Performance of Gas Turbine Compressor Cleaners

1993 ◽  
Vol 115 (3) ◽  
pp. 674-677 ◽  
Author(s):  
H. J. Kolkman
Keyword(s):  
Corrosion Inhibitor ◽  
Gas Turbine ◽  
Corrosion Inhibition ◽  
Gas Turbines ◽  
Jet Engines ◽  
Cleaning Efficiency ◽  
Compressor Blades ◽  
Gas Turbine Compressor

Deposits are regularly removed from compressor blades and vanes of installed jet engines and gas turbines by compressor washing. A compressor cleaner is sprayed into the compressor while operating at reduced or normal rpm. Recently developed compressor cleaners are claimed to be ecologically sound. In addition, many new compressor cleaners contain a corrosion inhibitor. The cleaning efficiency of eight (old and new) compressor cleaners was determined by means of simulated compressor washing of compressor blades that had become fouled in service. For the situation simulated, the cleaning efficiency of new, ecologically sound cleaners turned out to be poor as compared with old compressor cleaners. The corrosion inhibition offered by those cleaners that contain a corrosion inhibitor was found to be satisfactory.

Performance of Gas Turbine Compressor Cleaners

1992 ◽  
Author(s):  
H. J. Kolkman
Keyword(s):  
Corrosion Inhibitor ◽  
Gas Turbine ◽  
Corrosion Inhibition ◽  
Gas Turbines ◽  
Jet Engines ◽  
Cleaning Efficiency ◽  
Compressor Blades ◽  
Gas Turbine Compressor

Deposits are regularly removed from compressor blades and vanes of installed jet engines and gas turbines by compressor washing. Hereby a compressor cleaner is sprayed into the compressor while operating at reduced or normal r.p.m. Recently developed compressor cleaners are claimed to be ecologically sound. In addition, many new compressor cleaners contain a corrosion inhibitor. The cleaning efficiency of eight (old and new) compressor cleaners was determined by means of simulated compressor washing of compressor blades that had become foul in service. For the situation simulated, the cleaning efficiency of new, ecologically sound cleaners turned out to be poor as compared with old compressor cleaners. The corrosion inhibition offered by those cleaners that contain a corrosion inhibitor was found to be satisfactory.

Degradation of Compressor Blades of Gas Turbines in Coastal and Industrial Environment

2016 ◽  
Vol 1133 ◽  
pp. 371-375 ◽  
Author(s):  
Salmi Mohd Yunus ◽  
Saiful Adilin Sekari ◽  
Mohd Hafiz Abdul Ghaffar
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Unit ◽  
Oil Refinery ◽  
Oil Refining ◽  
Degradation Mechanisms ◽  
Gas Turbine Unit ◽  
Compressor Blades ◽  
Industrial Environment ◽  
Gas Turbine Compressor

Gas turbine compressor blades will age and degrade in their operation. There are a lot of factors that will contribute to the degradation mechanisms and its acceleration. These factors encompass the site location, the site conditions including the aspect of air quality, water washing practice, etc. A study undertaken by Materials Engineering Group of TNB Research Sdn Bhd on 2 units of gas turbine compressor those are located near to the sea around Peninsular of Malaysia, to determine the degradation mechanisms of the blades. All these gas turbine units are located in different industrial environment. The first gas turbine unit, so called GTA is located in coastal, petrochemicals production and crude oil refining environment. The second gas turbine unit, so called GTB, located in coastal and industrial environment. The surrounding industries of GTB including oil refinery, chemical, ship fabrication and etc. This paper reports the degradation type of those gas turbine units’ compressor blades with their contributing factors.

On Line Compressor Washing on Large Frame 9-FA Gas Turbines: Erosion on R0 Compressor Blade Leading Edge — Field Performance With a Novel On Line Wash System

2007 ◽  
Author(s):  
Jos Oosting ◽  
Klaas Boonstra ◽  
Annemarie de Haan ◽  
Dick van der Vecht ◽  
Jean-Pierre Stalder ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Leading Edge ◽  
Compressor Blade ◽  
Cleaning Efficiency ◽  
Compressor Blades ◽  
Erosion Risk ◽  
Plant Operator ◽  
On Line ◽  
Blade Leading Edge

