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 Test of a New Axial Compressor for the Nuovo Pignone Heavy-Duty Gas Turbines

1997 ◽  
Vol 119 (3) ◽  
pp. 633-639 ◽  
Author(s):  
Erio Benvenuti
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Dynamic Pressure ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Leading Edge ◽  
Heavy Duty ◽  
Pressure Transducers ◽  
Heavy Duty Gas Turbine ◽  
Easy Integration

This axial compressor design was primarily focused to increase the power rating of the current Nuovo Pignone PGT10 Heavy-Duty gas turbine by 10 percent. In addition, the new 11-stage design favorably compares with the existing 17-stage compressor in terms of simplicity and cost. By scaling the flowpath and blade geometry, the new aerodynamic design can be applied to gas turbines with different power ratings as well. The reduction in the stage number was achieved primarily through the meridional flowpath redesign. The resulting higher blade peripheral speeds achieve larger stage pressure ratios without increasing the aerodynamic loadings. Wide chord blades keep the overall length unchanged thus assuring easy integration with other existing components. The compressor performance map was extensively checked over the speed range required for two-shaft gas turbines. The prototype unit was installed on a special PGT10 gas turbine setup, that permitted the control of pressure ratio independently from the turbine matching requirements. The flowpath instrumentation included strain gages, dynamic pressure transducers, and stator vane leading edge aerodynamic probes to determine individual stage characteristics. The general blading vibratory behavior was proved fully satisfactory. With minor adjustments to the variable stator settings, the front stage aerodynamic matching was optimized and the design performance was achieved.

scholarly journals Design and Test of a New Axial Compressor for the Nuovo Pignone Heavy Duty Gas Turbines

1996 ◽  
Author(s):  
Erio Benvenuti
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Dynamic Pressure ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Leading Edge ◽  
Meridional Flow ◽  
Heavy Duty ◽  
Pressure Transducers ◽  
Easy Integration

This axial compressor design was primarily focused to increase the power rating of the current Nuovo Pignone PGT10 Heavy-Duty gas turbine by 10%. In addition, the new 11-stage design favourably compares with the existing 17-stage compressor in terms of simplicity and cost. By seating the flowpath and blade geometry, the new aerodynamic design can be applied to gas turbines with different power ratings as well. The reduction in the stage number was achieved primarily through the meridional flow-path redesign. The resulting higher blade peripheral speeds achieve larger stage pressure ratios without increasing the aerodynamic loadings. Wide chord blades keep the overall length unchanged thus assuring easy integration with other existing components. The compressor performance map was extensively checked over the speed range required for two-shaft gas turbines. The prototype unit was installed on a special PGT10 gas turbine setup, that permitted the control of pressure ratio independently from the turbine matching requirements. The flowpath instrumentation included strain-gages, dynamic pressure transducers and stator vane leading edge aerodynamic probes to determine individual stage characteristics. The general blading vibratory behavior was proved fully satisfactory. With minor adjustments to the variable stator settings the front stage aerodynamic matching was optimized and the design performance was achieved.

Performance and Numerical Flow Investigations of an Industrial Gas Turbine Intake System Under Different Operating Conditions

2006 ◽  
Author(s):  
Friederike C. Mund ◽  
Pericles Pilidis
Keyword(s):  
Gas Turbine ◽  
Operating Conditions ◽  
Relative Reduction ◽  
Maximum Deviation ◽  
Heavy Duty ◽  
Flow Distortion ◽  
Local Flow ◽  
Intake System ◽  
Heavy Duty Gas Turbine ◽  
Industrial Gas Turbine

An important loss in an industrial gas turbine is caused by the intake system. Even though these losses have a direct effect on the performance of the engine, the design of the intake system is dominated by local space restriction. Consequently, intake losses are site specific parameters. They correlate with the airflow velocity and therefore operating conditions of the engine affect the intake performance. But due to the high experimental effort necessary to investigate intake losses, only sparse information about this effect is available. For the present study a typical vertical industrial intake duct was investigated numerically for different operating scenarios. The performance simulation of a single shaft heavy duty gas turbine provided boundary conditions for the CFD (Computational Fluid Dynamics) study of the intake duct. For all operating conditions a large scale vortex developed in the intake plenum and entered the compressor. Bearing support struts caused local flow distortion at the compressor inlet. Even for extreme operating scenarios the relative changes of pressure recovery compared to the design point value were small (0.1%). However, the resulting power change was generally in excess of the intake loss deviation. Applied to a heavy duty gas turbine, the maximum deviation of 0.2% of power was equivalent to about 0.4 MW. In most cases lower pressure losses were predicted which benefited the overall engine performance. For the cold scenario the intake performance deteriorated and resulted in a relative reduction of power of nearly 0.5 MW.

