southern german gas turbine compressor station sound emission levels and noise control thereoff are evaluated based on authority specified immission levels.

Project history, planning and operating experience is shown.
Measurements of the Unsteady Flow Field Within the Stator Row of a Transonic Axial-Flow Fan: I — Measurement and Analysis Technique
Authors: Suder K. L. , Okiishi T. H. , Hathaway M. D. , Strazisar A. J. , Adamczyk J. J.
Published: March 2015

This two-part paper presents detailed laser anemometer measurements of the unsteady velocity field within the stator row of a transonic axial-flow fan. The objective of this study was to provide additional insight into unsteady blade-row interactions within high speed compressors which affect stage efficiency, energy transfer, and other design considerations. Part I of this paper describes the measurement and analysis techniques used for resolving the unsteady flow field features. The ensemble-average and variance of the measured velocities are used to identify the “rotor-wake-generated” and “unresolved” unsteadiness, respectively. The term “rotor-wake-generated” unsteadiness refers to the unsteadiness generated by the rotor wake velocity deficit and the term “unresolved” unsteadiness refers to all remaining contributions to unsteadiness such as vortex shedding, turbulence, mass flow fluctuations, etc. A procedure for calculating auto and cross correlations of the rotor-wake-generated and unresolved unsteady velocity fluctuations is described. These unsteady-velocity correlations have significance since they also result from a decomposition of the Navier-Stokes equations. This decomposition of the Navier-Stokes equations resulting in the velocity correlations used to describe the unsteady velocity field will also be outlined in this paper.
Measurements of the Unsteady Flow Field Within the Stator Row of a Transonic Axial-Flow Fan: II — Results and Discussion
Authors: Hathaway M. D. , Okiishi T. H. , Suder K. L. , Strazisar A. J. , Adamczyk J. J.
Published: March 2015

Results of detailed unsteady velocity field measurements made within the stator row of a transonic axial-flow fan are presented. Measurements were obtained at midspan for two different stator blade rows using a laser anemometer. The first stator row consists of double-circular-arc airfoils with a solidity of 1.68. The second stator row features controlled-diffusion airfoils with a solidity of 0.85. Both stator configurations were tested at design-speed peak efficiency conditions. In addition, the controlled-diffusion stator was also tested at near-stall design-speed conditions. The procedures developed in Part I of this paper are used to identify the “rotor-wake-generated” and “unresolved” unsteadiness from the velocity measurements. (The term “rotor-wake-generated” unsteadiness refers to the unsteadiness generated by the rotor wake velocity deficit and the term “unresolved” unsteadiness refers to all of the remaining unsteadiness which contributes to the spread in the distribution of velocities such as vortex shedding, turbulence, etc.) Auto and cross correlations of these unsteady velocity fluctuations are presented in order to indicate their relative magnitude and spatial distributions. Amplification and attenuation of both rotor-wake-generated and unresolved unsteadiness are shown to occur within the stator blade passage.
A Study of Thermodynamic Performance of CAES Plants, Including Unsteady Effects
Authors: Macchi Ennio , Lozza Giovanni
Published: March 2015

The thermodynamic performance of some representative CAES (Compressed Air Energy Storage) plant configurations is computed both at steady-state nominal point and during time-variable conditions, by making use of a simulation technique capable of accounting for thermal inertia of recuperators and TES (Thermal Energy Storage), for part-load characteristics of turbomachinery and for power regulation modes. The results of the analysis are presented in terms of the energy losses caused by the irreversibilities occurring in the various plant components, with reference to the second law of thermodynamics.
Boundary Layer Profile Investigations Downstream of an Aero-Engine Intake Anti-Icing Air Exhaust Slot
Authors: Downs S. J. , James E. H.
Published: March 2015

The boundary layer profile downstream of the anti-icing air exhaust slot of a two-dimensional aero-engine inlet section was investigated by means of a pitot rake. Results are presented for a range of inlet engine airflows with and without exhaust anti-icing air introduced. The boundary layer was found to be turbulent as expected owing to the presence upstream in the wind tunnel of a fixed water spray grid which may be used to simulate engine operation in clouds. Injection of anti-icing air produced a sub-layer downstream of the anti-icing air exhaust plane. Three methods of deriving boundary layer thickness from the experimental data were used and theoretical values determined for comparative purposes. The experimental measurements confirmed theoretical trends.
Coping With Gas Turbine Emissions Regulations
Authors: Solt J. C.
Published: March 2015

The subject of emissions regulations is complex. Worldwide there are over 20 countries that regulate permissible emissions, each with its own regulations. Certain groups, such as the European Economic Community (EEC) have regulations for all of their members. In the United States, federal regulations (Fig. 1) fall under the Environmental Protection Agency (EPA), while there are separate regulations for each of the 50 states. Fortunately, most of the state regulations are simply adapted from and are quite similar to federal regulations. However, several states have significantly more stringent standards than the federal regulations. The State of California, for example, not only has separate regulations, but each of the 45 pollution control districts within the state has its own regulations, most of which differ substantially from each other.

