Mechanical Reliability Considerations in the Modern High Temperature Industrial Gas Turbine

1980 ◽  
Vol 102 (2) ◽  
pp. 277-282
Author(s):  
J. J. Korta
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Mechanical Design ◽  
Mechanical Reliability ◽  
Service Experience ◽  
Design Considerations ◽  
Industrial Gas Turbine ◽  
High Degree

The mechanical design considerations of the CW352 two shaft industrial type gas turbine are discussed with emphasis on achieving a high degree of mechanical reliability based on the extensive service experience of the company’s mature 1450°F inlet machines. Problem areas of the early units are discussed and how avoidance of problems has been considered in the design of the CW352.

Mechanical Reliability Operational Experience in the Modern High Temperature Industrial Gas Turbine

1986 ◽  
Author(s):  
J. Korta
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Simple Cycle ◽  
Operational Experience ◽  
Mechanical Reliability ◽  
Industrial Gas Turbine ◽  
Regenerative Cycle

The CW352 two shaft industrial type gas turbine was first put in commercial service in 1979. By mid 1985 units in simple cycle and regenerative modes have accumulated in excess of 200,000 hrs. of operation, with lead units in excess of 50,000 hrs. simple cycle mode and 35,000 hrs. in regenerative cycle mode. The paper discusses the operational experience with emphasis on early field problems and their solutions.

Development, Fabrication, and Testing of a Prototype Water-Cooled Gas Turbine Nozzle

1983 ◽  
Vol 105 (1) ◽  
pp. 114-119 ◽  
Author(s):  
M. F. Collins ◽  
M. C. Muth ◽  
W. F. Schilling
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Small Scale ◽  
General Electric ◽  
Process Technology ◽  
Aqueous Corrosion ◽  
Post Test ◽  
Efficient Heat Transfer ◽  
Gas Turbine Nozzle ◽  
Industrial Gas Turbine

The design and development of a water-cooled high temperature gas turbine has been under active investigation by the General Electric Gas Turbine Division for the past 15 years. The transition from testing small scale, laboratory-size experimental hardware to full scale industrial gas turbine components was initiated in 1975 by General Electric and extended further under the U.S. Department of Energy’s High Temperature Turbine Technology (HTTT) program. A key element in this transition was the identification of a composite (hybrid) design for the first stage nozzles. This design permits efficient heat transfer to the water-cooling passageways, thus lowering effective strains and increasing part life. This paper describes the metallurgical considerations and process technology required for such hardware. A review of the materials selection criteria utilized for the nozzle is presented, along with the results of several materials development programs aimed at determining metallurgical compatibility of the component materials, diffusion bonding behavior and both hot corrosion and aqueous corrosion performance of key materials. A brief description of the actual cascade testing of the part is given, along with results of a post-test metallurgical analysis of the tested hardware.

scholarly journals Generalized High Speed Simulation of Gas Turbine Engines

1990 ◽  
Author(s):  
Nanahisa Sugiyama
Keyword(s):  
Real Time ◽  
Gas Turbine ◽  
Gas Turbines ◽  
High Speed ◽  
Power Plants ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Jet Engines ◽  
Industrial Gas Turbine ◽  
High Degree

This paper describes a real-time or faster-than-real-time simulation of gas turbine engines, using an ultra high speed, multi-processor digital computer, designated the AD100. It is shown that the frame time is reduced significantly without any loss of fidelity of a simulation. The simulation program is aimed at a high degree of flexibility to allow changes in engine configuration. This makes it possible to simulate various types of gas turbine engines, including jet engines, gas turbines for vehicles and power plants, in real-time. Some simulation results for an intercooled-reheat type industrial gas turbine are shown.

