Physical Aspects of Deposition From Coal-Water Fuels Under Gas Turbine Conditions

1990 ◽  
Vol 112 (1) ◽  
pp. 9-14 ◽  
Author(s):  
R. A. Wenglarz ◽  
R. G. Fox
Keyword(s):  
Gas Turbine ◽  
Combustion Products ◽  
Control Measures ◽  
Unburned Carbon ◽  
Test Results ◽  
Gas Temperature ◽  
Hot Gas ◽  
Stators And Rotors ◽  
Temperature Surface ◽  
Deposition Control

Deposition, erosion, and corrosion (DEC) experiments were conducted using three coal-water fuels (CWF) in a staged subscale turbine combustor operated at conditions of a recuperated turbine. This rich-quench-lean (RQL) combustor appears promising for reducing NOx levels to acceptable levels for future turbines operating with CWF. Specimens were exposed in two test sections to the combustion products from the RQL combustor. The gas and most surface temperatures in the first and second test sections represented temperatures in the first stators and rotors, respectively, of a recuperated turbine. The test results indicate deposition is affected substantially by gas temperature, surface temperature, and unburned carbon due to incomplete combustion. The high rates of deposition observed at first stator conditions showed the need for additional tests to identify CWF coals with lower deposition tendencies and to explore deposition control measures such as hot gas cleanup.

scholarly journals Physical Aspects of Deposition From Coal Water Fuels Under Gas Turbine Conditions

1989 ◽  
Author(s):  
Richard A. Wenglarz ◽  
Ralph G. Fox
Keyword(s):  
Gas Turbine ◽  
Combustion Products ◽  
Control Measures ◽  
Unburned Carbon ◽  
Test Results ◽  
Gas Temperature ◽  
Hot Gas ◽  
Stators And Rotors ◽  
Temperature Surface ◽  
Deposition Control

Deposition, erosion, and corrosion (DEC) experiments were conducted using three coal-water fuels (CWF) in a staged subscale turbine combustor operated at conditions of a recuperated turbine. This rich-quench-lean (RQL) combustor appears promising for reducing NOx levels to acceptable levels for future turbines operating with CWF. Specimens were exposed in two test sections to the combustion products from the RQL combustor. The gas and most surface temperatures in the first and second test sections represented temperatures in the first stators and rotors, respectively, of a recuperated turbine. The test results indicate deposition is affected substantially by gas temperature, surface temperature, and unburned carbon due to incomplete combustion. The high rates of deposition observed at first stator conditions showed the need for additional tests to identify CWF coals with lower deposition tendencies and to explore deposition control measures such as hot gas cleanup.

Design and Analysis of a Real-Time Hot Gas Temperature Estimator for Heavy-Duty Gas Turbines

2015 ◽  
Author(s):  
Eric A. Müller ◽  
Adrian Ticǎ
Keyword(s):  
Real Time ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Gas Temperature ◽  
Heavy Duty ◽  
Component Level ◽  
Load Range ◽  
Hot Gas ◽  
Dynamic Tracking ◽  
Heavy Duty Gas Turbine

The knowledge about a relevant process and lifetime indicative quantity, such as the hot gas temperature, is crucial for the control of a gas turbine. Since this indicative process quantity usually cannot be directly measured, it has to be estimated. The paper describes a model-based method to accurately estimate in real-time the hot gas temperature of a heavy-duty gas turbine. The method follows a well-balanced trade-off between resulting prediction accuracy and involved computational complexity. It takes advantage of the capability of a component-level dynamic model to predict the system behaviour and of the capacity of a dynamic tracking filter to adapt to the current gas turbine conditions. In a simulation study, it is shown that the proposed design can provide an accurate hot gas temperature estimation over the entire gas turbine load range, along the gas turbine lifecycle, and during fast transient manoeuvres.