The following is a discussion of the U.S. federal regulations as they apply to areas that presently meet the ambient air quality standards. These are called attainment areas. Areas that do not meet the ambient air quality standards are called nonattainment areas. For a gas turbine application in a nonattainment area, such as Denver, or in the State of California, it is imperative to check local regulations, which result from the federal regulations for nonattainment areas.
Ranking of Compressor Station Noise Sources Using Sound Intensity Techniques
Authors: Johns W. D. , Porter R. H.
Published: March 2015

Local residential development and the introduction of more restrictive noise regulations in Canada and the United States are creating a need to improve the noise abatement systems at many existing industrial sites including pipeline compressor stations. The initial phase of any silencing program should include a study to identify and rank the noise sources. Until recently, this type of noise study has been qualitative and inexact, requiring a trial and error approach which addressed only one or two sources at a time and often resulted in a prolonged and costly silencing program. The use of sound intensity techniques to determine sound power levels of all noise sources results in lower costs, improved job scheduling and greater likelihood of success of a silencing program. This paper discusses a case study which uses sound intensity techniques to rank noise sources at a natural gas compressor plant powered by a gas turbine.
FT8: A High Performance Industrial and Marine Gas Turbine Derived From the JT8D Aircraft Engine
Authors: Day William H.
Published: March 2015

This paper describes the FT8 gas turbine, which has been introduced by Turbo Power and Marine Systems (TPM). The FT8 is derived from the Pratt & Whitney JT8D aircraft engine and the TPM FT4 industrial gas turbine. The FT8 has been launched with a collaboration program between TPM and the China National Aerotechnology Import-Export Corporation (CATIC) of the People’s Republic of China. The collaboration program includes co-production of certain components and a 37-unit order from CATIC over a 10-year period for marine and industrial applications.
The Replacement Cruise Engine for the DDH 280 Tribal Class Destroyer
Authors: Mack I. D. , Hurl D. J.
Published: March 2015

A description of the existing propulsion plant in the DDH 280 Class Destroyer and problems with the existing cruise engine fit are outlined. The trade off analysis and option study which led to the decision to replace the existing cruise engine with a replacement gas turbine is examined and the criteria which were used in the selection of the Allison 570 K are then briefly addressed. Finally the intended technical fit and design considerations associated with the installation into the vessel are described.

The opinions expressed herein are those of the authors and not necessarily of the Department of National Defence, Canada.
LM500 CODAG Propulsion for the Danish Navy Stanflex 300
Authors: Daley Leonard T. , Munk Torben
Published: March 2015

A description of the Royal Danish Navy’s answer to fleet modernization — a standard hull platform with multi-mission interchangeable modules designed to replace obsolescent classes of minelayer, mine sweeper, surveillance and missile attack craft.

Propulsion for this ship will be provided by a triple screw combined diesel and gas turbine (CODAG) plant comprised of a General Electric Co. (USA) type LM500 marinized aeroderivative gas turbine and two (2) Motoren und Turbinen Union (MTU) 16V396 TB84 diesels. This is the first naval application of the General Electric Co. (USA) LM500 gas turbine.
Marine Gas Turbines - Engine Health Monitoring - New Approaches
Authors: Walker John , Summerfield Alan
Published: March 2015

Recent developments, coupled with field experience of Engine Health Monitoring Techniques within the Royal Navy Gas Turbine Fleet have enabled a fresh initiative. The advantages of adopting a policy of Condition Based Maintenance rather than a rigid hours concept are outlined and the Engine Health Monitoring (EHM) developments and affects on overhaul facilities are explained.
Altitude Tests of the XF3-30 Turbofan
Authors: Kitamura Masayuki , Uchida Morimasa , Yashima Satoshi
Published: March 2015

The XF3-30 turbofan has been successfully developed as the propulsion system for the Japan Air Self Defence Force’s XT-4 military intermediate trainer. Altitude tests were conducted four times in ATF (AEDC and GE) and four times on FTB in the engine development program.