On line compressor washing is an established practice amid gas turbine operators. Among these operators is the Netherlands Division of Electrabel who is operating at Eemshaven 5 x GE Frame 9-FA units since 1995. The plant operator used to perform routinely a daily on line wash and a single off line wash every year at shut down of the units for the annual inspection or maintenance outage. The on line water wash (OLWW) systems installed on these 5 engines are of the Turbotect Mk1 nozzle design and were originally procured and supplied by the OEM. To our knowledge, all other manufactured gas turbines in the 7/9-FA fleet are equipped with the OEMs’ own engineered OLWW nozzle systems. The OLWW regime of washing was reduced in June 2001 upon receipt of a recommendation by the OEM to inspect the first stages of the compressor for erosion marks. This recommendation was issued because some events have lead to investigation on erosion issues which materialized in the R0 (first stage rotor) compressor blades in some engines of the 7/9-FA fleet operating with the OEM OLWW system and resulting from frequent compressor wash routine, and/or from water ingestion used in power augmentation. Likewise, during the same time, some gas turbines at Eemscentrale had undergone their first major overhaul which allowed the compressor first row blading to be examined for signs of erosion. It was found that only minor erosion at the R0 blade leading edge had occurred over more than seven years of operation, during which period a daily on line wash had been performed. However, because of the erosion concerns among the 7/9-FA fleet and the OEM-recommended frequent inspections and measures to mitigate the rate of erosion due to droplet impingement, Electrabel investigated independently for a way of further reducing the erosion rate while maintaining on line washing over the lifetime of the gas turbine and improving the cleaning efficiency. To this effect, the OLWW system on unit EC-6 was upgraded in June 2004 with a new on line nozzle system specifically developed for use in large gas turbines. This paper presents the investigation results after some 24 months of operation and routine on line compressor washing. The Turbotect Mk3 OLWW nozzle system demonstrated and confirmed that it is contributing to mitigate the erosion risk on the R0 compressor blade leading edge, and in turn to decrease the number of blending operations over the life time of the R0 compressor blades. This nozzle designed for on line compressor cleaning of large gas turbines achieved a substantially improved cleaning effectiveness, respectively a lower rate in power degradation, by approx. 30 to 40% as compared to the current in use Mk1 OLWW nozzle system.

Influence of Blade Fillets on the Performance of a 15 Stage Gas Turbine Compressor

2008 ◽  
Author(s):  
E. Ku¨geler ◽  
D. Nu¨rnberger ◽  
A. Weber ◽  
K. Engel
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Guide Vane ◽  
Measurement Data ◽  
Rotor Blades ◽  
Jet Engines ◽  
Wall Functions ◽  
Multistage Compressors ◽  
The Individual ◽  
Gas Turbine Compressor

In the modern process of the aerodynamic design of multistage compressors and turbines for jet engines as well as for stationary gas turbines, 3D-CFD plays a key role. Before building the first test rig several designs have been investigated using numerical simulations. To understand the characteristics of the individual components it is necessary to simulate their behavior in a multistage simulation and investigate for example, the single stage maps of the compressor in order to understand how the load is divided between the different parts of the compressor during throttling. Increasing computing resources allow ever more details to be incorporated in a 3D simulation. In former times only single blade rows were investigated with a high resolution of the boundary layers, whereas in multistage configurations wall functions were state of the art. Today we are able to apply Low Reynolds resolution even for multistage configurations, so the designer is required to include more and more geometrical details into the simulation. One important such feature is the fillets of rotor and stator blades. Fillets reduce the flow deflection at the endwalls and therefore the loading of the downstream blade rows. This effect is accumulated in a multistage simulation. In this paper a 15-stage compressor with additional inlet and outlet guide vane designed for a stationary gas turbine was investigated with a modern CFD tool by using a real gas approach for two speedlines. Two simulations were done: first a clean configuration with tip and hub clearances but without blade fillets; in the second simulation all rotor blades and the cantilevered stator blades were additionally modeled with fillets. The comparison of the overall global values with measurement data shows a better performance of the simulation with fillets, especially by throttling the compressor. A deeper look into the compressor shows different loads for a considerable number of single stages. The analysis of the steady multistage simulations shows that the numerical stability is reached in different regions of the machine.

The United States Navy “Standard Day” for Marine Gas Turbines

2017 ◽  
Author(s):  
John Hartranft ◽  
Bruce Thompson ◽  
Dan Groghan
Keyword(s):  
United States ◽  
Gas Turbine ◽  
United States Navy ◽  
Gas Turbines ◽  
The United States ◽  
Industrial Applications ◽  
Jet Engines ◽  
Jet Engine ◽  
Advantages And Disadvantages ◽  
Power Capability