A Combustion Study of Gas Turbines Using Multi-Species/Reacting Computational Fluid Dynamic

2002 ◽  
Author(s):  
Sasan Armand ◽  
Mei Chen
Keyword(s):  
Carbon Monoxide ◽  
Gas Turbine ◽  
Environmental Contamination ◽  
Gas Turbines ◽  
Gas Flow ◽  
Fluid Dynamic ◽  
Combustion Products ◽  
Contamination Level ◽  
Short Term ◽  
Hot Gas

A multi-species/reacting combustion study was performed. The focus of the study was to quantify the effects of variation in air extraction and power rates on flame/outlet temperatures of a General Electric (GE), Frame 5 gas turbine. The environmental contamination level due to generation of carbon monoxide was also reported. GE, Frame 5 gas turbine has been widely used around the world for power generation, and as mechanical drives. The combustion products were examined throughout a range of air extraction rates, upon which it was determined that the combustion liners were susceptible to damage at air extraction rates above 10%, and the environmental contamination level due to carbon monoxide was increased. Furthermore, the gas flow exiting the combustion liner became non-homogeneous (i.e. a pocket of relatively hot gas formed in the middle of the flow path), which would cause damage to the downstream components. In conclusion, the short-term monetary gains from using compressed air from a gas turbine do not justify the costs of down time for repairs and the replacement of expensive hot-gas-path components.

scholarly journals Effect of Gas and Metal Temperatures on Gas Turbine Deposition

1982 ◽  
Author(s):  
Arthur Cohn
Keyword(s):  
Gas Turbine ◽  
Deposition Rate ◽  
Maximum Rate ◽  
Combustion Products ◽  
Metal Temperature ◽  
Residual Oil ◽  
Gas Temperature ◽  
Deposition Rates ◽  
Type Fuel ◽  
Oil Type

A number of test projects have measured the deposition rates of the combustion products of residual-oil-type fuel. This paper analyzes those results to obtain information on he effects of the gas and metal temperatures on the deposition rates. While the data is far from complete, certain major trends result from the data. For a given gas temperature, the deposition rate increases with decreasing metal temperature below the level of the gas temperature until a maximum rate is reached at ∼1200°F (650°C); then the deposition rate decreases as the metal temperature is further lowered and becomes small at metal temperatures near 700°F (370°C). For a given metal temperature, the deposition rate increases with higher gas temperatures. This may occur at an increasing rate for gas temperatures above 2000°F (1100°C).

scholarly journals АНАЛИТИЧЕСКОЕ ОПРЕДЕЛЕНИЕ ИСТИННОЙ УДЕЛЬНОЙ ИЗОБАРНОЙ ТЕПЛОЁМКОСТИ КОМПОНЕНТ ВОЗДУХА И ПРОДУКТОВ СГОРАНИЯ С УЧЁТОМ ВЛИЯНИЯ ТЕМПЕРАТУРЫ И ДАВЛЕНИЯ И ЭФФЕКТА ТЕРМИЧЕСКОЙ ДИССОЦИАЦИИ

2019 ◽  
pp. 4-17
Author(s):  
Майя Владимировна Амброжевич ◽  
Михаил Анатольевич Шевченко
Keyword(s):  
Heat Capacity ◽  
Gas Turbine ◽  
Pressure Ratio ◽  
Thermal Dissociation ◽  
Combustion Products ◽  
Heat Capacities ◽  
Isobaric Heat Capacity ◽  
Working Fluid ◽  
Gas Temperature ◽  
Temperature And Pressure

