Vibration Analysis of Gas Turbine SIEMENS 162MW- V94.2 Related to Iran Power Plant Industry in Fars Province

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Figure 2. Typical relative vibration monitoring system

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Figure 3. Typical Eddy Current Probe System (CMSS 68)

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Gas turbines vibration monitoring systems are usually equipped with some contact piezoelectric probes. Absolute vibrations in mm/s RMS are measured. The absolute and relative vibration data are compared. Fake trips are distinguished easily by this method. Probe installation mistakes are usually caused such fake trips. Typical gas turbine condition monitoring contact probes shown in Figure 4.

Gas turbine systems are usually equipped with some vibration indicators. These indicators are usually installed in main board substations. The absolute and relative vibration data and trends are presented ^[2]. Besides, the basic principles of piezoelectric probes discussed in ^[3].

Figure 4. CA303 and CE136 Accelerometer

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Misalignment and unbalance is the most cause of machine vibration. An unbalanced rotor always cause more vibration and generates excessive force in the bearing area and reduces the life of the machine. Understanding and practicing the fundamentals of rotating shaft parameters is the first step in reducing unnecessary vibration, reducing maintenance costs and increasing machine uptime. Misalignment and unbalance have unique characteristics in FFT, TWF or phase behavior of machine. Vibration analysis could predict unexpected shut down in industrial plants ^[4].

Some successful vibration analysis case reports discussed in ^{[5, 6, 7, 8]}. Besides, field balance of gas turbine utilities discussed in ^[9]. In addition, the shaft crack is one of the most challenging concepts in most critical equipment fault diagnosis. The shaft crack characteristics are unique. The guidelines is identified in different ways. This fault is distinguished with different techniques. Moreover, some parametric study has been conducted to discuss the effect of the crack location and material gradient on both the natural frequencies and the corresponding mode shapes ^[10].

The journal bearing wear is considered as an important factor in preventive maintenance. This factor is affected by lubrication. The oil sample locations care identified by CM engineers. Nowadays new lubricants are introduced to lubrication world. An environmental friendly palm-grease has already been formulated from modified RBDPO (Refined Bleach Deodorized Palm Oil) as base oil and lithium soap as thickener. Such palm-grease is dedicated for general application and equipment working in different industries (such as oil and petrochemical industries). This type of lubricants are improved the machine performance. Besides, these lubricants are usually used for high speed machines. Tribology performance, especially the anti-wear property of this lubricant are considerably improved ^[11].

The signal processing methods are developed too much in recent years. One of the alternative statistical analysis is known as I-kaz Multi Level method. This method was originally developed base on I-kaz TM but with higher order of signal decomposition. The new I-kaz Multi Level method was proven very sensitive and detects very well in amplitude and frequency changes of a measured signal. Nowadays high speed machines TWF and FFT are achieved with more resolutions^[12].

Robust real-time surveillance and secure system, for critical oil pipeline infrastructures, with combination of conventional network and wireless sensor network along with microwave network shows significant improvement with eleven times more efficient to conventional systems by reducing leakage and loss reporting time to control center. This system will be more efficient to detect any threats in real time and can report to central control room without any further delay. These techniques are recently developed for gas turbine condition monitoring specially in remote areas ^[13].

Different maintenance strategies such as corrective, time based, preventive, condition-based and predictive maintenance are used for different equipment. New fuzzy multi criteria model is introduced and it is used for the optimization decision making of the complex systems. Maintenance strategies have been modeled with consideration of several fuzzy parameters. Different machine parts with respect to introduced criteria may need different maintenance policies. Suitable maintenance policies can be selected ^[14].

Several modern vibration monitoring systems are recently developed in USA for gas turbines. The vibration monitoring system acquires vibration data from an engine and processes the data with advanced algorithms to determine engine component health, both in a diagnostic and prognostic fashion. The method includes the steps of measuring an operating parameter and a corresponding set of vibration amplitudes for a plurality of rotating components during a period of operation and normalizing the set of measured vibration amplitudes based on established amplitude limits.

According to one embodiment, the method comprises, receiving engine data from the turbine engine while in service, where the engine data include vibration data measured by one or more sensors disposed on the turbine engine. The method further comprises receiving user input through a user interface, processing the vibration data in response to the user input and displaying the processed vibration data through the user interface.

The processed data being displayed as a function of a time parameter. According to another embodiment, the method comprises, receiving engine data from the plurality of turbine engines while in service, where the engine data include vibration data measured by a plurality of sensors disposed on the turbine engines. The method further includes receiving user input through a user interface, processing the vibration data in response to the user input and displaying the processed vibration data through the user interface. The processed data being displayed as a function of a time parameter associated with at least one of the turbine engines.

According to still another embodiment, the system comprises a general data module configured to receive periodic data from a controller of a turbine engine. The periodic data representing operational states of the turbine engine, a vibration data module configured to receive vibration data from a measurement module associated with the turbine engine and generate a functional relationship between the vibration data and a time parameter according to user input.

