scholarly journals Design issues and performance of a chemically recuperated aeroderivative gas turbine

1998 ◽  
Vol 212 (5) ◽  
pp. 315-329 ◽  
Author(s):  
C Carcasci ◽  
B Facchini ◽  
S Harvey
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Research Work ◽  
Performance Characteristics ◽  
Design Issues ◽  
Steam Reformer ◽  
Turbine Engine ◽  
Part Load ◽  
Surface Areas ◽  
Methane Steam

A number of innovative gas turbine cycles have been proposed lately, including the humid air turbine (HAT) and the chemically recuperated gas turbine (CRGT). The potential of the CRGT cycle lies in the ability to generate power with a high efficiency and ultra-low NOx emissions. Much of the research work published on the CRGT cycle is restricted to an analysis of the thermodynamic potential of the cycle. However, little work has been devoted to discussion of some of the relevant design and operation issues of such cycles. In this paper, part-load performance characteristics are presented for a CRGT cycle based on an aeroderivative gas turbine engine adapted for chemical recuperation. The paper also includes discussion of some of the design issues for the methane-steam reformer component of the cycle. The results of this study show that large heat exchange surface areas and catalyst volumes are necessary to ensure sufficient methane conversion in the methane steam reformer section of the cycle. The paper also shows that a chemically recuperated aeroderivative gas turbine has similar part-load performance characteristics compared with the corresponding steam-injected gas turbine (STIG) cycle.

Design Issues for the Methane-Steam Reformer of a Chemically Recuperated Gas Turbine Cycle

1998 ◽  
Author(s):  
Carlo Carcasci ◽  
Simon Harvey
Keyword(s):  
Gas Turbine ◽  
Heat Recovery ◽  
High Efficiency ◽  
Catalytic Reduction ◽  
Research Effort ◽  
Methane Steam Reforming ◽  
Design Issues ◽  
Cold Side ◽  
Steam Reformer ◽  
Methane Steam

Significant research effort is currently centered on developing advanced gas turbine systems for electric power generation applications. A number of innovative gas turbine cycles have been proposed lately, including the Humid Air Turbine (HAT), and the Chemically Recuperated Gas Turbine (CRGT). The potential of the CRGT cycle lies in the ability to generate power with a high efficiency while achieving ultra-low NO emissions without the need for selective catalytic reduction of the exhaust gases. However, much of the work that has been published on such cycles is restricted to a discussion of the thermodynamic potential of the cycle, and little work has focussed on discussion of some of the specific design issues associated with such a cycle. More specifically, design of the chemical recuperation heat recovery device involves a complex design trade-off in order to achieve a design with acceptable hot and cold-side pressure drops and acceptable overall dimensions. The design of such a heat recovery device is more complex than that of a traditional heat recovery steam generator (HRSG), since the methane steam reformer must not only allow sufficient heat transfer to occur, but also allow a sufficient cold side residence time, so that the methane steam reforming reactions can come close to equilibrium, ensuring maximal methane conversion. In this work, the authors present a code capable of performing the design of a methane steam reformer heat recovery device based on a heat exchanger geometry similar to that of a traditional HRSG. The purpose of the paper is to discuss the key parameters relevant to the design of a CRGT MSR reactor, and how these parameters interact with the rest of the cycle. Various design options are discussed, and the results of a parametric analysis are presented, leading to the identification of several suitable geometries.

The Part-Load Performance of Various Gas-Turbine Engine Schemes

1948 ◽  
Vol 159 (1) ◽  
pp. 198-219 ◽  
Author(s):  
D. H. Mallinson ◽  
W. G. E. Lewis
Keyword(s):  
Heat Exchange ◽  
Gas Turbine ◽  
Simple Form ◽  
Constant Pressure ◽  
Performance Characteristics ◽  
Turbine Engines ◽  
Turbine Engine ◽  
Part Load ◽  
Pressure Cycle ◽  
Marine Applications

The literature on the gas turbine already contains much information concerning the performance of the “constant-pressure” cycle both in its simple form and in its more complicated forms involving intercooled compression, reheated expansion, and heat exchange. Such information enables the design performance of a particular engine to be estimated, but there appears to be very little published work to help the designer to foretell what changes in performance are to be expected when particular engines operate at non-design conditions. What work there is seems to have been restricted to very simple engines, and is often further limited by the assumption of unalterable component performance characteristics. In this lecture we attempt to include in a general comparison of part-load performance characteristics not only the simpler designs but also some of the more complex turbine engines which will be needed for land and marine applications. At the same time, by considering, in appropriate cases, the influence of changes in the assumed component performance features on the part-load operation of an engine, a broadening of the basis of comparison is made possible. As a result of the work we shall describe we feel that, although as yet so little of the possible field of investigation has been surveyed, it is nevertheless possible to indicate the main guiding principles by which the comparative part-load performance of different gas turbine schemes may be assessed.

