The Design and Development of an Electrically Operated Fuel Control Valve for Industrial Gas Turbines

1991 ◽  
Author(s):  
A. G. Salsi ◽  
F. S. Bhinder
Keyword(s):  
Gas Turbines ◽  
Entire Range ◽  
Control Valve ◽  
Performance Characteristics ◽  
Design And Development ◽  
Wide Range ◽  
Industrial Gas Turbines

Industrial gas turbines operate over a wide range of combinations of loads and speeds. The fuel control valve must be designed to cover the entire range precisely. The design of an electrically operated fuel control valve is described and comparison between the predicted and measured performance characteristics is shown.

A Single Valve Gas Fuel Flow Control for Gas Turbines

1993 ◽  
Author(s):  
William O. Statler
Keyword(s):  
Flow Control ◽  
Gas Turbine ◽  
Mass Flow ◽  
Gas Turbines ◽  
Control Valve ◽  
Control Loop ◽  
Fuel Flow ◽  
Wide Range ◽  
Gas Fuel ◽  
Flow Element

A method of mass flow control of fuel gas to a gas turbine has been developed and applied in control retrofits to existing gas turbines. Unlike other gas flow control systems in use on gas turbines this system actually measures the mass flow going into the turbine combustion system and uses this value as the feedback in a control loop to modulate a single throttling control valve. The system utilizes a common venturi flow element to develop a differential pressure which, along with inlet pressure and temperature, is used to compute the mass flow. Locating this flow element downstream of the control valve where the pressure is low at low flows reduces the usual problem of the wide range of delta-pressure (proportional to the square of the mass flow) to a workable level. This extends the range of this common type of flow measurement system enough that it becomes practical to apply it to the gas fuel flow control loop of a gas turbine.

Advanced Catalytic Pilot for Low NOx Industrial Gas Turbines

2002 ◽  
Author(s):  
Hasan Karim ◽  
Kent Lyle ◽  
Shahrokh Etemad ◽  
Lance Smith ◽  
William Pfefferle ◽  
...  
Keyword(s):  
High Pressure ◽  
Surface Temperature ◽  
Gas Turbines ◽  
Lean Burn ◽  
Pressure Testing ◽  
Wide Range ◽  
Industrial Gas Turbines ◽  
Design And Testing ◽  
Pilot Burner ◽  
Load Conditions

This paper describes the design and testing of a catalytically-stabilized pilot burner for current and advanced Dry Low NOx (DLN) gas turbine combustors. In this paper, application of the catalytic pilot technology to industrial engines is described using Solar Turbines’ Taurus 70 engine. The objective of the work described is to develop the catalytic pilot technology and document the emission benefits of catalytic pilot technology when compared to higher, NOx producing pilots. The catalytic pilot was designed to replace the existing pilot in the existing DLN injector without major modification to the injector. During high pressure testing, the catalytic pilot showed no incidence of flashback or autoignition while operating over wide range of combustion temperatures. The catalytic reactor lit off at a temperature of approximately 598K (325°C/617°F) and operated at simulated 100% and 50% load conditions without a preburner. At high pressure, the maximum catalyst surface temperature was similar to that observed during atmospheric pressure testing and considerably lower than the surface temperature expected in lean-burn catalytic devices. In single injector rig testing, the integrated assembly of the catalytic pilot and Taurus 70 injector demonstrated NOx and CO emission less than 5 ppm @ 15% O2 for 100% and 50% load conditions along with low acoustics. The results demonstrate that a catalytic pilot burner replacing a diffusion flame or partially-premixed pilot in an otherwise DLN combustor can enable operation at conditions with substantially reduced NOx emissions.

Measurement of Heat Transfer and Flow Structures in a Closed Rotating Cavity

2022 ◽  
Author(s):  
Richard Jackson ◽  
Hui Tang ◽  
James Scobie ◽  
J. Michael Owen ◽  
Gary Lock
Keyword(s):  
Heat Transfer ◽  
Gas Turbines ◽  
Pressure Sensors ◽  
Flow Structures ◽  
Closed Cavity ◽  
Experimental Range ◽  
Wide Range ◽  
Industrial Gas Turbines ◽  
Induced Flow ◽  
Compressibility Effects

Abstract Buoyancy-induced flow occurs inside the rotating compressor cavities of gas turbines. These cavities are usually open at the inner radius, but in some industrial gas turbines, they are effectively closed. This paper presents measurements of the disc heat transfer and rotating flow structures in a closed cavity over a wide range of engine relevant conditions. These experimentally derived distributions of disc temperature and heat flux are the first of their kind to be published. The radial distribution of the non-dimensional disc temperature virtually collapsed onto a single curve over the full experimental range. There was a small, monotonic departure from this common curve with increasing Reynolds number; this was attributed to compressibility effects where the core temperature increases as the rotational speed increases. These results imply that, if compressibility effects are negligible, all rotating closed cavities should have a disc temperature distribution uniquely related to the geometry and disc material; this is of important practical use to the engine designer. Unsteady pressure sensors detected either three or four vortex pairs across the experimental range. The number of pairs changed with Grashof number, and the structures slipped relative to the rotating discs by less than 1% of the disc speed.