The vibration data including information about vibration of the turbine engine provided by a plurality of sensors associated with the turbine engine. The database configured to store periodic and vibration data. This method provide the historical data in response to the user input. Historical data module configured to retrieve the periodic and vibration data from the database. Some display device configured to display periodic, vibration, and historical data^[15].

2. Experimental Details

The case history about vibration and operation behavior of gas turbine SIEMENS 162MW- V94.2 Related to Iran Power Plant Industry in Fars Province is explained in this part. Gas turbine technical specifications are briefly discussed. Gas Turbine Features are represented in Figure 5.

Figure 5. SIEMENS V94.2 Gas Turbine Features

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Figure 6. V94.2 Gas Turbine Combustion chamber features

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Gas Turbine Combustion chamber features are represented in Figure 6.

The blading system is SI3D. the blades are described as vane #1 and vane #2.

Figure 7. Some SI3D Blading Samples

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Main rotor and typical blades related to gas turbine SIEMENS162MW- V94.2 are shown in Figure 8. In addition, blades design features plot is shown in Figure 9.

Figure 8. Typical blades related to gas turbine SIEMENS162MW- V94.2

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Figure 9. Blades design features plot

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Employing wet compression system available in market since 2003.

Figure 10. wet compression process

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Machinery features and basic principles related to gas turbine SIEMENS162MW- V94.2 are determined. Vibration analysis will discussed in details in the next stage. Before, it is worthy to discuss some new and interesting patent and innovation in gas turbine world ^[16].

Turbine blade for industrial gas turbine is used which includes a blade substrate formed of a single-crystal heat-resistant alloy containing C: 0.06 to 0.08%, B: 0.016 to 0.035%, Hf: 0.2 to 0.3%, Cr: 6.9 to 7.3%, Mo: 0.7 to 1.0%, W: 7.0 to 9.0%, Re: 1.2 to 1.6%, Ta: 8.5 to 9.5%, Nb: 0.6 to 1.0%, Al: 4.9 to 5.2%, Co: 0.8 to 1.2%, and the remainder substantially consisting of Ni with reference to mass, and includes a diffusion barrier layer, a metal layer, a bond coat, and a top coat, these layers and coats being stacked in this order on a surface of the blade substrate, the metal layer having a thickness of 5 to 30 μm.

Therefore, the turbine blade can be provided which has a thermal barrier coating formed without loss of a function of the diffusion barrier layer ^[15].

Damper system recently developed in gas turbine world. The damper includes a width dimension, a height dimension, and a length dimension, and a forward plate and an automatic fine tuning (AFT) plate. The AFT plate is larger than the forward plate along the width and height dimension and includes an upper portion extending in the height dimension, the upper portion having a non-symmetric configuration. The damper further includes a longitudinal structure extending in the length dimension and connecting the forward plate and the AFT plate. The damper includes a width dimension, a height dimension, and a length dimension, and a forward plate.

The damper includes an AFT plate including a larger area than the forward plate along the width and height dimension, an upper portion having an upper point that is offset with respect to a central axis of the AFT plate extending in the height dimension, and a rectangular-shaped discourager extending AFT in the length dimension from the AFT plate. The damper also includes a longitudinal structure extending in the length dimension and connecting the forward plate and the AFT plate.

The turbine rotor assembly includes a turbine rotor having a plurality of turbine blade slots, and a plurality of turbine blades having an airfoil, a platform, and a root structure, the root structure of each turbine blade shaped to be received in a corresponding turbine blade slot of the turbine rotor. The turbine rotor assembly also includes an under-platform gap formed adjacent and below the platforms of adjacent turbine blades, and an under-platform cavity formed between an outer radial surface of the rotor and adjacent turbine blade root structures, and below adjacent turbine blade platforms. The turbine rotor assembly further includes a turbine damper located within at least one of the under-platform cavities, the turbine damper including a width dimension, a height dimension, and a length dimension. The damper further includes a forward plate sized to provide a forward flow gap into the under platform cavity and the under-platform gap, and an AFT plate sized to cover a portion of the under platform cavity and a portion of the under-platform gap ^[15].

Gas-turbine engines used in transportation, energy, and defense sectors rely on high-temperature thermal-barrier coatings (TBCs) for improved efficiencies and power. The promise of still higher efficiencies and other benefits is driving TBCs research and development worldwide. An introduction to TBCs-complex, multi-layer evolving systems is presented, where these fascinating systems touch on several known phenomena in materials science and engineering ^[17].

Facilitates removal of the patent pending lateral generator from between the turbines for maintenance or repair already investigated by several gas turbine manufacturers ^[18].

Energy efficiency is one of the main objectives for the development of new power plant technology in order to reduce fuel consumption and emissions. In response to the increasing, worldwide need for reliable, low cost and environmentally compatible generation. New Siemens SGT5-8000H Gas Turbine recently introduced by Siemens Company.

The SGT5-8000 H will have a net power output of at least 340 MW and will be optimized for the combined cycle process with a net power output of more than 530 MW and a efficiency over 60%. A major benefit for the customer is the high efficiency of 60%. Efficiency not only plays an important role with respect to environmental aspects, but also for the profitability of the power plant.

