scholarly journals Design and Development of the PGT 10 Heavy-Duty Advanced Gas Turbine

1985 ◽  
Author(s):  
E. Benvenuti ◽  
R. Gusso
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Laboratory Model ◽  
Heavy Duty ◽  
Cooling Flows ◽  
High Pressure Ratio ◽  
Blade Cooling ◽  
Power Turbine ◽  
High Flexibility ◽  
Industrial Gas Turbine

The PGT 10, a heavy-duty two shaft industrial gas turbine in the 10,000 to 14,000 HP (7,500 to 10,500 kW) nominal power range has been designed; the prototype unit is in construction, with testing scheduled in 1986. The main distinctive design features are a high pressure ratio and the capability of regenerative cycle operation, coupled with an uncommon combination of adjustable compressor stator vanes and power turbine nozzles, providing very high flexibility in control of cycle parameters. In association with state of art firing temperatures, simple cycle thermal efficiencies up to 34% can be anticipated, while a 36% efficiency level over the whole power range is possible with coupling to a regenerator. Reliability and long life of hot parts were pursued through extensive reference to successful heavy-duty turbine experience and careful trade-off between aerodynamic design and implementation of nozzle and blade cooling devices; extensive laboratory model tests have been performed to properly check and calibrate hot part cooling flows and distributions prior to full prototype testing.

scholarly journals Optimum Power Boosting of Gas Turbine Cycles With Refrigerated Inlet Air and Compressor Intercooling

1996 ◽  
Author(s):  
Mohand A. Ait-Ali
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Inlet Temperature ◽  
Turbine Blade Cooling ◽  
High Pressure Ratio ◽  
Blade Cooling ◽  
Air Inlet ◽  
Turbine Inlet ◽  
Compressor Work

With or without turbine blade cooling, gas turbine cycles have consistently higher turbine inlet temperatures than steam turbine cycles. But this advantage is more than offset by the excessive compressor work induced by warm inlet temperatures, particularly during operation on hot summer days. Instead of seeking still higher turbine inlet temperatures by means of sophisticated blade cooling technology and high temperature-resistant blade materials, it is proposed to greatly increase the cycle net work and also improve thermal efficiency by decreasing the compressor work. This is obtained by using refrigerated inlet air and compressor intercooling to an extent which optimizes the refrigerated air inlet temperature and consequently the gas turbine compression ratio with respect to maximum specific net power. The cost effectiveness of this conceptual cycle, which also includes regeneration, has not been examined in this paper as it requires unusually high pressure ratio gas turbines and compressors, as well as high volumetric air flow rate and low temperature refrigeration equipment for which reliable cost data is not easily available.

A New 1.7MW Industrial Gas Turbine: The Ruston Hurricane

1991 ◽  
Author(s):  
A. T. Sanders ◽  
M. H. Tothill ◽  
G. R. Wood
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Thermodynamic Efficiency ◽  
The Novel ◽  
Exhaust Temperature ◽  
High Pressure Ratio ◽  
Industrial Gas Turbine ◽  
Novel Design

The paper describes the design of a compact new 1.7MW (2300hp) single shaft industrial gas turbine and package, with high efficiency and exhaust temperature ideal for industrial congeneration applications. These advantages are obtained with a high pressure ratio single stage centrifugal compressor, single high temperature combustor and two-stage axial flow turbine using only one row of cooled blades. The novel design features are described with the associated development testing. A typical installation is also described showing the potential for very high overall thermodynamic efficiency.

scholarly journals The PGT 10 Heavy Duty 10 MW Gas Turbine

1988 ◽  
Author(s):  
R. Gusso ◽  
E. Benvenuti ◽  
D. Bianchi ◽  
D. Sabella
Keyword(s):  
Gas Turbine ◽  
High Reliability ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Load Testing ◽  
Heavy Duty ◽  
Heavy Duty Gas Turbine ◽  
Performance Results ◽  
Turbine Design ◽  
Industrial Gas Turbine

The PGT 10 two-shaft, 10 MW, industrial gas turbine has a capability of up to 34% simple-cycle efficiency, high reliability with extended range of operation and low exhaust emissions. Features like the 14:1 pressure ratio and high specific mass flow transonic axial compressor are at the highest levels in the heavy-duty gas turbine design. The firing temperature, the blade cooling techniques, the extended modularization of components and subassemblies are in their turn representative of the well-proven, state-of-art technology: performance results also from the aero-thermodynamic design aimed at maximizing component efficiencies. This paper introduces the major aspects of the PTG 10 turbine design. After full-load testing was successfully completed on the first units, the PTG 10 has entered normal production in 1987 and several units have already been installed or shipped.

