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.

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 Developments Leading to an Axial Flow Compressor for a 25 MW Class High Efficiency Gas Turbine

1990 ◽  
Author(s):  
Y. Kashiwabara ◽  
Y. Katoh ◽  
H. Ishii ◽  
T. Hattori ◽  
Y. Matsuura ◽  
...  
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Mechanical Design ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Rotating Stall ◽  
Design Parameters ◽  
Axial Flow Compressor ◽  
Heavy Duty Gas Turbine ◽  
Flow Compressor

In this paper, the development leading to a 17-stage axial flow compressor (pressure ratio 14.7) for the 25 MW class heavy duty gas turbine H-25 is described. In the course of developing the H-25’s compressor, extensive measurements were carried out on models. Experimental results are compared with predicted values. Aerodynamic experiments covered the measurements of unsteady flows such as rotating stall and surge as well as the steady-state performance of the compressor. Based on the results of these tests, the aerodynamic and mechanical design parameters of the full scale H-25 compressor were finalized on the basis of two model compressors. Detailed measurements of the first unit of the H-25 gas turbine were carried out. Test results on the compressor are presented and show the achievement of the expected design targets.

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

1982 ◽  
Vol 104 (4) ◽  
pp. 823-831 ◽  
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

The paper describes the design and development of a 15 stage axial flow compressor for a 6-MW 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.

Design of the 6C Heavy-Duty Gas Turbine

2003 ◽  
Author(s):  
David Harper ◽  
Devin Martin ◽  
Harold Miller ◽  
Robert Grimley ◽  
Fre´de´ric Greiner
Keyword(s):  
Power Systems ◽  
Gas Turbine ◽  
High Efficiency ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Load Test ◽  
Advanced Technology ◽  
General Electric ◽  
Three Stages ◽  
Flow Compressor

The MS6001C gas turbine combines the proven reliability of the General Electric gas turbine family with the advanced technology developed for the FA, FB and H machine designs. The engine configuration is a single shaft bolted rotor, driving a 50 or 60 Hz. generator though a cold end mounted load gear. Rated at 42.3 MW, with a thermal efficiency of 36.3%, the MS6001C will provide greater than a four percent increase in efficiency over the MS6001B. This paper is focused on the design and development of the MS6001C gas turbine, highlighting the commonality between this and other General Electric Power Systems (GEPS) and General Electric Aircraft Engines (GEAE) designs, as well as introducing some new and innovative features. The new high efficiency, 12 stage, axial flow compressor, features a 19:1 pressure ratio with three stages of variable guide vanes. The can annular, six chamber, Dry Low NOx (DLN-2.5H) combustion system is scaled from field proven, low emission technology. The turbine incorporates three stages, two cooled blade rows, and operates at a 1327°C firing temperature. After a thorough factory full speed no load test has been conducted, the first MS6001C engine will be shipped to a customer site in Kemalpasalzmir Turkey, where an instrumented full load test will be conducted to validate the design.

MAN’s New Gas Turbines for Mechanical Drive and Power Generation Applications

2013 ◽  
Author(s):  
Emil Aschenbruck ◽  
Michele Cagna ◽  
Volker Langusch ◽  
Ulrich Orth ◽  
Andreas Spiegel ◽  
...  
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Gas Turbines ◽  
High Efficiency ◽  
Pressure Ratio ◽  
High Heat ◽  
Product Line ◽  
Pollutant Emission ◽  
Two Stage ◽  
Exhaust Temperature

MAN Diesel & Turbo recently developed a completely new gas turbine family for the first time in its history. The first product line contains both two-shaft and single-shaft gas turbines in the 6 – 7 MW class. The two-shaft engine was thoroughly tested at MAN’s gas turbine test center, and the first engine has been delivered to a launch customer. For MAN, it constitutes a technology platform that will produce further developments and new models in the coming years. The two-shaft design makes the new gas turbine an ideal mechanical drive for both turbo compressors and pumps. This gas turbine operates to suit the optimum duty point of the driven machine; both in a wide speed and power range. The two stage power turbine design allows for a wide speed range of 45 to 105% while maintaining high efficiency. For power generation a single-shaft version has been created by adding one additional stage to the two stage high pressure turbine. The compressor pressure ratio is 15, which is high enough for achieving the highest potential efficiency for both generator and compressor drive applications. Low pollutant emission levels are achieved with MAN’s DLN combustion technology. The gas turbine exhaust temperature is sufficiently high to reach high heat recovery rates in combined heat and power cycles. Another important feature of the new gas turbine is its unrestricted suitability for taking load quickly and rapid load changes. Service costs have also been significantly improved upon. MAN opted for a sturdy and modular gas turbine construction, while not compromising on efficiency. The objective is to extend service life and shorten down time occurrences. The modular package assembly process helps to reduce routine maintenance and repair time, and ultimately package downtime.

