Wyniki wyszukiwania - BazTech

Ograniczanie wyników

Znaleziono wyników: 2

Liczba wyników na stronie

Wyniki wyszukiwania

Sortuj według:

Ogranicz wyniki do:

The impact of unevenness and instability of flue gas temperature on the technical condition of gas turbine blades

Błachnio J., Kułaszka A., Perczyński J.

Journal of KONES

2018

Vol. 25, No. 2

45--51

Gas turbines are used in the power sector, aviation, pump houses, and other technical systems. Such a broad range of application is associated with favourable indicators: high power, rather low weight per unit of power, significant efficiency, as well as high durability. All of these indicators greatly depend on the combustion chamber flue gas temperature. It is important for the flue gas temperature to be uniform around the turbine perimeter and stable over time. This condition is extremely important also in the case of frequent temperature variations associated, e.g. with a variable operating range of a manoeuvre aircraft turbojet engine. The paper analyses the causes for the unevenness and instability of combustion chamber flue gas temperature. The impact of the fuel quality, the technical condition of the fuel supply system, as well as the operating conditions of the combustion chamber-turbine assembly was shown. The issues regarding the presence of various types of damage to turbine elements, their blades in particular, were defined. The main cause behind the damage is the unevenness and instability of flue gas temperature, resulting in the presence of overheating, creeping, thermal fatigue, high-temperature corrosion of blade material. The forms of that damage, especially the first turbine stages, were presented. Blade material microstructure test results showed increased layer thickness, grain-size, and especially, adverse modification of the strengthening γ' phase in the temperature function. It was concluded periodic diagnostics of turbine blades with the optical method enables the non-invasive evaluation of their technical condition and drawing conclusions in terms of their durability.

Analysis of non-standard MiG-29 engine start procedures

Trelka M., Perczyński J., Bartoszewicz J.

Combustion Engines

2014

R. 53, nr 4

40--47

The paper describes alternative start procedures if regular MiG-29 engine start procedures are disturbed. The work presents ground engine start procedures with a turbine starter and an automatic start of both engines. A procedure algorithm has been presented in case malfunctions are detected depending on the level of the malfunction complexity. Example results have been included that come from the flight operating parameters recorder showing the versatility of events that may occur when starting the MiG-29 engines.

W artykule opisano metodykę postępowania w sytuacji zakłóceń normalnych procedur uruchamiania silników samolotu MiG-29. Przedstawiono w nim uruchamianie silników na ziemi za pomocą rozrusznika turbinowego oraz uruchamianie automatyczne obu silników samolotu. Zaprezentowano algorytm postępowania przy wykryciu awarii w zależności od stopnia jej skomplikowania. Zamieszczono także przykładowe wyniki pochodzące z rejestratora parametrów eksploatacyjnych samolotów, obrazujące różnorodność niepożądanych zdarzeń, które mogą wystąpić podczas uruchomienia silników samolotu MiG-29.