Application of an Optical Pyrometer to Newly Developed Industrial Gas Turbine

2012 ◽  
Author(s):  
Tomoki Taniguchi ◽  
Ryozo Tanaka ◽  
Yuji Shinoda ◽  
Masanori Ryu ◽  
Norbert Moritz ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Evaluation Process ◽  
Optical Pyrometer ◽  
Blade Surface ◽  
High Pressure Turbine ◽  
Low Pressure Turbine ◽  
Lower Temperature ◽  
Measurement And Evaluation ◽  
Industrial Gas Turbine ◽  
Engine Condition

Kawasaki Heavy Industries, Ltd (KHI) have developed a new industrial gas turbine, L30A. The turbine section composed of two-stage high pressure turbine and three-stage low pressure turbine. In the development period, a commercial pyrometer system was employed to measure blade temperatures under real engine condition. The pyrometer was equipped with an updated detector module and could measure lower temperature compared to the conventional one. Thus it could be used to measure all stages of blades with one pyrometer. The validity of the result was demonstrated by comparing the result with data obtained with other conventional techniques. With the pyrometer system the temperature distribution on the blade surface was easily available and cooling capabilities of blades were evaluated without taking much time. This paper describes the detail of measurement and evaluation process.

Development of FT9 Marine Gas Turbine

1981 ◽  
Author(s):  
D. A. Groghan ◽  
C. L. Miller
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
System A ◽  
On Line ◽  
Condition Monitoring System ◽  
Industrial Gas Turbine ◽  
Engine Condition

The FT9 Marine Gas Turbine development program was initiated in August 1973 by the Naval Sea Systems Command to fulfill, in part, the requirement for a family of gas turbine engines ranging in power from 1000 to 30,000 hp. The FT9 satisfied the requirement to develop a 30,000 hp class marine gas turbine. The FT9 is a derivative of the Pratt & Whitney Aircraft JT9D engine, which powers Boeing 747, DC-10 and A300 aircraft, and of the FT4 industrial gas turbine engine. The FT9 specification also required development of an on-line engine condition monitoring system. A rigorous development test program showed the FT9 has met all specified U.S. Navy requirements and demonstrated its suitability for use in U.S. Navy combatant ships.

Effects of Anti-Icing System Operation on Gas Turbine Performance and Monitoring

2001 ◽  
Author(s):  
K. Mathioudakis ◽  
A. Tsalavoutas
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Performance Model ◽  
False Alarms ◽  
System Operation ◽  
Diagnostic Ability ◽  
Engine Model ◽  
On Line ◽  
Industrial Gas Turbine ◽  
Engine Condition

The effect of operation of compressor bleed anti-icing on the performance of an industrial gas turbine is analysed. The effect of putting this system in operation is first qualitatively discussed, while the changes on various performance parameters are derived by using a computer engine performance model. The main point of the paper is the study of the effect of anti-icing system operation on parameters used for engine condition monitoring. It is shown that operation of the anti-icing system causes an apparent modification of such parameters, which may reduce the diagnostic ability of an on-line monitoring system and produce false alarms. It is shown that by incorporating the effect of anti-icing system operation into a diagnostic engine model, such problems can be avoided and the diagnostic ability of the system is not influenced by anti-icing activation. The analysis presented is substantiated through experimental data from a twin shaft gas turbine operating in the field.

The Design and Test of Air-Cooled Blading for an Industrial Gas Turbine

1982 ◽  
Author(s):  
J. M. Hannis ◽  
M. K. D. Smith
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Turbine Stage ◽  
High Pressure Turbine ◽  
Transient Conditions ◽  
Blade Cooling ◽  
Advance Information ◽  
Industrial Gas Turbine ◽  
Design And Testing ◽  
A Current

The design and testing of a cooled high pressure turbine stage to provide advance information for the Ruston Tornado 6MW industrial gas turbine is described. The cooled stage was designed to replace an existing uncooled stage in a current Ruston gas turbine to allow development testing under actual engine conditions. The instrumentation techniques used on the development engine, including infrared pyrometry, are discussed and results of the tests covering nozzle vane and rotor blade cooling under steady state and transient conditions and engine performance are presented and compared with the design predictions.

Numerical Investigations on the Effects of Swirling Combustor Exit Flow on HP-Turbine Inlet Flow for the Industrial Gas Turbine THM 1304

1993 ◽  
Author(s):  
K. J. Bauermeister ◽  
H.-J. Dohmen ◽  
H. Simon
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Swirling Flow ◽  
Flow Direction ◽  
Flow Distribution ◽  
Flow Conditions ◽  
High Pressure Turbine ◽  
Worst Case ◽  
Turbine Inlet ◽  
Industrial Gas Turbine

To reduce gas turbine exhaust emissions the combustion system of the MAN GHH industrial gas turbine THM 1304 (ISO power 9250 kW) has been modified. The two outboard combustors in a V–configuration enabled to enlarge the chambers and thus to increase the retention time. Compared to the initial design the nature of combustor exit flow is considerably changed to an additional swirling flow. To estimate the effects of these flow conditions on gas turbine performance the flow towards the high pressure turbine should be investigated. For that purpose a numerical flow simulation in the casing between the combustion chambers and the high pressure turbine nozzles has been accomplished. A Navier–Stokes–Solver (Finite Element Method) has been applied to the computation of the threedimensional turbulent flow. The essential results, especially the flow conditions in front of the HP–turbine nozzles are presented with respect to the idealized combustor exit flow conditions. Besides the swirl strength, the direction of rotation and the swirl relation are varied. It is shown, that the flow at HP–turbine inlet is essentially characterized by the mainly centripetally directed combustor exit flow. Dependent on the above mentioned swirl flow parameters the characteristic flow distribution at HP–turbine inlet changes more or less. In the most favourable case the mass flow distribution at HP–turbine inlet varies circumferentially approx. ±14% and in the worst case approx. ±26%. Associated deviations from the ideal axial flow direction of approx. ±30° respectively ±40° are calculated.