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 The Development of a Multi-Stage Compressor for Heavy Duty Industrial Gas Turbines

1995 ◽  
Author(s):  
T. Meindl ◽  
F. Farkas ◽  
W. Klussmann
Keyword(s):  
Gas Turbines ◽  
High Efficiency ◽  
Pressure Ratio ◽  
Combined Cycle ◽  
Design Data ◽  
High Pressure Ratio ◽  
Multi Stage ◽  
Industrial Gas Turbines ◽  
Industrial Gas Turbine ◽  
Market Requirement

ABB has developed a new type of industrial gas turbine, the GT24 and GT26, in order to meet the increasing market requirement for a high efficiency in both simple cycle and combined cycle modes. The new engines are characterized by an increased pressure-ratio, a sequential combustion system and top component efficiencies. One of the most demanding tasks has been the development of the new high pressure ratio compressor, designed with controlled diffusion airfoils and 3 variable vane rows. In order to verify the aerodynamic design and the mechanical integrity, the first 15 stages of the compressor have been modeled and tested in an extensively instrumented rig. Both the aerodynamic behavior and the blade stresses have been measured during start-up, off-design, and nominal-speed operation, mapping the entire compressor performance field. The experimental results agree well with the predicted design data.

Design and Development of a 14-Stage Axial Compressor for Industrial Gas Turbine

2012 ◽  
Author(s):  
Takuya Ikeguchi ◽  
Akinori Matsuoka ◽  
Yusuke Sakai ◽  
Yoshinobu Sakano ◽  
Kenichiro Yoshiura
Keyword(s):  
Gas Turbine ◽  
Structural Reliability ◽  
Scale Effects ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Geometric Optimization ◽  
Cfd Analysis ◽  
Aerodynamic Design ◽  
Stall Margin ◽  
Industrial Gas Turbine

A 14-stage axial flow compressor was newly designed and tested for developing an advanced industrial gas turbine. In order to achieve a high thermal efficiency required for the new gas turbine, the compressor needed to have a significantly higher pressure ratio and higher efficiency than those of existing engines. The new design methodology used to this compressor design was based on an automated airfoil geometric optimization system combined with a 3D-CFD analysis, which resulted in arbitrary shaped airfoil design in most blade rows. A multi-stage CFD analysis was used effectively in order to adjust a loading distribution along stages and to obtain a proper stage matching. Before the full development of the gas turbine, an approximately two-thirds scaled compressor rig tests were conducted to verify the aerodynamic design and the structural reliability. The test results of the first build indicated a satisfactory level of efficiency and mass flow, but with a lack of sufficient stall margin. The second build with the re-staggered vanes was tested and its result showed improvements both in stall margin and in efficiency. The prototype test of developing an industrial gas turbine also had been conducted. The measured performance of the compressor which was scaled up from the second build rig compressor achieved the design target. Consequently, the aerodynamic design which considered the scale effects of the compressor was successful.

Development of a High-Pressure-Ratio Axial Flow Compressor for a Medium-Size Gas Turbine

1986 ◽  
Vol 108 (2) ◽  
pp. 233-239 ◽  
Author(s):  
Y. Kashiwabara ◽  
Y. Matsuura ◽  
Y. Katoh ◽  
N. Hagiwara ◽  
T. Hattori ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Mechanical Design ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Axial Flow ◽  
Medium Size ◽  
High Pressure Ratio ◽  
Compressor Pressure Ratio ◽  
Predicted Values ◽  
Flow Compressor

In this paper, the development of a model 17-stage axial compressor (pressure ratio 14.7) for a medium-size gas turbine is described. The aerodynamic and mechanical design features of the compressor are presented. In advance of the full 17-stage test, the first three and nine stages were tested. Measured results confirm the design performance in the first stages of the 17-stage compressor. The details of the construction of the facilities, instrumentation and data acquisition system for the full 17-stage test are described. Test results for the 17-stage compressor are presented. The measured results are in good agreement with the predicted values.

A new correlation for estimating the gas turbine cost

2021 ◽  
pp. 095765092199438
Author(s):  
Dominique Adolfo ◽  
Carlo Carcasci ◽  
Beniamino Pacifici
Keyword(s):  
Power Plant ◽  
Gas Turbine ◽  
New Technology ◽  
Pressure Ratio ◽  
Combined Cycle ◽  
Thermodynamic Efficiency ◽  
Energy Investment ◽  
Exhaust Temperature ◽  
New Correlation ◽  
Cost Of Energy

The recent changes in energy scenario with rising attention to decarbonization, introduction of new technology and renewable source have led to design power plant with the lowest values of cost of energy, investment payback period, CO2 emission, especially in cogeneration and combined cycle plants. The cost of a gas turbine, an industrial key intellectual property value, represents a large portion of total plant capital cost. In fact, the correlations used to determine this cost, represent an important part in the optimization of power plant studied. In this work, a new cost correlation has been determined using gas turbine data presents into GTW handbook. The overall correlation, dependently only on gas turbine output power, used in a lot of scientific studies is here actualized, calculating new split-power and new coefficients for Heavy Duty and Aeroderivative gas turbine. Therefore, a more complete and detailed correlation is developed, introducing additional parameters, such as thermodynamic efficiency, pressure ratio, exhaust temperature and exhaust mass flow rate, whose values are available on gas turbine datasheet. The new correlation here proposed reflects better real gas turbine configurations and costs.

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