LP compressor blade vibration characteristics at starting conditions of a 100 MW heavy-duty gas turbine

2004 ◽  
Vol 18 (6) ◽  
pp. 895-903 ◽  
Author(s):  
An Sung Lee ◽  
Alexandre F. Vedichtchev
Keyword(s):  
Gas Turbine ◽  
Compressor Blade ◽  
Vibration Characteristics ◽  
Heavy Duty ◽  
Blade Vibration ◽  
Starting Conditions ◽  
Heavy Duty Gas Turbine

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.

Experience With Large Heavy-Duty Gas Turbine Rotors

1981 ◽  
Author(s):  
O. R. Schmoch ◽  
B. Deblon
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Rotor ◽  
Strength Properties ◽  
Operating Conditions ◽  
Material Strength ◽  
Heavy Duty ◽  
Turbine Rotors ◽  
Heavy Duty Gas Turbine ◽  
Response To Temperature

The peripheral speeds of the rotors of large heavy-duty gas turbines have reached levels which place extremely high demands on material strength properties. The particular requirements of gas turbine rotors, as a result of the cycle, operating conditions and the ensuing overall concepts, have led different gas turbine manufacturers to produce special structural designs to resolve these problems. In this connection, a report is given here on a gas turbine rotor consisting of separate discs which are held together by a center bolt and mutually centered by radial serrations in a manner permitting expansion and contraction in response to temperature changges. In particular, the experience gained in the manufacture, operation and servicing are discussed.

scholarly journals Design of a 65,000-Hp Heavy Duty Two-Shaft Gas Turbine

1974 ◽  
Author(s):  
A. J. Orsino ◽  
K. E. Gilbert ◽  
H. Kojima
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Operating Experience ◽  
Commercial Application ◽  
Heavy Duty ◽  
Heavy Duty Gas Turbine ◽  
High Level

This paper describes the design of a 65,000-Hp heavy duty gas turbine for marine service, for land-based mechanical drive applications and for 50 Hz power generation. Operating experience of generically similar units was used to establish the high level of reliability and maintainability incorporated into this unit. This model series gas turbine will be available for commercial application in 1974.

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