Design and Development of a 12:1 Pressure Ratio Compressor for the Ruston 6-MW Gas Turbine

1982 ◽  
Author(s):  
F. Carchedi ◽  
G. R. Wood
Keyword(s):  
Gas Turbine ◽  
Test Data ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Aerodynamic Design ◽  
Design And Development ◽  
Surge Line ◽  
Flow Compressor ◽  
Industrial Gas Turbine ◽  
Spanwise Flow

This paper describes the design and development of a 15-stage axial flow compressor for a −6MW industrial gas turbine. Detailed aspects of the aerodynamic design are presented together with rig test data for the complete characteristic including stage data. Predictions of spanwise flow distributions are compared with measured values for the front stages of the compressor. Variable stagger stator blading is used to control the position of the low speed surge line and the effects of the stagger changes are discussed.

scholarly journals The Design and Evaluation of a 14 Stage, 16:1 Pressure Ratio Compressor for an Industrial Gas Turbine

1996 ◽  
Author(s):  
Mohammad R. Saadatmand
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Rotor Blade ◽  
Pressure Ratio ◽  
Three Dimensional ◽  
Operating Conditions ◽  
Suction Surface ◽  
Design Intent ◽  
Flow Through ◽  
Industrial Gas Turbine

The aerodynamic design process leading to the production configuration of a 14 stage, 16:1 pressure ratio compressor for the Taurus 70 gas turbine is described. The performance of the compressor is measured and compared to the design intent. Overall compressor performance at the design condition was found to be close to design intent. Flow profiles measured by vane mounted instrumentation are presented and discussed. The flow through the first rotor blade has been modeled at different operating conditions using the Dawes (1987) three-dimensional viscous code and the results are compared to the experimental data. The CFD prediction agreed well with the experimental data across the blade span, including the pile up of the boundary layer on the corner of the hub and the suction surface. The rotor blade was also analyzed with different grid refinement and the results were compared with the test data.

scholarly journals Industrial Gas Turbine Uprates: Tips, Tricks and Traps

1997 ◽  
Author(s):  
T. L. Ragland
Keyword(s):  
Gas Turbine ◽  
Output Power ◽  
Gas Turbines ◽  
Customer Value ◽  
Low Cost ◽  
Pressure Ratio ◽  
Original Design ◽  
Advantages And Disadvantages ◽  
Industrial Gas Turbine ◽  
Cycle Efficiency

After industrial gas turbines have been in production for some amount of time, there is often an opportunity to improve or “uprate” the engine’s output power or cycle efficiency or both. In most cases, the manufacturer would like to provide these uprates without compromising the proven reliability and durability of the product. Further, the manufacturer would like the development of this “Uprate” to be low cost, low risk and result in an improvement in “customer value” over that of the original design. This paper describes several options available for enhancing the performance of an existing industrial gas turbine engine and discusses the implications for each option. Advantages and disadvantages of each option are given along with considerations that should be taken into account in selecting one option over another. Specific options discussed include dimensional scaling, improving component efficiencies, increasing massflow, compressor zero staging, increasing firing temperature (thermal uprate), adding a recuperator, increasing cycle pressure ratio, and converting to a single shaft design. The implications on output power, cycle efficiency, off-design performance engine life or time between overhaul (TBO), engine cost, development time and cost, auxiliary requirements and product support issues are discussed. Several examples are provided where these options have been successfully implemented in industrial gas turbine engines.

Quick Start of an Industrial Gas Turbine Engine Through the Development of “Silent Start” VGV Schedule

2020 ◽  
Author(s):  
Senthil Krishnababu ◽  
Vili Panov ◽  
Simon Jackson ◽  
Andrew Dawson
Keyword(s):  
Guide Vane ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Rotating Stall ◽  
Rotor Blades ◽  
Start Time ◽  
Turbine Engine ◽  
High Pressure Ratio ◽  
Compressor Map ◽  
Industrial Gas Turbine

Abstract In this paper, research that was carried out to optimise an initial variable guide vane schedule of a high-pressure ratio, multistage axial compressor is reported. The research was carried out on an extensively instrumented scaled compressor rig. The compressor rig tests carried out employing the initial schedule identified regions in the low speed area of the compressor map that developed rotating stall. Rotating stall regions that caused undesirable non-synchronous vibration of rotor blades were identified. The variable guide vane schedule optimisation carried out balancing the aerodynamic, aero-mechanical and blade dynamic characteristics gave the ‘Silent Start’ variable guide vane schedule, that prevented the development of rotating stall in the start regime and removed the non-synchronous vibration. Aerodynamic performance and aero-mechanical characteristics of the compressor when operated with the initial schedule and the optimised ‘Silent Start’ schedule are compared. The compressor with the ‘Silent Start’ variable guide vane schedule when used on a twin shaft engine reduced the start time to minimum load by a factor of four and significantly improved the operability of the engine compared to when the initial schedule was used.

Design Study of an Advanced Concept Simple Gas Turbine for Possible Use in Low Emission Automobiles

1972 ◽  
Author(s):  
H. C. Eatock ◽  
M. D. Stoten
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Simple Cycle ◽  
Turbine Engines ◽  
Nox Emissions ◽  
Preliminary Design ◽  
Gas Turbine Engines ◽  
High Pressure Ratio

United Aircraft Corporation studied the potential costs of various possible gas turbine engines which might be used to reduce automobile exhaust emissions. As part of that study, United Aircraft of Canada undertook the preliminary design and performance analysis of high-pressure-ratio nonregenerated (simple cycle) gas turbine engines. For the first time, high levels of single-stage component efficiency are available extending from a pressure ratio less than 4 up to 10 or 12 to 1. As a result, the study showed that the simple-cycle engine may provide satisfactory running costs with significantly lower manufacturing costs and NOx emissions than a regenerated engine. In this paper some features of the preliminary design of both single-shaft and a free power turbine version of this engine are examined. The major component technology assumptions, in particular the high pressure ratio centrifugal compressor, employed for performance extrapolation are explained and compared with current technology. The potential low NOx emissions of the simple-cycle gas turbine compared to regenerative or recuperative gas turbines is discussed. Finally, some of the problems which might be encountered in using this totally different power plant for the conventional automobile are identified.

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