Transonic Compressor Development for Large Industrial Gas Turbines

1983 ◽  
Vol 105 (3) ◽  
pp. 417-421 ◽  
Author(s):  
B. Becker ◽  
M. Kwasniewski ◽  
O. von Schwerdtner
Keyword(s):  
Gas Turbine ◽  
Mass Flow ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Industrial Applications ◽  
Transonic Compressor ◽  
Industrial Gas Turbines ◽  
Compressor Map ◽  
Industrial Gas Turbine ◽  
Cycle Efficiency

With increasing mass flow and constant rotational speed of the single shaft gas turbine, the diameters and tip speeds of compressor and turbine blading have to be enlarged. A significant further increase in mass flow can be achieved with transonic compressor stages, as they have been in service in aero gas turbines for many years. For industrial applications, weight and stage pressure ratio are not nearly as important as efficiency. Therefore, different design criteria had to be applied, which led to a moderate front stage pressure ratio of 1.5 with a rotor tip inlet Mach number of 1.37 and a high solidity blading. In order to simulate the first three stages of a 200-MW gas turbine, a test compressor scaled by 1:5.4 was built and tested. These measurements confirmed the aerodynamic performance in the design point very well. The compressor map showed a satisfactory part speed behavior. These results prove that the single-shaft industrial gas turbine still has a high development potential with respect to power increase. Additionally, with the higher pressure ratio, the cycle efficiency will be improved considerably.

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.

The Compact Industrial Gas Turbine Recent Technical Improvements

1978 ◽  
Author(s):  
A. W. T. Mottram
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Aircraft Engine ◽  
Industrial Applications ◽  
Aircraft Engines ◽  
Technical Standard ◽  
Continual Improvement ◽  
Industrial Gas Turbines ◽  
Environmental Requirements ◽  
Industrial Gas Turbine

The industrial gas turbine requires continual improvement in order to increase output and efficiency, to extend its life and to meet fresh environmental requirements. In the compact industrial gas turbine, derived from the aircraft engine, the required improvements are achieved in three ways: (a) new features are incorporated which have been developed to meet the specific requirements of industrial applications, (b) technical improvements developed initially for aircraft engines are applied to existing industrial engines, and (c) new engines developed for aircraft and to a higher technical standard are introduced into industrial service. This paper describes recent improvements to Rolls-Royce compact industrial gas turbines with particular reference to the Olympus C and Olympus 593.

Industrial Gas Turbine Performance Uprates: Tips, Tricks, and Traps

1998 ◽  
Vol 120 (4) ◽  
pp. 727-734 ◽  
Author(s):  
T. L. Ragland
Keyword(s):  
Gas Turbine ◽  
Output Power ◽  
Gas Turbines ◽  
Low Cost ◽  
Pressure Ratio ◽  
Original Design ◽  
Power Cycle ◽  
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, cycle efficiency, or both. Typically, 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.

Evaluation Program for New Industrial Gas Turbine Materials

1978 ◽  
Vol 100 (4) ◽  
pp. 704-710
Author(s):  
Ch. Just ◽  
C. J. Franklin
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Time Cost ◽  
New Materials ◽  
Evaluation Program ◽  
Evaluation Time ◽  
Industrial Gas Turbines ◽  
New Material ◽  
Industrial Gas Turbine ◽  
Phase Evaluation

The need for a thorough and systematic standard evaluation program for new materials for modern industrial gas turbines is shown by several examples and facts. A complete list of the data required by the designer of an industrial gas turbine is given, together with comments to some of the more important properties. A six-phase evaluation program is described which minimizes evaluation time, cost, and the risk of introducing a new material.

scholarly journals Impact of compressed air energy storage demands on gas turbine performance

2020 ◽  
pp. 095765092090627 ◽  
Author(s):  
Uyioghosa Igie ◽  
Marco Abbondanza ◽  
Artur Szymański ◽  
Theoklis Nikolaidis
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Engine Performance ◽  
Compressed Air ◽  
Design Stage ◽  
Simulation Code ◽  
Ratio Distribution ◽  
Stall Margin ◽  
Industrial Gas Turbines