The basic thermophysical parameter of the working fluid of all thermal machines without exception is isobaric heat capacity (specific heat at constant pressure). Traditionally, in engineering calculations of isobaric heat capacity are determined as a tabular value for average heat capacities, or approximated with a square parabola within a given temperature range. Isobaric heat capacity is a function of temperature only. At the current level of GTE development, when the overall compressor pressure ratio is already up to 50 and the tendency of its increase remains it is unacceptable to neglect the pressure. However, the turbine inlet gas temperature also rises that will inevitably lead to the effect of thermal dissociation in the combustion products of the gas turbine engine. The studies of the thermal dissociation effect influence on the parameters of the working process of advanced GTE show that this ignoring leads to computational errors. At the present time, there are mathematical models that allow calculating the isobaric heat capacity as a function of temperature and pressure (taking into account the effect of thermal dissociation) but they are laborious, which is not always practical when estimate calculations performing and program algorithms writing. Consequently, the authors posed the problem of obtaining of simple analytic relationships that make it possible to calculate the isobaric heat capacity as a function of temperature and pressure (taking into account the effect of thermal dissociation). Based on the tabular data for the main components of the gas turbine combustion products within a given range of pressures and temperatures (nitrogen: p = 1 ... 200 bar, T = 150 ... 2870 K, oxygen: p = 1 ... 200 bar, T = 210 ... 2870 K, argon: p = 1 ... 200 bar, T = 190 ... 1300 K, the water vapor: p = 0.1 ... 200 bar, T = 640 ... 1250 K and p = 0.1 ... 400 bar and T = 1250 ... 3200 K, carbon dioxide: p = 1 ... 200 bar, T = 390 ... 2600 K), analytical dependencies were obtained for the calculation of isobaric heat capacities as functions of temperature and pressure taking into account the effect of thermal dissociation. The results of the calculations were compared with tabulated experimental data.

Test Results of Low NOx Catalytic Combustors for Gas Turbines

1994 ◽  
Vol 116 (3) ◽  
pp. 511-516 ◽  
Author(s):  
Y. Ozawa ◽  
J. Hirano ◽  
M. Sato ◽  
M. Saiga ◽  
S. Watanabe
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Combustion Method ◽  
Combustion Efficiency ◽  
Test Results ◽  
Gas Temperature ◽  
Combustion Gas ◽  
Catalytic Combustor ◽  
Combustion Tests

Catalytic combustion is an ultralow NOx combustion method, so it is expected that this method will be applied to a gas turbine combustor. However, it is difficult to develop a catalytic combustor because catalytic reliability at high temperature is still insufficient. To overcome this difficulty, we designed a catalytic combustor in which premixed combustion was combined. By this device, it is possible to obtain combustion gas at a combustion temperature of 1300°C while keeping the catalytic temperature below 1000°C. After performing preliminary tests using LPG, we designed two types of combustor for natural gas with a capacity equivalent to one combustor used in a 20 MW class multican-type gas turbine. Combustion tests were conducted at atmospheric pressure using natural gas. As a result, it was confirmed that a combustor in which catalytic combustor segments were arranged alternately with premixing nozzles could achieve low NOx and high combustion efficiency in the range from 1000°C to 1300°C of the combustor exit gas temperature.

2750 Deg F Engine Test of a Transpiration Air-Cooled Turbine

1971 ◽  
Vol 93 (2) ◽  
pp. 238-248 ◽  
Author(s):  
S. L. Moskowitz ◽  
S. Lombardo
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Effective Means ◽  
Inlet Temperature ◽  
Test Results ◽  
Gas Temperature ◽  
Supersonic Aircraft ◽  
Turbine Inlet ◽  
Marine Applications ◽  
Turbine Blading

The development of gas turbine engines for advanced subsonic and supersonic aircraft as well as for potential utilization of these high performance engines for stationary and marine applications requires, as a key element, the ability to operate at turbine inlet temperatures above the actual melting temperatures of the turbine materials. A limit on gas temperature levels is imposed by the fact that current alloys available for use in turbines, exhibit inadequate strength and oxidation characteristics above 1600–1800 deg F. However, the performance gains offered by operating engines at a high turbine inlet temperature may be realized through the application of an efficient method of cooling the highly stressed turbine components. As a step toward demonstrating that transpiration cooling of turbine blading is an effective means for achieving reliable and efficient gas turbine operation in a high gas temperature environment, a full-scale engine was tested at average gas temperatures of 2750–2800 deg F with a transpiration cooled turbine fabricated from normally used turbine alloys which are limited to metal temperatures of 1600–1800 deg F. The authors discuss the design of the transpiration air-cooled turbine, the technique used in fabricating the porous turbine blading, and the experimental test results obtained from operating the high-temperature engine. Furthermore, correlation of the test results on blade cooling with analytical predictions is presented.