Following the successful development of aircraft jet engines during World War II (WWII), the United States Navy began exploring the advantages of gas turbine engines for ship and boat propulsion. Early development soon focused on aircraft derivative (aero derivative) gas turbines for use in the United States Navy (USN) Fleet rather than engines developed specifically for marine and industrial applications due to poor results from a few of the early marine and industrial developments. Some of the new commercial jet engine powered aircraft that had emerged at the time were the Boeing 707 and the Douglas DC-8. It was from these early aircraft engine successes (both commercial and military) that engine cores such as the JT4-FT4 and others became available for USN ship and boat programs. The task of adapting the jet engine to the marine environment turned out to be a substantial task because USN ships were operated in a completely different environment than that of aircraft which caused different forms of turbine corrosion than that seen in aircraft jet engines. Furthermore, shipboard engines were expected to perform tens of thousands of hours before overhaul compared with a few thousand hours mean time between overhaul usually experienced in aircraft applications. To address the concerns of shipboard applications, standards were created for marine gas turbine shipboard qualification and installation. One of those standards was the development of a USN Standard Day for gas turbines. This paper addresses the topic of a Navy Standard Day as it relates to the introduction of marine gas turbines into the United States Navy Fleet and why it differs from other rating approaches. Lastly, this paper will address examples of issues encountered with early requirements and whether current requirements for the Navy Standard Day should be changed. Concerning other rating approaches, the paper will also address the issue of using an International Organization for Standardization, that is, an International Standard Day. It is important to address an ISO STD DAY because many original equipment manufacturers and commercial operators prefer to rate their aero derivative gas turbines based on an ISO STD DAY with no losses. The argument is that the ISO approach fully utilizes the power capability of the engine. This paper will discuss the advantages and disadvantages of the ISO STD DAY approach and how the USN STD DAY approach has benefitted the USN. For the future, with the advance of engine controllers and electronics, utilizing some of the features of an ISO STD DAY approach may be possible while maintaining the advantages of the USN STD DAY.

A Statistical Study on HCF Validation Data for Axial Gas Turbine Compressor Blades

2021 ◽  
Author(s):  
Lukas Schuchard ◽  
Stefano Cerutti ◽  
Matthias Voigt ◽  
Ronald Mailach
Keyword(s):  
Gas Turbine ◽  
Statistical Study ◽  
Compressor Blades ◽  
Validation Data ◽  
Gas Turbine Compressor

Failure Investigation of Frame 6FA Gas Turbine Compressor Blades

2015 ◽  
Vol 69 (2) ◽  
pp. 647-651 ◽  
Author(s):  
M. Swamy ◽  
Kulvir Singh ◽  
A. H. V. Pavan ◽  
Antony Harison M. C. ◽  
G. Jayaraman
Keyword(s):  
Gas Turbine ◽  
Compressor Blades ◽  
Failure Investigation ◽  
Gas Turbine Compressor

Blade Faults Diagnosis in Power Generation Gas Turbines

2017 ◽  
Author(s):  
Meng Hee Lim ◽  
Salman Leong ◽  
Kar Hoou Hui
Keyword(s):  
Power Generation ◽  
Statistical Analysis ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Vibration Signal ◽  
Health Condition ◽  
Baseline Data ◽  
Compressor Blades ◽  
Industrial Gas Turbines

This paper presents a case study in managing the dilemma of whether to resume or stop the operation of a power generation gas turbine with suspected blade faults. Vibration analysis is undertaken on the vibration signal of the gas turbine, to obtain an insight into the health condition of the blades before any decision is made on the operation of the machine. Statistical analysis is applied to study the characteristics of the highly unstable blade pass frequency (BPF) of the gas turbine and to establish the baseline data used for blade fault assessment and diagnosis. Based on the excessive increase observed on specific BPF amplitudes in comparison to the statistical baseline data, rubbing at the compressor blade is suspected. An immediate overhaul is therefore warranted, and the results from the inspection of the machine confirm the occurrence of severe rubbing at the compressor blades and labyrinth glands of the gas turbine. In conclusion, statistical analysis of BPF amplitude is found to be a viable tool for blade fault diagnosis in industrial gas turbines.

Determination of Vibration Amplitudes and Stresses Using the Holography Interference Techniques and Finite Element Method

1983 ◽  
Vol 105 (4) ◽  
pp. 484-488 ◽  
Author(s):  
Z. F. Fu
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Gas Turbine ◽  
Strain Gage ◽  
Present Method ◽  
The Finite Element Method ◽  
Compressor Blades ◽  
Gas Turbine Compressor ◽  
Element Method

A new method which combines the holography interference technique with the finite element method for determining the distribution of vibration amplitudes and stresses of gas turbine compressor blades is presented in this paper. In comparison with the ordinary electrical strain gage method, the present method has the advantage that there is no limitation to the number of measuring points and good results can be obtained even at high order modes.

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