Utilizing the results of each test, the engine has been improved in sufficient time to meet the aircraft development program schedule, and successful flight tests of XT-4 powered by XF3-30 have been made.
The Circumferential Velocity Profile for Secondary Flow Calculations
Authors: Douvikas D. , Kaldellis J. , Papailiou K. D.
Published: March 2015

The circumferential (and transverse) velocity profile is examined in external and internal flow problems. The various cases, unbounded, semi-bounded and fully bounded, are examined and expressions are developed for each one of them, taking viscous and compressibility effects into account.

A comprehensive and generalised description is presented which considers the transfer of vorticity along the streamlines and provides simple expressions for the circumferential velocity profiles which, although different from previous attempts, have as particular cases the results of Johnston’s and Hawthorne’s work.
Conical Grid Plate Flame Stabilizers: Number and Size of Jet Shear Layers
Authors: Ali A. F. , Andrews G. E.
Published: March 2015

The influence of the number and size of the jet shear layers, at a constant total hole area, was investigated in a propane fuelled conical grid plate flame stabiliser. The combustion inefficiency, NOx and flame stability were determined for shear layer designs with 90, 8 and 4 holes. The total shear layer volume increased as the number of holes was reduced and combustion within these larger shear layers was responsible for the superior flame stability and combustion efficiency, but higher NOx emissions. Large shear layers and hence a small number of holes were necessary to achieve an adequate performance at a 400K inlet temperature, but at 600K the 90 hole system had the best combination of low NOx and combustion inefficiency. However, the 8 hole system had a performance close to the 90 hole system at 600K and better than it at 400K and was concluded to be the preferable design.
Cyclic Spinning Testing of Aero-Engine Discs
Authors: Aoano H. , Chikata T. , Satoh R. , Wakatsuki T. , Hikita M.
Published: March 2015

Aero-engine discs must be demonstrated to have sufficient low cycle fatigue lives. To evaluate the low cycle fatigue lives of aero-engine discs, we have carried out several cyclic spinning tests. During the testing, some discs were burst, and some discs were cracked. Through the experience of the testing, we have developed a technique for detecting the crack initiation of the discs during spinning tests. By using the technique obtained, it is possible to stop driving before the discs would burst. Procedures and obtained data are presented in detail.
Development of the XF3-30 Turbofan Engine
Authors: Yamada Hidejiro , Hamatani Hiroshi , Ishizawa Kazuhiko
Published: March 2015

The XF3-30 is the low-bypass-ratio turbofan engine which has been developed to power the XT-4 intermediate trainer for the Japan Air Self Defence Force. This engine has been designed and tested in accordance with the requirements of MIL-E-5007D with some modifications to meet the particular requirements of an intermediate trainer and circumstances in Japan. All of the qualification tests including endurance tests, low cycle fatigue test, altitude test, foreign object ingestion test and environmental icing test were successfully completed by Mar. 1986 and flight test of the XT-4 trainer aircraft powered by two of the XF3-30 engines has proceeded without any-engine related problems.
Performance of the Integrated Gas and Steam Cycle (IGSC) for Reheat Gas Turbines
Authors: Takeya Kazuo , Yasui Hajime
Published: March 2015

In 1978, the Japanese government started a national project for energy conservation called the Moonlight Project. The Engineering Research Association for Advanced Gas Turbines was selected to research and develop an advanced gas turbine for this project.

The development stages were planned as follows: First, the development of a reheat gas turbine for a pilot plant (AGTJ-100A), and second, a prototype plant (AGTJ-100B). The AGTJ-100A has been undergoing performance tests since 1984 at the Sodegaura Power Station of the Tokyo Electric Power Co., Inc. (TEPCO).

The inlet gas temperature of the high pressure turbine (HPT) of the AGTJ-100A is 1573K, while that of the AGTJ-100B is 100K higher. Therefore, various advanced technologies have to be applied to the AGTJ-100B HPT. Ceramic coating on the HPT blades is the most desirable of these technologies.

In this paper, the present situation of development, as well as future R & D plans for ceramic coating, is taken into consideration. Steam blade cooling is applied for the IGSC.
A Computer Program to Analyze Cogeneration Plant Heat Balances and Equipment Design
Authors: Stewart J. C. , Hsun C. F.
Published: March 2015

This paper describes a computer program designed to calculate and analyze cogeneration plant heat balances and equipment and to plot heat balance diagrams. For normal design point conditions, the program calculates gas turbine performance, designs a heat recovery boiler to suit the process requirements, calculates a steam turbine performance and deaerator balance to complete the cycle. In addition, the program will calculate off-design performance for a supplementary firing option or for changes in ambient conditions, gas turbine part load or process conditions.
Development of Coal-Fueled Gas Turbine Systems for Electric Utility Application
Authors: Thoman R. J. , Horazak D. A. , Hals F. A.
Published: March 2015