High Temperature Film Cooling Test Facility and Preliminary Test Results

2012 ◽  
Author(s):  
D. L. Straub ◽  
T. G. Sidwell ◽  
K. H. Casleton ◽  
M. A. Alvin ◽  
S. Chien ◽  
...  
Keyword(s):  
High Temperature ◽  
Film Cooling ◽  
Preliminary Test ◽  
Test Sample ◽  
Test Facility ◽  
Test Results ◽  
Gas Temperature ◽  
University Of Pittsburgh ◽  
Hot Gas ◽  
The University

This paper describes a new high temperature test facility developed through a collaborative effort between the University of Pittsburgh and the Department of Energy’s National Energy Technology Laboratory (NETL). The scope of this paper will include a description of this experimental test facility and a discussion of some test results collected from a flat plate (Haynes 230) using a single row of fan-shaped film cooling holes. This test specimen has been tested at two different pressures (i.e., 1.3 and 3 bar). The hot gas path flow velocity (i.e., 60 m/s) and the hot gas temperature (i.e., 1300 K) have been maintained as a constant for these tests. At each of these test conditions, five different film cooling blowing ratio conditions have been evaluated, including a condition with no film cooling. The overall cooling effectiveness and the reduction in heat flux for a point near the center of the test sample are reported and discussed.

scholarly journals Development of 300kW-Class Ceramic Gas Turbine (CGT301) Engine System

1995 ◽  
Author(s):  
Masashi Tatsuzawa ◽  
Tomoki Taoka ◽  
Takeshi Sakida ◽  
Shinya Tanaka
Keyword(s):  
Gas Turbine ◽  
Development Process ◽  
Thermal Stresses ◽  
Turbine Blades ◽  
Axial Flow ◽  
Thermal Conditions ◽  
Fatigue Tests ◽  
Test Results ◽  
Gas Temperature ◽  
Engine System

CGT301 is a recuperated, single-shaft ceramic gas turbine for co-generation use. Ceramic parts are used in the hot section of the engine, such as turbine blades, nozzle vanes, combustor liners, heat exchanger elements and gas path parts. These ceramic parts are designed axi-symmetrically to reduce their sizes and thermal stresses and to avoid their unexpected deformations. The turbine is a two-stage axial flow type. As a primary feature of this turbine, the rotors are composed of ceramic blades inserted into metallic disks. The ceramic parts of the engine system have been tested before installing them in the engine to assure their reliability in the following manner. The ceramic blades have been examined by hot-spin test with the gas temperature of 1100°C and up to 110% of the engine rated speed. The ceramic stationary parts such as nozzle vanes, combustor liners and gas path parts, have been assembled and installed in a test rig with almost the same constraint and thermal conditions as the engine, and thermal fatigue tests of 100 cycles between 1200°C and 300°C have been conducted. After the proof tests of ceramic parts, they have been installed in the engine, step by step. Finally, the engine has been operated with a TIT of 1200°C at the engine rated speed of 56000 rpm. The present paper describes the development process and shows test results of the ceramic gas turbine at a TIT of 1200°C.

scholarly journals Gas-Turbine Loading Schedule for Maximum Life of the Hot Gas Path Components

1970 ◽  
Author(s):  
Stanislaw Bednarski ◽  
C. N. Shen
Keyword(s):  
Plastic Strain ◽  
Thermal Shock ◽  
Gas Turbine ◽  
Firing Temperature ◽  
Thermal Fatigue ◽  
Computational Procedure ◽  
Time Dependent ◽  
Gas Temperature ◽  
Hot Gas ◽  
Loading Process

The paper describes development of a computational procedure for determining the optimal firing temperature schedule during loading of the gas turbine. It is assumed that the temperature has to be increased in a pre-determined time in a way that will minimize thermal fatigue deterioration of the turbine hot gas path elements. The gas temperature is constrained to lie between certain time-dependent limits all through the transient. The maximum plastic strain in a given loading process is taken as a measure of parts deterioration. The calculations performed are for hollow, stationary airfoils of a gas turbine, but the method is easily adaptable to full profiles and rotational airfoils as well as non-turbine applications where temperature is to be altered while thermal shock is to be minimized. A numerical example is given for illustration of the method.

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