Computational and Experimental Analysis of an Industrial Gas Turbine Compressor

2011 ◽  
Author(s):  
Alexander Wiedermann ◽  
Dirk Frank ◽  
Ulrich Orth ◽  
Markus Beukenberg
Keyword(s):  
Gas Turbine ◽  
Mechanical Design ◽  
Phase 1 ◽  
Tip Clearance ◽  
Vibration Modes ◽  
Blade Vibration ◽  
Flow Solver ◽  
Pressure Profiles ◽  
Wide Range ◽  
Industrial Gas Turbine

Test rig results and their comparison with computational analyses of a highly-loaded 11-stage compressor for a newly developed industrial gas turbine will be presented in this paper. The scope of the tests has been validation of aerodynamic and mechanical features of the bladed flow path to meet both the demands for single- and dual-shaft operation of the gas turbine. The test was carried out in three phases using extensive instrumentation. In phase 1 the front stages have been tested, and in phase 2 the test of the full 11-stage compressor was performed including numerous aerodynamic and structural check-outs. Vane and blade vibration modes were measured in all rows with numerous strain gauges using a telemetry system and Tip Timing, which additionally was applied to the front stage rotors. Concerning the mechanical design, finite element predictions of the vibration modes of all blades and vanes were carried out in the design phase to guarantee safe and resonance-free operation for a wide range of operational speeds which could be verified by the test data up to higher modes. Flow field computations were carried out with both a through flow solver and full 3-D viscous multistage solver based on Denton’s TBLOCK, where all rotor and stator flow fields had been solved simultaneously and compared with experiments. The effects of tip clearance and stator cavities on compressor performance have been taken into account by the computational analysis. Effects of inlet distortion were examined in phase 3. Comprehensive comparisons of computed and measured results will be presented. The extensive instrumentation gave also insight into flow details as vane pressure distributions and total pressure profiles in span wise direction. It will be shown that the agreements of predicted and measured data were excellent.

Development and F-Class Industrial Gas Turbine Engine Testing of Smart Components With Direct-Write Embedded Sensors and High Temperature Wireless Telemetry

2008 ◽  
Author(s):  
David Mitchell ◽  
Anand Kulkarni ◽  
Edward Roesch ◽  
Ramesh Subramanian ◽  
Andrew Burns ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Condition Based Maintenance ◽  
Direct Write ◽  
Turbine Engine ◽  
Wireless Telemetry ◽  
Industrial Gas Turbines ◽  
Engine Testing ◽  
Industrial Gas Turbine

The potential for savings provided to worldwide operators of industrial gas turbines, by transitioning from the current standard of interval-based maintenance to condition-based maintenance may be in the tens of millions of dollars per year. Knowledge of the historical and current condition of life-limiting components will enable more efficient use of industrial gas turbine resources via increased operational flexibility, with less risk of unplanned outages as a result of off-parameter operations. To date, it has been impossible to apply true condition-based maintenance to industrial gas turbines because the extremely harsh operating conditions in the heart of a gas turbine preclude using the necessary advanced sensor systems to monitor the machine’s condition continuously. The U.S. Department of Commerce’s National Institute of Standards and Technology – Advanced Technology Program (NIST-ATP) awarded the Joint Venture team of Siemens Power Generation, Inc. and MesoScribe Technologies, Inc. a four-year, $5.4 million program in November, 2004, titled Conformal, Direct-Write-Technology-Enabled, Wireless, Smart Turbine Components. The target was to develop a potentially industry-changing technology to build smart, self-aware engine components that incorporate embedded, harsh-environment-capable sensors and high temperature capable wireless telemetry systems for continuously monitoring component condition in both the compressor and turbine sections. The approach involves several difficult engineering challenges, including the need to embed sensors on complex shapes, such as turbine blades, embedding wireless telemetry systems in regions with temperatures that preclude the use of conventional silicon-based electronics, protecting both sensors and wireless devices from the extreme temperatures and environments of an operating gas turbine, and successfully transmitting the sensor information from an environment very hostile to wireless signals. The program included full-scale, F-class industrial gas turbine engine test demonstrations with smart components in both the compressor and turbine sections. The results of the development program and engine testing to date will be discussed.

Mechanical Design of Turbine Blades With Interlocking Tip Shrouds

2001 ◽  
Author(s):  
David F. Toler
Keyword(s):  
Gas Turbine ◽  
Systematic Approach ◽  
Mechanical Design ◽  
Turbine Blades ◽  
Aerodynamic Design ◽  
Substantial Body ◽  
Virtual Absence ◽  
And Performance ◽  
Industrial Gas Turbine

Abstract In contrast to the substantial body of literature regarding turbine aerodynamics and performance, there is a virtual absence of literature on the mechanical design of turbine components. As a contribution to this discipline, this paper is intended to provide an overview of a systematic approach for the mechanical design of turbine blades with interlocking tip shrouds which will result in a near-optimum mechanical and aerodynamic design for an industrial gas turbine.