Development of a 30PS Class Small Gas Turbine and Its Power-Up Version

1989 ◽  
Vol 111 (2) ◽  
pp. 225-231
Author(s):  
A. Hoshino ◽  
T. Sugimoto ◽  
T. Tatsumi ◽  
Y. Nakagawa
Keyword(s):  
Gas Turbines ◽  
Pulse Width Modulation ◽  
Control Valve ◽  
Single Stage ◽  
Auxiliary Equipment ◽  
High Rotational Speed ◽  
Gasoline Engines ◽  
Base Engine ◽  
Industrial Gas Turbines ◽  
Prime Movers

Due to the recent popularity of small and medium-sized industrial gas turbines in many fields, gas turbines below 100 SHP have been employed as prime movers, a power range traditionally reserved for diesel and gasoline engines. Generally speaking, however, small gas turbines have many design difficulties in thermal efficiency, high rotational speed, compact auxiliary equipment, etc., derived from limitations of their dimensions. Small gas turbines S5A-01 and S5B-01, which have 32 PS output power at standard conditions, have been developed and are being produced. Presently, a 30 percent growth rated power producer for S5A-02 and S5B-02 gas turbines is under development. These engines’ configurations are as follows: single-stage centrifugal compressor; single-stage radial turbine; single can combustor; hybrid fuel nozzle with pressure atomizer and airblast atomizer; fuel control valve with pulse width modulation system; electric motor drive fuel pump. In this paper, the authors describe the design features and development history of the base engine and the experimental results with the growth rated version.

Evaluation of Advanced Combustors for Dry NOx Suppression With Nitrogen Bearing Fuels in Utility and Industrial Gas Turbines

1982 ◽  
Vol 104 (2) ◽  
pp. 429-438 ◽  
Author(s):  
M. B. Cutrone ◽  
M. B. Hilt ◽  
A. Goyal ◽  
E. E. Ekstedt ◽  
J. Notardonato
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Water Injection ◽  
Operating Conditions ◽  
Department Of Energy ◽  
Technical Program ◽  
Wide Range ◽  
Industrial Gas Turbines ◽  
Low Levels

The work described in this paper is part of the DOE/LeRC Advanced Conversion-Technology Project (ACT). The program is a multiple contract effort with funding provided by the Department of Energy, and technical program management provided by NASA LeRC. Combustion tests are in progress to evaluate the potential of seven advanced combustor concepts for achieving low NOx emissions for utility gas turbine engines without the use of water injection. Emphasis was on the development of the required combustor aerothermodynamic features for burning high nitrogen fuels. Testing was conducted over a wide range of operating conditions for a 12:1 pressure ratio heavy-duty gas turbine. Combustors were evaluated with distillate fuel, SRC-II coal-derived fuel, residual fuel, and blends. Test results indicate that low levels of NOx and fuel-bound nitrogen conversion can be achieved with rich-lean combustors for fuels with high fuel-bound nitrogen. In addition, ultra-low levels of NOx can be achieved with lean-lean combustors for fuels with low fuel-bound nitrogen.

Comparative Analysis of Off-Design Performance Characteristics of Single and Two Shaft Industrial Gas Turbines

2002 ◽  
Author(s):  
J. H. Kim ◽  
T. S. Kim ◽  
J. L. Sohn ◽  
S. T. Ro
Keyword(s):  
Gas Turbines ◽  
Combined Cycle ◽  
Performance Characteristics ◽  
Cycle Performance ◽  
Operating Characteristics ◽  
Exhaust Temperature ◽  
Operating Modes ◽  
Recovery Capacity ◽  
Industrial Gas Turbines ◽  
Component Models

Off-design steady performance and operating characteristics of single and two shaft gas turbines for electric power generation have been investigated comparatively. A set of balance equations has been derived based on validated component models. A simultaneous calculation scheme has been employed, which is flexible to various engine configurations. Part-load performance analyses of two commercial gas turbines have been carried out to compare operating characteristics between single and two shaft engines. The predicted performance characteristics of both engines coincide soundly with the manufacturer’s data and also correspond with the inherent characteristics of each configuration. The adoption of the VIGV modulation has been addressed in order to examine the possibility of leveling up the heat recovery capacity by maintaining a high turbine exhaust temperature (TET) when those gas turbines are used for combined cycle plants. Maintaining TET at its design value as far as the VIGV modulation allows has been simulated and it has been determined that the TET control is possible at up to 40% and 50% load in the single and two shaft engine, respectively. Combined cycle performances have also been investigated for two engine configurations in different operating modes. While the VIGV modulation produces a favorable influence over the combined cycle performance of the single shaft configuration, the two shaft engine does not appear to be effectively improved by the VIGV modulation since the degradation of gas turbine performance counteracts the advantage of the higher performance of the bottoming (steam turbine) cycle.