As fuel is the largest single cost item for running a power plant, an increase of two percentage points can save the operator millions of Euros over the entire life cycle of a combined cycle power plant with a capacity of 530 MW ^[19].

3. Results and Discussion

In this part a case history related to Gas Turbine SIEMENS V94.2 is explained. This gas turbine is related to Iran Power Plant Industry in Fars Province and is in main operation board high vibration.

Case history

Duration: Tuesday, April 24, 2012 to Friday, May 4, 2012.

After facing some problems in gas turbine Fars utility startup period, the gas turbine was tripped in 1000 RPM. The trip was because of high amounts of vibrations. The vibration groups were take part a session for analyzing the balancing condition of rotor and gas turbine foundation.

Both the balancing and foundation maintenance data was in good conditions then vibration groups decided to close monitoring the gas turbine. Further investigations in maintenance history showed that gas turbine middle shaft was falling during machinery maintenance actions and installed after repair in machinery workshop. There was a strong hypothesis that this may the main root of all vibration problems in this machine. The vibration analysis of hypothesis are discussed.

Besides, other possibilities are mentioned. First, the electronic group checked the absolute and relative conditioners to adjust the related options with technical documents. Then the analyzer group readjust all the adaptation numbers in turning gear condition with technical document. After that, all the relative vibrations in turbine, compressor and generator were monitored in 600 RPM in the next stage.

The operation condition were not agree to continue increasing RPM then in the next day the gas turbine first start up to 600 RPM then process were decided to reduce the RPM up to 450 and after one hour they were increased the RPM little by little up to 990 RPM gradually. In this stage Gas turbine trip occurred because of high amount of absolute vibrations. As we checked all the trend of vibration monitoring data it was clear that the gas turbine did not have any problem up to 750 RPM.

In addition, there was an acceptable adaptation between all monitoring systems in process board and CM vibration trends in both absolute and relative monitoring systems. Unfortunately, after 750 RPM the related vibrations were increasing gradually. In addition, the absolute vibrations were increased dramatically after 940 RPM but relative vibrations were decreased slightly.

Absolute vibrations were increased and relative vibrations were decreased simultaneously! This increasing in absolute vibration in turbine side was 17.5 mm/s RMS that caused vibration trip in 990 RPM.

The absolute and relative vibrations were decreased slightly in the same manner in trip period. Furthermore, All journals temperature monitoring trends was normal and in range during this period. The decreasing relative vibration with increasing in absolute vibration never seen in other gas turbines by the vibration groups and seem to be a new vibration behavior!

Figure 11. Absolute and relative vibration trends from control monitoring system process main board

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Because of low frequency condition, the absolute sensors cannot help in vibration analysis but there is some valuable information in relative sensors data that called slow roll in CM texts and will help us in shaft centerline analysis.

Figure 12. Turbine and compressor orbit OCE and CE in turning gear condition

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Table 1. Shaft position by 9-volt initial installation

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Tables index

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Vibrations in 750 RPM should be focused because of the higher amplitudes. Besides, The FFT in 600 RPM is shown in Figure 14.

Figure 13. FFT Absolute vibrations turbine side in 600 RPM (horizontal, vertical and axial)

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750 RPM approximately is beginning of the first gas turbine SIEMENS162MW- V94.2 critical speed and the vibration data in this condition can help too much for the gas turbine vibration analysis.

Figure 14. Relative vibrations FFT turbine 1, turbine 2, compressor and OCE in 750 RPM

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Figure 15. Orbits turbine, compressor, OCE and CE in 750 RPM

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The gas turbine vibration modal analysis is shown in Figure 17. Vibration modal analysis is obtained by using the phase values and their trends in different locations (points).

Figure 16. Vibration modal analysis 1X (left is related to turbine side)

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Vibration monitoring system in operation main board showed that the relative vibration decreased suddenly when absolute vibration caused gas turbine trip. In addition, CM vibration graphs indicated the same information.

Figure 17. Turbine and compressor start up and shut down condition (trip position are indicated by cursor)

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Figure 18. Turbine relative vibrations Bode diagrams

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Figure 19. Compressor relative vibrations Bode diagrams

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The reason of this phenomena could be discovered by drawing bode diagrams for relative vibration sensors in both turbine and compressor.

As shown in above bode diagrams, overall amplitude vibration was decreased in one sensor and was increased in other sensor simultaneously!

This increasing behavior is related to a turbine side mode of vibration for 940 RPM in 30 sensor but this mode of vibration was disappeared and was replaced by another mode of vibration in 90 sensor.

This phenomena was caused high amount of vibrations in turbine side and was occurred after increasing RPM. Besides, this phenomena are indicated in gas turbine Nyquist diagrams and is called Split Resonance. Split Resonance may cause Backward whirl between 940 to 980 RPM in both turbine and compressor journals ^[20].

Figure 20. Turbine and compressor relative vibrations Nyquist diagrams

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Finally, turbine and compressor relative vibrations waterfall or three-dimensional FFT diagrams were obtained (for startup and trip). These diagrams were developed some hypothesis in gas turbine fault diagnosis.

Figure 21. Turbine and compressor three-dimensional FFT diagrams for startup and trip (waterfall graphs)

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