“…These markings are comparable to those observed on aerofoils in IGTs. 25 11 Photographs taken of the a leading and b trailing edges of blades exposed in the second stage of the cascade after its removal following the 300 h cascade/modified burner rig commissioning run. Note the presence of one ‘white’ blade that had over-heated due to a faulty cooling air supply system…”
Integrated gasification combined cycles can incorporate pre-combustion carbon capture. High-H 2 syngas produces high H 2 O levels after combustion, potentially accelerating gas turbine component damage. Determining materials systems' suitability for this novel environment requires exposures in representative environments. Thus, an existing 0.7 MW burner rig was modified to generate the combustion environment and incorporate a cascade of 15 air-cooled turbine blades. Computational fluid dynamic calculations using blade dimensions and flow requirements supported the cascade design and determined blade placement within the gas flow. Trials of the modified unit have shown that a simulated combusted H 2 -rich syngas composition was generated at gas temperatures ≤1440°C. A 1000 h exposure has been carried out with thermal barrier coated blades to demonstrate the operation of the unit.
“…These markings are comparable to those observed on aerofoils in IGTs. 25 11 Photographs taken of the a leading and b trailing edges of blades exposed in the second stage of the cascade after its removal following the 300 h cascade/modified burner rig commissioning run. Note the presence of one ‘white’ blade that had over-heated due to a faulty cooling air supply system…”
Integrated gasification combined cycles can incorporate pre-combustion carbon capture. High-H 2 syngas produces high H 2 O levels after combustion, potentially accelerating gas turbine component damage. Determining materials systems' suitability for this novel environment requires exposures in representative environments. Thus, an existing 0.7 MW burner rig was modified to generate the combustion environment and incorporate a cascade of 15 air-cooled turbine blades. Computational fluid dynamic calculations using blade dimensions and flow requirements supported the cascade design and determined blade placement within the gas flow. Trials of the modified unit have shown that a simulated combusted H 2 -rich syngas composition was generated at gas temperatures ≤1440°C. A 1000 h exposure has been carried out with thermal barrier coated blades to demonstrate the operation of the unit.
Gas-path diagnostics is an essential part of gas turbine (GT) condition-based maintenance (CBM). There exists extensive literature on GT gas-path diagnostics and a variety of methods have been introduced. The fundamental limitations of the conventional methods such as the inability to deal with the nonlinear engine behavior, measurement uncertainty, simultaneous faults, and the limited number of sensors available remain the driving force for exploring more advanced techniques. This review aims to provide a critical survey of the existing literature produced in the area over the past few decades. In the first section, the issue of GT degradation is addressed, aiming to identify the type of physical faults that degrade a gas turbine performance, which gas-path faults contribute more significantly to the overall performance loss, and which specific components often encounter these faults. A brief overview is then given about the inconsistencies in the literature on gas-path diagnostics followed by a discussion of the various challenges against successful gas-path diagnostics and the major desirable characteristics that an advanced fault diagnostic technique should ideally possess. At this point, the available fault diagnostic methods are thoroughly reviewed, and their strengths and weaknesses summarized. Artificial intelligence (AI) based and hybrid diagnostic methods have received a great deal of attention due to their promising potentials to address the above-mentioned limitations along with providing accurate diagnostic results. Moreover, the available validation techniques that system developers used in the past to evaluate the performance of their proposed diagnostic algorithms are discussed. Finally, concluding remarks and recommendations for further investigations are provided.
STRESZCZENIE W artykule przedstawiono cele i metody diagnostyki drganiowej okrętowych turbinowych silników spalinowych ze szczególnym uwzględnieniem badań w procesie rozruchu i zatrzymania silnika. Dokonano podziału metod na jakościowe i ilościowe oraz przedstawiono ich zakres stosowalności. Przedstawiono rolę baz danych identyfikujących cechy charakterystyczne parametrów drganiowych analizowanych w trybie on-line. Scharakteryzowano i sklasyfikowano metodę badań w stanach nieustalonych oraz przedstawiono wrażliwość symptomów drganiowych na występujące uszkodzenia. układów wirnikowych w procesie Przedstawiono metodykę identyfikacji uszkodzeń wybiegu silnika.
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