Industrial gas turbines are now required to operate more flexibly as a result of incentives and priorities given to renewable forms of energy. This study considers the extraction of compressed air from the gas turbine; it is implemented to store heat energy at periods of a surplus power supply and the reinjection at peak demand. Using an in-house engine performance simulation code, extractions and injections are investigated for a range of flows and for varied rear stage bleeding locations. Inter-stage bleeding is seen to unload the stage of extraction towards choke, while loading the subsequent stages, pushing them towards stall. Extracting after the last stage is shown to be appropriate for a wider range of flows: up to 15% of the compressor inlet flow. Injecting in this location at high flows pushes the closest stage towards stall. The same effect is observed in all the stages but to a lesser magnitude. Up to 17.5% injection seems allowable before compressor stalls; however, a more conservative estimate is expected with higher fidelity models. The study also shows an increase in performance with a rise in flow injection. Varying the design stage pressure ratio distribution brought about an improvement in the stall margin utilized, only for high extraction.

scholarly journals The Effects of Chemistry Variations in New Nickel-Based Superalloys for Industrial Gas Turbine Applications

2020 ◽  
Vol 51 (9) ◽  
pp. 4902-4921 ◽  
Author(s):  
Sabin Sulzer ◽  
Magnus Hasselqvist ◽  
Hideyuki Murakami ◽  
Paul Bagot ◽  
Michael Moody ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Experimental Characterization ◽  
Multi Scale ◽  
Aerospace Applications ◽  
Scale Modeling ◽  
Industrial Gas Turbines ◽  
Multi Scale Modeling ◽  
Superior Corrosion Resistance ◽  
Industrial Gas Turbine

Abstract Industrial gas turbines (IGT) require novel single-crystal superalloys with demonstrably superior corrosion resistance to those used for aerospace applications and thus higher Cr contents. Multi-scale modeling approaches are aiding in the design of new alloy grades; however, the CALPHAD databases on which these rely remain unproven in this composition regime. A set of trial nickel-based superalloys for IGT blades is investigated, with carefully designed chemistries which isolate the influence of individual additions. Results from an extensive experimental characterization campaign are compared with CALPHAD predictions. Insights gained from this study are used to derive guidelines for optimized gas turbine alloy design and to gauge the reliability of the CALPHAD databases.

Evolution and Future Trend of Large Frame Gas Turbines: A New 1600 Degree C, J Class Gas Turbine

2012 ◽  
Author(s):  
Satoshi Hada ◽  
Masanori Yuri ◽  
Junichiro Masada ◽  
Eisaku Ito ◽  
Keizo Tsukagoshi
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Standard Condition ◽  
Development Program ◽  
Combined Cycle ◽  
Component Technology ◽  
Extensive Experience ◽  
National Project ◽  
Cycle Efficiency

MHI recently developed a 1600°C class J-type gas turbine, utilizing some of the technologies developed in the National Project to promote the development of component technology for the next generation 1700°C class gas turbine. This new frame is expected to achieve higher combined cycle efficiency and will contribute to reduce CO2 emissions. The target combined cycle efficiency of the J type gas turbine will be above 61.5% (gross, ISO standard condition, LHV) and the 1on1 combined cycle output will reach 460MW for 60Hz engine and 670MW for 50Hz engine. This new engine incorporates: 1) A high pressure ratio compressor based on the advanced M501H compressor, which was verified during the M501H development in 1999 and 2001. 2) Steam cooled combustor, which has accumulated extensive experience in the MHI G engine (> 1,356,000 actual operating hours). 3) State-of-art turbine designs developed through the 1700°C gas turbine component technology development program in Japanese National Project for high temperature components. This paper discusses the technical features and the updated status of the J-type gas turbine, especially the operating condition of the J-type gas turbine in the MHI demonstration plant, T-Point. The trial operation of the first M501J gas turbine was started at T-point in February 2011 on schedule, and major milestones of the trial operation have been met. After the trial operation, the first commercial operation has taken place as scheduled under a predominantly Daily-Start-and-Stop (DSS) mode. Afterward, MHI performed the major inspection in October 2011 in order to check the mechanical condition, and confirmed that the hot parts and other parts were in sound condition.