The authors’ companies are working to establish the technology base for an advanced direct coal-fired gas turbine system. This work, sponsored by the Department of Energy, is directed at the electric utility application. This paper describes the technical approach and discusses its feasibility. Successful development of a slagging combustor is key to this effort. It will first be developed at subscale. Following this, integrated testing will incorporate the subscale slagging combustor and a small gas turbine into an operating electric generating system. In addition, a utility-sized combustor module will be designed and tested under utility operating conditions.
Coal-Fired Gas Turbine for Locomotive Propulsion
Authors: Green Leon
Published: March 2015

Substitution of a deeply-cleaned coal-water slurry fuel for bulk solid coal in an atmospheric fluidized-bed combustor permits a sequence of evolutionary steps which can convert the conventional AFBC into a pressurized, combustion-stirred, fluidized-bed heat exchanger compact enough to propel a standard locomotive by use of a closed Brayton power cycle.
A Simplified Method for 3-D Potential Flow in Turbomachinery Using Vortex Sheet Boundary Conditions
Authors: Jiang H. , Cai R. , Zhu Y.
Published: March 2015

Within the framework of inviscid flow theory, the character of three-dimensional flow in turbomachinery blade row is discussed. One of the important differences between 3-D and 2-D flow in turbomachinery is the discontinuity of velocity at the two sides of trailing edge and across downstream boundary. The inconsistency of the traditional periodicity conditions for downstream boundary and of the axisymmetric assumption for outlet flow with the three-dimensionality of turbomachinery flow is discussed also. For 3-D potential flow, the vortex sheet boundary conditions (VSBC) for downstream boundary and a fully 3-D condition for outlet flow are presented. A simplified method is developed by implementation of VSBC on a fixed vortex boundary in order to predict the fully 3-D flow in blade passage as well as downstream of blade row. In the present investigation two calculations are carried out. In one calculation the traditional boundary conditions are imposed while in another one the VSBC are used to demonstrate the capability of the newly develped boundary conditions. The agreement between some calculated results and the theoretical analysis is very well.
Part Load Performance of the Intercooled Two-Shaft Gas Turbine With Power Output at Constant Speed on the High-Pressure Shaft
Authors: Gasparovic N. , Kim J.-W.
Published: March 2015

The general analysis of the part load performance of gas turbines indicates that the intercooled cycle with two shafts and power output at constant speed on the high-pressure shaft can have a good part load efficiency. Calculations with fixed geometry of the turbomachines show an intolerable increase of the turbine inlet temperature above the permissible level. By introducing variable geometry in the turbomachines, this disadvantage can be overcome. With variable inlet guide vanes at the high-pressure compressor an excellent part load performance is achieved. Further improvements are possible by adding an internal heat exchanger.
A New Method of Calculating Optimum Velocity Distribution Along the Blade Surface on Arbitrary Stream Surface of Revolution in Turbomachines
Authors: Zixiang Zou , Ding Yuan
Published: March 2015

This paper presents a physical model and its mathematical expressions (partial differential equation group), which are to be used to calculate the optimum velocity distribution on blade surface. The method is based on the theory of boundary layer and the calculation of cascade loss, and to employ the Pontijagin maximum principle as well as the new optimum techniques in applied mathematics. In this paper, a computing method of optimum velocity distribution along the blade surface in 2-D incompressible flow is presented by analysing and solving the equation group, and then by using the method which is presented by Zou Zixiang (1976), and through a logical analysis, a new method has been offered, which can converted from an optimum velocity distribution along the plane stream surface of incompressible fluid flow into that of an arbitrary stream surface of revolution in compressible fluid flow.
Transient Behavior of Solar Heated Radiation Receivers for Small Gas Turbine Power Plants
Authors: Bammert K. , Johanning J. , Lange H.
Published: March 2015

Solar heating of gas turbine plants is moving back to the focus of current research. The mainly unsteady operation of solar turbine power plants can only be predicted with sufficient accuracy if the transient behavior of the solar radiation receiver is known. Therefore the transient behavior of cavity receivers of different designs is investigated. The mathematical model used to simulate heat transfer and energy storage is illustrated. Computed results for two receivers with different inner lining are compared and evaluated concerning their use in practice.
Applying Kalina Technology to a Bottoming Cycle for Utility Combined Cycles
Authors: Kalina A. L. , Leibowitz H. M.
Published: March 2015

A new power generation technology often referred to as the Kalina cycle, is being developed as a direct replacement for the Rankine steam cycle. It may be applied to any thermal heat source, low or high temperature. Among several Kalina cycle variations there is one that is particularly well suited as a bottoming cycle for utility combined cycle applications. It is the subject of this paper.

