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.

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 Status of Joint General Electric-Maritime Administration Heavy Duty Gas Turbine Development Program

1973 ◽  
Author(s):  
S. M. Kaplan ◽  
H. Helfenstein
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
The United States ◽  
Maritime Industry ◽  
Heavy Duty ◽  
General Electric ◽  
The Status ◽  
Development Goals ◽  
Heavy Duty Gas Turbine ◽  
Turbine Design

The United States Maritime Administration and the Gas Turbine Products Division of the General Electric Company have joined in a five-year, cost-sharing program to promote the domestic maritime industry using improved concepts of heavy duty gas turbine design. This paper describes the elements of that program and reports on the progress at its midpoint, two and one-half years following its inception. The status of project development goals and technical attainments to date indicate that the contractual objectives of both parties are being attained.

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.

A New Superalloy Enabling Heavy Duty Gas Turbine Wheels for Improved Combined Cycle Efficiency

2017 ◽  
Author(s):  
Andrew Detor ◽  
◽  
Richard DiDomizio ◽  
Don McAllister ◽  
Erica Sampson ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Combined Cycle ◽  
Heavy Duty ◽  
Heavy Duty Gas Turbine ◽  
Cycle Efficiency

Impact of Different Film-Cooling Modes at Trailing Edge on the Aerodynamic Performance of Heavy Duty Gas Turbine Cascade

2011 ◽  
Vol 84-85 ◽  
pp. 259-263
Author(s):  
Xun Liu ◽  
Song Tao Wang ◽  
Xun Zhou ◽  
Guo Tai Feng
Keyword(s):  
Gas Turbine ◽  
Film Cooling ◽  
Large Mass ◽  
Turbine Cascade ◽  
Heavy Duty ◽  
Trailing Edge ◽  
Central Difference ◽  
Adiabatic Effectiveness ◽  
Heavy Duty Gas Turbine ◽  
The Impact

In this paper, the trailing edge film cooling flow field of a heavy duty gas turbine cascade has been studied by central difference scheme and multi-block grid technique. The research is based on the three-dimensional N-S equation solver. By way of analysis of the temperature field, the distribution of profile pressure, and the distribution of film-cooling adiabatic effectiveness in the region of trailing edge with different cool air injection mass and different angles, it is found that the impact on the film-cooling adiabatic effectiveness is slightly by changing the injection mass. The distribution of profile pressure dropped intensely at the pressure side near the injection holes line with the large mass cooling air. The cooling effect is good in the region of trailing edge while the injection air is along the direction of stream.

scholarly journals Aerodynamic Design and Testing of an Improved 1st Stage Compressor Rotor for a Heavy Duty Gas Turbine

1981 ◽  
Author(s):  
I. Ispas ◽  
H. J. Zollinger
Keyword(s):  
Gas Turbine ◽  
Rotor Blade ◽  
Aerodynamic Design ◽  
Heavy Duty ◽  
High Loss ◽  
Compressor Rotor ◽  
Performance Map ◽  
Computer Codes ◽  
Heavy Duty Gas Turbine ◽  
Design And Testing

To evaluate the potential of the compressor of Sulzer’s Typ 3 gas turbine, a series of engine tests was analyzed with two computer codes. The comparison between measured and calculated performance map are given in the paper. The design goal was to find modifications, which can be applied easily to already operating engines. The simplest option-increase of shaft speed with the existing blades-would have caused high loss due to increased tip Mach number. The calculation revealed, that a newly designed first rotor blade is an appropriate modification to increase massflow and efficiency. No further change is required, because the calculations indicate, that all subsequent stages operate at near optimum incidence. The calculations were confirmed experimentally. The paper presents the new rotor blade and its influence on the compressor calculated and measured performance.

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