Rig Testing of the Operability of a Transonic Compressor Blade of an Industrial Gas Turbine

2019 ◽  
Author(s):  
Hyunsu Kang ◽  
Sungjong Ahn ◽  
Kyusic Hwang ◽  
Justin Bock ◽  
Jeongseek Kang ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Large Scale ◽  
Load Condition ◽  
Compressor Blade ◽  
Guide Vanes ◽  
Aerodynamic Damping ◽  
Transonic Compressor ◽  
Full Speed ◽  
Industrial Gas Turbine

Abstract This paper describes the flow and vibrations measured in a 1.5-stage transonic research compressor tested at the Notre Dame Turbomachinery Laboratory. The compressor is a sub-scale version of a large-scale industrial gas turbine. The experiment measured the compressor performance and investigated the operability issues of stall and flow-induced blade vibrations due to buffet and flutter. The buffet was investigated at full-speed with fully-closed inlet guide vanes; the full-speed, no-load condition of gas turbines used for power generation. The flutter was investigated at part-speed conditions with partially closed guide vanes; the part-power condition where stall flutter typically occurs for aero-engines. At both of these conditions the blades operate with high incidence and moderate velocity, which can result in flow-induced vibrations. Aero-elastic simulations were performed to predict the flutter boundary. The flutter analysis predicted positive aerodynamic damping near the operating line, and a decrease in aerodynamic damping as the stall boundary was approached. No flutter was observed in the stable operating range of the compressor. The experimental campaign used blade tip timing to measure the vibrations and unsteady pressure transducers above the compressor blade. These two types of data were correlated to better understand the drivers of vibration. The paper describes the behavior of the aerodynamic drivers of buffet and flutter and the resulting vibration.

7H™ Combustion System Performance With Fuel Moisturization

2006 ◽  
Author(s):  
Markus Feigl ◽  
Geoff Myers ◽  
Stephen R. Thomas ◽  
Raub Smith
Keyword(s):  
Gas Turbines ◽  
Combined Cycle ◽  
Combustion System ◽  
Heavy Duty ◽  
Single Digit ◽  
Efficiency Performance ◽  
Industrial Gas Turbines ◽  
Industrial Gas Turbine ◽  
Cycle Efficiency ◽  
Full Pressure

This paper describes the concept and benefits of the fuel moisturization system for the GE H System™ steam-cooled industrial gas turbine. The DLN2.5H combustion system and fuel moisturization system are both described, along with the influence of fuel moisture on combustor performance as measured during full-scale, full-pressure rig testing of the DLN2.5H combustion system. The lean, premixed DLN2.5H combustion system was targeted to deliver single-digit NOx and CO emissions from 40% to 100% combined cycle load in both the Frame 7H (60 Hz) and Frame 9H (50 Hz) heavy-duty industrial gas turbines. These machines are also designed to yield a potential combined-cycle efficiency of 60 percent or higher. Fuel moisturization contributes to the attainment of both the NOx and the combined-cycle efficiency performance goals, as discussed in this paper.

Steam-Cooled Gas Turbine Casings, Struts, and Disks in a Reheat Gas Turbine Combined Cycle: Part I—Compressor and Combustor

1983 ◽  
Vol 105 (4) ◽  
pp. 844-850 ◽  
Author(s):  
I. G. Rice
Keyword(s):  
Steam Turbine ◽  
Gas Turbine ◽  
Gas Turbines ◽  
High Performance ◽  
Material Selection ◽  
Pressure Ratio ◽  
Industrial Applications ◽  
Combined Cycle ◽  
Tip Clearance ◽  
Turbine Output

High-cycle pressure-ratio (38–42) gas turbines being developed for future aircraft and, in turn, industrial applications impose more critical disk and casing cooling and thermal-expansion problems. Additional attention, therefore, is being focused on cooling and the proper selection of materials. Associated blade-tip clearance control of the high-pressure compressor and high-temperature turbine is critical for high performance. This paper relates to the use of extracted steam from a steam turbine as a coolant in a combined cycle to enhance material selection and to control expansion in such a manner that the cooling process increases combined-cycle efficiency, gas turbine output, and steam turbine output.

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