Obiekt

Tytuł odmienny:

Analiza emisji tlenków azotu z wykorzystaniem oprogramowania GasTurb dla lotniczego silnika turbinowego F100-PW-229 ; Analiza emisji tlenków azotu z wykorzystaniem oprogramowania GasTurb dla lotniczego silnika turbinowego F100-PW-229

Współtwórca:

Aleksandra LUDWICZAK ; Aleksandra LUDWICZAK

Abstrakt:

The article discusses various aspects related to determining the composition of exhaust gases (i.e. nitrogen oxides) generated by a turbine aircraft engine. The paper highlights the problem of ozone depletion caused by toxic components of aircraft engine exhaust gases. The study is concerned with an engine used on the F-16 aircraft, i.e. F100-PW-229. GasTurb 12 software was used to calculate the engine’s operating parameters and to determine nitrogen oxides emission levels. The calculations were also performed analytically. The calculated thrust value was compared with data published in scientific articles (thrust of the engine). Characteristics of NOx emissions were obtained as a function of high-pressure rotor speed, temperature at the combustion chamber outlet, temperature downstream of the compressor, and engine thrust. The results obtained seem to correlate closely with data available in the literature.
; The article discusses various aspects related to determining the composition of exhaust gases (i.e. nitrogen oxides) generated by a turbine aircraft engine. The paper highlights the problem of ozone depletion caused by toxic components of aircraft engine exhaust gases. The study is concerned with an engine used on the F-16 aircraft, i.e. F100-PW-229. GasTurb 12 software was used to calculate the engine’s operating parameters and to determine nitrogen oxides emission levels. The calculations were also performed analytically. The calculated thrust value was compared with data published in scientific articles (thrust of the engine). Characteristics of NOx emissions were obtained as a function of high-pressure rotor speed, temperature at the combustion chamber outlet, temperature downstream of the compressor, and engine thrust. The results obtained seem to correlate closely with data available in the literature.

Miejsce wydania:

Warszawa
; Warszawa

Wydawca:

Wojskowa Akademia Techniczna ; Wojskowa Akademia Techniczna

Data utworzenia:

2010 r.0

Data złożenia:

2024-06-30 ; 2024-06-30

Data akceptacji:

2025-01-09 ; 2025-01-09

Data wydania:

2025-03-31 ; 2025-03-31

Rozmiar:

B5 ; B5

Identyfikator:

oai:ribes-88.man.poznan.pl:2728

Sygnatura:

doi:10.5604/01.3001.0055.0333 ; doi:10.5604/01.3001.0055.0333

ISSN elektroniczny:

2720-5266 ; 2720-5266

ISSN drukowany:

2081-5891 ; 2081-5891

Język:

angielski ; angielski

Licencja:

kliknij tutaj, żeby przejść ; kliknij tutaj, żeby przejść

Właściciel praw:

Wojskowa Akademia Techniczna ; Wojskowa Akademia Techniczna

Strona początkowa:

9 ; 9

Strona końcowa:

20 ; 20

Tom:

16 ; 16

Czasopismo:

PROMECH ; PROMECH

Słowa kluczowe:

aircraft turbine engine, combustion chamber, exhaust gases, emissions, nitrogen oxides ; aircraft turbine engine, combustion chamber, exhaust gases, emissions, nitrogen oxides