scholarly journals Design and Off-Design Analysis of a CRGT Cycle Based on the LM2500-STIG Gas Turbine

1998 ◽  
Author(s):  
Carlo Carcasci ◽  
Bruno Facchini ◽  
Simon Harvey
Keyword(s):  
Performance Analysis ◽  
Gas Turbine ◽  
High Efficiency ◽  
Catalytic Reduction ◽  
Research Effort ◽  
Research Work ◽  
Simulation Code ◽  
Methane Steam ◽  
Cycle Simulation ◽  
Significant Research

Significant research effort is currently centered on developing advanced gas turbine systems for electric power generation applications. A number of innovative gas turbine cycles have been proposed lately, including the Humid Air Turbine (HAT), and the Chemically Recuperated Gas Turbine (CRGT). The potential of the CRGT cycle lies in the ability to generate power with a high efficiency while achieving ultra-low NO emissions without the need for selective catalytic reduction of the exhaust gases. Much of the research work published on the CRGT cycle is restricted to an analysis of the thermodynamic potential of the cycle. However, a detailed performance analysis of such cycles requires the development of a suitable cycle simulation code, capable of simulating cycle operation at the design point and in part load conditions. In this paper, the authors present a modular code for complex gas turbine cycle simulations. The code includes a module for design and off-design simulation of the methane-steam reformer chemical heat recovery device of a CRGT cycle. The code is then used to perform a detailed design and off-design performance analysis of a CRGT cycle based on the LM2500-STIG cycle adapted for chemical recuperation.

The ultra-high efficiency gas turbine engine, UHEGT, Part II: A numerical study on reducing the stator blade surface temperature by indexing fuel injectors and using film cooling

2020 ◽  
pp. 095765092097353
Author(s):  
Seyed M Ghoreyshi ◽  
Meinhard T Schobeiri
Keyword(s):  
Surface Temperature ◽  
Gas Turbine ◽  
Film Cooling ◽  
Total Pressure ◽  
High Efficiency ◽  
Combustion Process ◽  
Blade Surface ◽  
Turbine Engine ◽  
Fuel Injectors ◽  
Stator Blade

In the Ultra-High Efficiency Gas Turbine Engine, UHEGT (introduced in our previous studies) the combustion process is no longer contained in isolation between the compressor and turbine, rather distributed within the axial gaps before each stator row. This technology substantially increases the thermal efficiency of the engine cycle to above 45%, increases power output, and reduces turbine inlet temperature. Since the combustion process is brought into the turbine stages in UHEGT, the stator blades are exposed to high-temperature gases and can be overheated. To address this issue and reduce the temperature on the stator blade surface, two different approaches are investigated in this paper. The first is indexing (clocking) of the fuel injectors (cylindrical tubes extended from hub to shroud), in which the positions of the injectors are adjusted relative to each other and the stator blades. The second is film cooling, in which cooling holes are placed on the blade surface to bring down the temperature via coolant injection. Four configurations are designed and studied via computational fluid dynamics (CFD) to evaluate the effectiveness of the two approaches. Stator blade surface temperature (as the main objective function) along with other performance parameters such as temperature non-uniformity at rotor inlet, total pressure loss over the injectors, and total power production by rotor are evaluated for all configurations. The results show that indexing presents the most promising approach in reducing the stator blade surface temperature while producing the least amount of total pressure loss.

scholarly journals 2MW Class High Efficiency Gas Turbine IM270 for Co-Generation Plants

1996 ◽  
Author(s):  
Hideo Kobayashi ◽  
Shogo Tsugumi ◽  
Yoshio Yonezawa ◽  
Riuzou Imamura
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Mechanical Design ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Maintenance Cost ◽  
Turbine Engine ◽  
Generation Plant ◽  
Emission Regulation ◽  
Heavy Duty Gas Turbine