The Design and Testing of Air-Cooled Blading for an Industrial Gas Turbine

1983 ◽  
Vol 105 (3) ◽  
pp. 466-473 ◽  
Author(s):  
J. M. Hannis ◽  
M. K. D. Smith
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Turbine Stage ◽  
High Pressure Turbine ◽  
Transient Conditions ◽  
Blade Cooling ◽  
Advance Information ◽  
Industrial Gas Turbine ◽  
Design And Testing ◽  
A Current

The design and testing of a cooled high-pressure turbine stage to provide advance information for the Ruston Tornado 6MW industrial gas turbine is described. The cooled stage was designed to replace an existing uncooled stage in a current Ruston gas turbine to allow development testing under actual engine conditions. The instrumentation techniques used on the development engine, including infrared pyrometry, are discussed and results of the tests covering nozzle vane and rotor blade cooling under steady-state and transient conditions and engine performance are presented and compared with the design predictions.

Implementing TQM practices in Pakistani Higher Education Institutions

2016 ◽  
Vol 2 (1) ◽  
Author(s):  
Rizwan Ahmed ◽  
Syed Iftikhar Ali
Keyword(s):  
Higher Education ◽  
Process Control ◽  
Business Schools ◽  
Higher Education Institutions ◽  
Evaluation Process ◽  
Theoretical Framework ◽  
Educational Institutions ◽  
Higher Educational Institutions ◽  
Main Factors ◽  
Measurement And Evaluation

<span>Implementing TQM practices at the Higher Educational Institutions of Pakistan,<span> especially at the business schools, is relatively a new concept and it is in its initial stages.<span> The theoretical framework of this study is based upon the instrument that measures the<span> extent of TQM implementation in Higher Education Institutions. Based upon literature<span> review, the framework having 14 dimensions is used in this study. Exploratory Factor<span> Analysis (EFA) extracted 13 factors as the determinants of TQM Implementation in<span> business schools of Pakistan such as Stakeholders’ Focus, Recognition and Reward,<span> Measurement and Evaluation, Process Control and Improvement, Resources, Leadership,<span> Empowerment are some of the main factors as each of these factors are explaining more<span> than 5% of the variation in the data<br /><br class="Apple-interchange-newline" /></span></span></span></span></span></span></span></span></span></span>

Development of L1-norm sliding mode observer for sensor fault diagnosis of an industrial gas turbine

2021 ◽  
pp. 095965182199617
Author(s):  
Mahyar Akbari ◽  
Abdol Majid Khoshnood ◽  
Saied Irani
Keyword(s):  
Fault Detection ◽  
State Space ◽  
Gas Turbine ◽  
Sliding Mode ◽  
State Space Model ◽  
Sensor Fault ◽  
Space Model ◽  
Decision Logic ◽  
Sensor Fault Detection ◽  
Industrial Gas Turbine

In this article, a novel approach for model-based sensor fault detection and estimation of gas turbine is presented. The proposed method includes driving a state-space model of gas turbine, designing a novel L1-norm Lyapunov-based observer, and a decision logic which is based on bank of observers. The novel observer is designed using multiple Lyapunov functions based on L1-norm, reducing the estimation noise while increasing the accuracy. The L1-norm observer is similar to sliding mode observer in switching time. The proposed observer also acts as a low-pass filter, subsequently reducing estimation chattering. Since a bank of observers is required in model-based sensor fault detection, a bank of L1-norm observers is designed in this article. Corresponding to the use of the bank of observers, a two-step fault detection decision logic is developed. Furthermore, the proposed state-space model is a hybrid data-driven model which is divided into two models for steady-state and transient conditions, according to the nature of the gas turbine. The model is developed by applying a subspace algorithm to the real field data of SGT-600 (an industrial gas turbine). The proposed model was validated by applying to two other similar gas turbines with different ambient and operational conditions. The results of the proposed approach implementation demonstrate precise gas turbine sensor fault detection and estimation.

Performance Prediction of Gas Turbine Under Different Strategies Using Low Heating Value Fuel

2013 ◽  
Author(s):  
Edson Batista da Silva ◽  
Marcelo Assato ◽  
Rosiane Cristina de Lima
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Equivalence Ratio ◽  
Safe Operation ◽  
Engine Operation ◽  
Heating Value ◽  
Gasification Process ◽  
Surge Margin ◽  
And Performance ◽  
Industrial Gas Turbine

Usually, the turbogenerators are designed to fire a specific fuel, depending on the project of these engines may be allowed the operation with other kinds of fuel compositions. However, it is necessary a careful evaluation of the operational behavior and performance of them due to conversion, for example, from natural gas to different low heating value fuels. Thus, this work describes strategies used to simulate the performance of a single shaft industrial gas turbine designed to operate with natural gas when firing low heating value fuel, such as biomass fuel from gasification process or blast furnace gas (BFG). Air bled from the compressor and variable compressor geometry have been used as key strategies by this paper. Off-design performance simulations at a variety of ambient temperature conditions are described. It was observed the necessity for recovering the surge margin; both techniques showed good solutions to achieve the same level of safe operation in relation to the original engine. Finally, a flammability limit analysis in terms of the equivalence ratio was done. This analysis has the objective of verifying if the combustor will operate using the low heating value fuel. For the most engine operation cases investigated, the values were inside from minimum and maximum equivalence ratio range.

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