The Evolution of Compressor and Turbine Bladings in Gas Turbine Design

1967 ◽  
Vol 89 (2) ◽  
pp. 199-205 ◽  
Author(s):  
C. Seippel
Keyword(s):  
Steam Turbine ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Parallel Evolution ◽  
Axial Compressor ◽  
Expansion Turbine ◽  
The Stability ◽  
Turbine Design ◽  
The City

The author, having been associated with the construction of gas turbines from the first 4000-kw unit delivered in 1939 to the city of Neuchaˆtel to the present time, gives some personal views on the evolution of the axial compressor and turbine bladings which are the key elements to the gas turbines. The axial compressor was created to supply air efficiently for the supercharged “Velox” boiler. It made the evolution to the modern gas turbine possible. The main problems encountered were related to the stability of flow. An enormous increase of volume capacity was achieved in the course of time. The increase of pressure ratio made special measures necessary to overcome instability at starting. The expansion turbine started on the basis of steam turbine practice and underwent a parallel evolution to large capacities. Its particular problems are related to the high temperatures of the gases.

The Design and Development of an Advanced Heavy-Duty Gas Turbine

1988 ◽  
Vol 110 (2) ◽  
pp. 243-250 ◽  
Author(s):  
D. E. Brandt
Keyword(s):  
Gas Turbine ◽  
Comprehensive Treatment ◽  
Heavy Duty ◽  
Operating Characteristics ◽  
Component Design ◽  
Technological Advances ◽  
Heavy Duty Gas Turbine ◽  
And Performance ◽  
Factory Testing ◽  
Turbine Design

Significant advances in all elements of gas turbine design technologies have occurred during the past decade. These developments have created a technical climate conducive to the creation of a totally new heavy-duty gas turbine, as opposed to the uprating of an existing design. This paper discusses the features and characteristics of a new heavy-duty gas turbine that takes advantage of the latest technological advances. Discussed are the basis for design parameter selection, the operating characteristics, the materials of construction, and the component design features. Also presented are the features and performance of the unique combustion system and the results of and plans for component and prototype testing. This paper represents a comprehensive treatment of this advanced gas turbine, which is in the initial manufacturing stage in preparation for extensive factory testing followed by shipment to a customer by mid-1988.

scholarly journals The Evolution of a Reliable Gas Turbine

1982 ◽  
Author(s):  
D. E. Brandt ◽  
E. J. Walsh ◽  
R. G. Kunkel
Keyword(s):  
Gas Turbine ◽  
Cost Effective ◽  
Heavy Duty ◽  
Field Validation ◽  
Heavy Duty Gas Turbine ◽  
Design Deficiencies ◽  
Turbine Design

This paper presents the evolution of a reliable and cost effective heavy duty gas turbine. Its pedigree is discussed, including the correction of deficiencies in an earlier turbine design. Specific topics addressed include the correction of field developed design deficiencies in the earlier turbine, the prototype and field validation of these earlier turbine deficiencies and the prototype and field validation of the new turbine which was scaled from the earlier design.

SANS-study of the nano-defects in a NiCrMoV wheel of the axial compressor of a heavy duty gas turbine

2005 ◽  
Vol 26 (3) ◽  
pp. 191-195 ◽  
Author(s):  
M. Rogante ◽  
G.F. Ceschini ◽  
L. Tognarelli ◽  
E. Rétfalvi ◽  
V.T. Lebedev
Keyword(s):  
Gas Turbine ◽  
Axial Compressor ◽  
Heavy Duty ◽  
Heavy Duty Gas Turbine

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 Non-Metallic Brush Seal in Heavy Duty GT Units, GE-Made Frame No. 7, Model EA

2007 ◽  
Author(s):  
Steve Ingistov
Keyword(s):  
Gas Turbine ◽  
Axial Compressor ◽  
Operational Experience ◽  
Heavy Duty ◽  
The Core ◽  
Air Temperatures ◽  
Brush Seal ◽  
Brush Seals ◽  
Bearing Number ◽  
Industrial Gas Turbine

This Paper describes design, fabrication, installation and operational experience with non-metallic brush seals installed in all four GT Units, GE-made, Frame No 7, Model EA, presently operating at Watson Cogeneration Company, Carson, California, USA. First non-metallic brush seal was installed early 2002 and is currently in operation. Non-metallic brush seal serves in particular application to reduce the leakage of lubrication oil into the axial compressor suction. At the time of installation, it was the first application[1], to author’s knowledge, where the non-metallic bristle brush seal was used in heavy duty industrial gas turbine. Non-metallic brush seal can be successfully used where the local temperatures and pressures allow their safe usage. Compressor bearing number one is close to its suction where the air temperatures are low enough to enable the usage of non-metallic bristles which in turn are the core of the brush seals.

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