Using an ammonia/water mixture as the working fluid and a condensing system based on absorption refrigeration principles the Kalina bottoming cycle outperforms a triple pressure steam cycle by 16 percent. Additionally, this version of the Kalina cycle is characterized by an intercooling feature between turbine stages, diametrically opposite to normal reheating practice in steam plants.

Energy and mass balances are presented for a 200 MWe Kalina bottoming cycle. Kalina cycle performance is compared to a triple pressure steam plant. At a peak cycle temperature of 950° F the Kalina plant produces 223.5 MW vs. 192.6 MW for the triple pressure steam plant, an improvement of 16.0 percent. Reducing the economizer pinch point to 15° F results in a performance improvement in excess of 30 percent.
Development and Testing of the 13MW Class Heavy Duty Gas Turbine MF-111
Authors: Akita Eiji , Aoyama Kuniaki , Tsukuda Yoshiaki , Fukue Ichiro , Aoki Sunao
Published: March 2015

A new 13 MW class heavy duty gas turbine “MF-111” with the combustor outlet temperature of 1250°C (1523 K) was developed and tested.

The thermal efficiency of MF-111 is designed to be 32% for simple-cycle and 45% in combined-cycle operation.

MF-111 has single-shaft configuration, 15-stage axial flow compressor, 8 cannular type combustors and 3-stage axial flow turbine.

Advanced cooling technology was incorporated for the turbine and the combustor design to be capable of higher combustor outlet temperature.

The prototype was shoptested at full load in April, 1986. The performance and the metal temperatures of hot parts were confirmed to well satisfy the design goal. The first machine of MF-111 started the commercial operation from August, 1986 and has logged satisfactory operations.
Topping the Groningen Steam Turbine Plant With a Gas Turbine
Authors: Veenema J. J. , Brueckner H. , Finckh H. H.
Published: March 2015

Retrofitting existing steam turbine power plants with a gas turbine topping cycle can greatly enhance their efficiency to levels comparable with those of plants originally constructed as fully fired combined cycles. The economic benefits of this approach make it so attractive that utilities in the Netherlands are at present converting well over 3000 MW of conventional steam power. This paper describes various technical and economic aspects of topping the natural gas-fired 600 MW Eemscentrale 2 unit. In particular, the improvements made to the thermodynamic cycle, the adaptation of its components and the partial load behavior of the plant are discussed. The economic analysis reveals that significant fuel savings justify the capital investment.
Investigation of Integrated Selection of Optimum Engine Cycle Parameters
Authors: Jin Zhang , Daguang Chen , Xingjian Zhu , Zhili Zhu
Published: March 2015

From the viewpoint of systems engineering, a method for integrated selection of the optimal engine cycle parameters and control scheme to satisfy the flight requirement of an aircraft is given. This method concerns the matching and interaction of the engine with the aircraft. In this paper, a simplified engine mathematical model with very short computer execution time is used. An integrated mathod and a synthesis computer program in a brick form for optimum engine cycle parameters and control scheme selection are provided which are very flexible, and can be used for the conceptual design of new engine, and for the modification of production engines. It is effective in shortening the optimal engine selecting time. An example is given which shows the significance of integrated selection of optimum engine cycle parameters and the feasibility of the method.
Friction Damping of Random Vibration in Gas Turbine Engine Airfoils
Authors: Sinha Alok
Published: March 2015

The optimal value of slip load is calculated for a frictionally damped turbine blade subjected to random excitation. The nature of excitation is assumed to be Gaussian white noise and the statistics of response are obtained using equivalent linearization approach. The results from this technique are compared with those from numerical simulations.
A Diagnosis of Failure of a Compressor Blade
Authors: Kubiak J. A. , Franco J. M. , Carnero A. , Rothhirsch L A. , Aguirre R. J.
Published: March 2015

The methodology and the procedure of diagnosis of a cracked stationary blade of a compressor due to high cycle fatigue is presented. The natural frequencies of the blades and a stator row were measured and an analysis of the casing vibrations during start-up and under load conditions of the compressor was conducted in a search for the cause of the failure. Using finite element code the natural frequencies and the vibratory stresses of the stator row blades (vanes) were computed. The computed maximum vibratory stresses in the vane were concentrated in the location of the crack which originated from the welded joint. It was concluded that the welded joint requires modification.