Plate Fin Regenerators for Industrial Gas Turbines

1978 ◽  
Vol 100 (4) ◽  
pp. 576-585 ◽  
Author(s):  
K. W. Cuffe ◽  
P. K. Beatenbough ◽  
M. J. Daskavitz ◽  
R. J. Flower
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Gas Turbines ◽  
The Past ◽  
Mode Of Operation ◽  
Industrial Gas Turbines ◽  
Industrial Gas Turbine ◽  
High Temperature Operation ◽  
Surface Changes

This paper reviews Harrison Radiator’s various designs and improvements in the Industrial Gas Turbine Regenerator that it has been supplying over the past 20 years, and describes a new design regenerator intended for high cyclic and/or high temperature operation. Design improvements and surface changes have occurred to keep pace with the changing consumer’s requirements and application. These changes have been effective in improving the cyclic ability of the regenerator and in reducing the field maintenance required on the earlier models due to the changing mode of operation. The new regenerator design has been created to meet the changing requirements of the applications.

Experimental Investigation of High Temperature Wear Resistant Coatings for Industrial Gas Turbine

2003 ◽  
Author(s):  
Hideyuki Matsuoka ◽  
Nobuo Shinohara ◽  
Yuji Sugita ◽  
Kunihiro Ichikawa ◽  
Hideyuki Arikawa ◽  
...  
Keyword(s):  
Wear Resistance ◽  
High Temperature ◽  
Gas Turbine ◽  
Vapor Deposition ◽  
Gas Turbines ◽  
Physical Vapor Deposition ◽  
Coating Materials ◽  
Severe Wear ◽  
High Temperature Wear ◽  
Industrial Gas Turbine

In the contact section of industrial gas turbine parts, wear can be observed after normal operations. Especially, in the contact area of combustors and their fittings, such as a transition piece and a seal plate, the severe wear may occur owing to combustion vibration under high temperature. If such severe wear occurs, some inspections or repair of the combustor parts may be needed. The short cycle of inspection and repair will decrease the performance of the gas turbine. Though combustors and their fittings are subjected to high temperature condition without any lubricant, any relevant prevention has not been developed yet. In this paper, wear resistance of ceramic hard coating materials, i.e. titanium nitride (TiN), titanium aluminum nitride (TiaAIN), chromium nitride (CrN), titanium carbide (TiC), silicon carbide (SiC), aluminum oxide (Al2O3) against various metals was tested under the condition similar to that in a gas turbines. These coatings were deposited by physical vapor deposition (PVD) or chemical vapor deposition (CVD) processes. It was concluded that, the combination of Al2O3 coating and stellite #6B had excellent high temperature wear resistance.

Improved Processing Route for Aluminization of Gas Turbine Components

2000 ◽  
Author(s):  
Thomas A. Kircher ◽  
David Solovei ◽  
Joseph H. Steck ◽  
Srinivasan (Shanks) Shankar
Keyword(s):  
Gas Turbine ◽  
Vapor Phase ◽  
Protective Coatings ◽  
Processing Route ◽  
Diffusion Capacity ◽  
Aluminide Coatings ◽  
Wide Range ◽  
Pack Aluminizing ◽  
Industrial Gas Turbine ◽  
High Degree

Pack aluminizing and vapor-phase aluminizing (VPA) are common methods for producing protective coatings on aero and industrial gas turbine hot section components. SermAlcote® slurry aluminization is an alternative to many industrial pack and vapor-phase aluminizing processes. SermAlcote® slurry aluminization processes are designed to meet existing commercial specifications while offering significant improvements in cost, quality and turntime over competitive aluminizing processes. Advantages of this processing route include simplified masking, shorter thermal processing cycles, improved diffusion capacity (no powder, simplified racks), and elimination of powder handling/storage concerns. Unlike conventional slurry aluminizing methods, the SermAlcote® process produces very uniform diffused aluminide coatings over a very wide range of applied slurry amounts. This simplifies the manufacturing process and produces high degree of process repeatability and uniformity. Data and examples are presented in order to describe the characteristics of SermAlcote® slurry aluminization processes for producing aluminide coatings, platinum-modified aluminide coatings, and over-aluminized MCrAlY coatings.

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