Advanced Catalytic Pilot for Low NOx Industrial Gas Turbines

2003 ◽  
Vol 125 (4) ◽  
pp. 879-884 ◽  
Author(s):  
H. Karim ◽  
K. Lyle ◽  
S. Etemad ◽  
L. L. Smith ◽  
W. C. Pfefferle ◽  
...  
Keyword(s):  
High Pressure ◽  
Surface Temperature ◽  
Gas Turbines ◽  
Lean Burn ◽  
Pressure Testing ◽  
Wide Range ◽  
Industrial Gas Turbines ◽  
Design And Testing ◽  
Pilot Burner ◽  
Load Conditions

This paper describes the design and testing of a catalytically stabilized pilot burner for current and advanced Dry Low NOx (DLN) gas turbine combustors. In this paper, application of the catalytic pilot technology to industrial engines is described using Solar Turbines’ Taurus 70 engine. The objective of the work described is to develop the catalytic pilot technology and document the emission benefits of catalytic pilot technology when compared to higher, NOx producing pilots. The catalytic pilot was designed to replace the existing pilot in the existing DLN injector without major modification to the injector. During high-pressure testing, the catalytic pilot showed no incidence of flashback or autoignition while operating over wide range of combustion temperatures. The catalytic reactor lit off at a temperature of approximately 598 K (325°C/617°F) and operated at simulated 100% and 50% load conditions without a preburner. At high pressure, the maximum catalyst surface temperature was similar to that observed during atmospheric pressure testing and considerably lower than the surface temperature expected in lean-burn catalytic devices. In single-injector rig testing, the integrated assembly of the catalytic pilot and Taurus 70 injector demonstrated NOx and CO emission less than 5 ppm @ 15% O2 for 100% and 50% load conditions along with low acoustics. The results demonstrate that a catalytic pilot burner replacing a diffusion flame or partially premixed pilot in an otherwise DLN combustor can enable operation at conditions with substantially reduced NOx emissions.

Low Heating Value Fuel Burning Capabilities of General Electric Industrial Gas Turbines

1982 ◽  
Author(s):  
R. A. Battista ◽  
R. P. Pandalai ◽  
M. B. Hilt
Keyword(s):  
Gas Turbines ◽  
Industrial Process ◽  
Small Scale ◽  
General Electric ◽  
Heating Value ◽  
Lower Heating Value ◽  
Wide Range ◽  
Industrial Gas Turbines ◽  
Gas Conditioning ◽  
Lower Heating

The advent of higher fuel prices and operational costs associated with energy production have had a profound impact on the application of the gas turbine as a prime mover. This paper describes an extensive program carried out by the General Electric Company to demonstrate the ability of both the heavy-duty and aircraft-derivative gas turbines to operate satisfactorily while burning a wide range of lower heating value fuels, typical of industrial process or gas conditioning plants. Analytical predictions of flammability limit changes due to fuel composition variations, and combustion inlet air temperature effects are compared with small scale atmospheric burner tests. Finally, full scale single burner and sector test results are presented which demonstrate the capability of present generation combustion systems to operate on lower heating value fuels.

Paper 9: Combustion Aspects of Industrially Applied Aero Gas Turbines

1968 ◽  
Vol 183 (14) ◽  
pp. 85-97
Author(s):  
G. Pilkington ◽  
D. R. Carlisle
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Ground Level ◽  
Steam Injection ◽  
Combustion Stability ◽  
Combustion System ◽  
Design And Development ◽  
Gaseous Fuels ◽  
Wide Range ◽  
Combustion Technology

This paper concentrates on the combustion experience gained by the application of the Rolls-Royce Avon aero gas turbine to industrial usage and each of the following subjects is considered in detail. A brief summary of the design philosophy which has dictated the configuration of the basic aero combustion equipment. The particular implications of industrial operation as this affects the combustion system. This includes the effect of different fuels and operation for long periods in a ground level environment. The operational problems experienced to date with the basic aero equipment and the design and development work undertaken to overcome them. These problems comprise frettage, flare distortion, smoke output, starting, corrosion and combustion stability. The design and development of an improved system, now under way, which will be capable of satisfactory operation with a wide range of liquid or gaseous fuels without component change. The use of steam injection into the combustion system as a means of improving overall cycle efficiency. Consideration of the range of industrial fuels available, from diluted gases to distillate and residual oils, and their suitability for gas turbine usage. Future trends in combustion technology.

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