IHI is developing a new heavy duty gas turbine engine for 2MW class co-generation plants, which is called IM270. This engine is a simple cycle and single-spool gas turbine engine. Target thermal efficiency is the higher level in the same class engines. A dry low NOx combustion system has been developed to clear the strictest emission regulation in Japan. All parts of the IM270 are designed with long life for low maintenance cost. It is planned that the IM270 will be applied to a dual fluid system, emergency generation plant, machine drive engine and so on, as shown in Fig.1. The development program of IM270 for the co-generation plant is progress. The first prototype engine test has been started. It has been confirmed that the mechanical design and the dry low NOx system are practical. The component tuning test is being executed. On the other hand, the component test is concurrently in progress. The first production engine is being manufactured to execute the endurance test using a co-generation plant at the IHI Kure factory. This paper provides the conceptual design and status of the IM270 basic engine development program.

scholarly journals A Model and State-Space Controllers for an Intercooled, Regenerated (ICR) Gas Turbine Engine

1992 ◽  
Author(s):  
J. W. Watts ◽  
T. E. Dwan ◽  
R. W. Garman
Keyword(s):  
State Space ◽  
Gas Turbine ◽  
High Efficiency ◽  
Linear Quadratic Regulator ◽  
Gas Turbine Engine ◽  
Linear Quadratic ◽  
Turbine Engine ◽  
Simulation Language ◽  
Linear State ◽  
High Level

A two-and-one-half spool gas turbine engine was modeled using the Advanced Computer Simulation Language (ACSL), a high level simulation environment based on FORTRAN. A possible future high efficiency engine for powering naval ships is an intercooled, regenerated (ICR) gas turbine engine and these features were incorporated into the model. Utilizing sophisticated instructions available in ACSL linear state-space models for this engine were obtained. A high level engineering computational language, MATLAB, was employed to exercise these models to obtain optimal feedback controllers characterized by the following methods: (1) state feedback; (2) linear quadratic regulator (LQR) theory; and (3) polygonal search. The methods were compared by examining the transient curves for a fixed off-load, and on-load profile.

Analysis on the Performance Characteristics of SOFC/GT Hybrid Systems Based on a Commercially Available MW-Class Gas Turbine

2005 ◽  
Author(s):  
Tae Won Song ◽  
Jeong L. Sohn ◽  
Tong Seop Kim ◽  
Sung Tack Ro
Keyword(s):  
Gas Turbine ◽  
Hybrid System ◽  
Guide Vane ◽  
Control Strategies ◽  
Operating Conditions ◽  
Performance Characteristics ◽  
Inlet Guide Vane ◽  
Part Load ◽  
Optimal Power ◽  
Selection Of

To investigate the possible applications of the SOFC/MGT hybrid system to large electric power generations, a study for the kW-class hybrid power system conducted in our group is extended to the MW-class hybrid system in this study. Because of the matured technology of the gas turbine and commercial availability in the market, it is reasonable to construct a hybrid system with the selection of a gas turbine as an off-the-shelf item. For this purpose, the performance analysis is conducted to find out the optimal power size of the hybrid system based on a commercially available gas turbine. The optimal power size has to be selected by considering specifications of a selected gas turbine which limit the performance of the hybrid system. Also, the cell temperature of the SOFC is another limiting parameter to be considered in the selection of the optimal power size. Because of different system configuration of the hybrid system, the control strategies for the part-load operation of the MW-class hybrid system are quite different from the kW-class case. Also, it is necessary to consider that the control of supplied air to the MW-class gas turbine is typically done by the variable inlet guide vane located in front of the compressor inlet, instead of the control of variable rotational speed of the kW-class micro gas turbine. Performance characteristics at part-load operating conditions with different kinds of control strategies of supplied fuel and air to the hybrid system are investigated in this study.

Development of the Centaur Type H Gas Turbine Engine

1985 ◽  
Author(s):  
G. L. Padgett ◽  
W. W. Davis
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
State Of The Art ◽  
Gas Turbine Engine ◽  
Development Plan ◽  
Inlet Temperature ◽  
Market Place ◽  
Turbine Inlet Temperature ◽  
Turbine Engine ◽  
Computer Aided

In response to the needs of the market place for turbines in the 5000 to 6000 hp class, Solar Turbines Incorporated has responded with an uprate of their Centaur engine. Discussed in this paper are the features of the uprated engine, the Development Plan and the methodology for incorporating into the design the advanced aerodynamic and mechanical technology of the Mars engine. The Mars engine is a high efficiency 12,500 hp engine which operates at a turbine inlet temperature of 1935°F. State-of-the-art computer aided methods have been applied to produce the design, and the results from this approach are displayed.

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