GAS TURBINE ENGINE COMBUSTOR WITH OPENINGS

GAS TURBINE ENGINE COMBUSTOR WITH OPENINGS

A gas turbine engine (10) includes a compressor section (12), a combustor section (14), and a turbine section (16) in fore-to-aft serial flow arrangement and defines an engine centerline (20). The combustor section (14) includes a combustor liner (40, 42) at least partially defining a combustor cham...

Ausführliche Beschreibung

Gespeichert in:
Bibliographische Detailangaben
Hauptverfasser: PAL, Sibtosh, BADHUK, Pabitra, SINHA ROY, Arijit, NAIK, Pradeep, VUKANTI, Perumallu, PATRA, Ajoy, PANDURI, Bhavya Naidu, BUCARO, Michael, CHIRANTHAN, R Narasimha, CHAKRABORTY, Aritra
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
BLASTING
COMBUSTION APPARATUS
COMBUSTION PROCESSES
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
Online-Zugang:Volltext bestellen
Tags: Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
Beschreibung
Zusammenfassung:A gas turbine engine (10) includes a compressor section (12), a combustor section (14), and a turbine section (16) in fore-to-aft serial flow arrangement and defines an engine centerline (20). The combustor section (14) includes a combustor liner (40, 42) at least partially defining a combustor chamber (50), and a dome wall (70) coupled to the combustor liner (40, 42), and defining a forward end of the combustion chamber (50). A first fuel nozzle (72) is located on the dome wall (70) and fluidly coupled to the combustion chamber (50). A first set of compressed air openings (76a) emit compressed air into the combustion chamber (50) along a first flow path (F) and a second set of compressed air openings (76b) emit compressed air into the combustion chamber (50) along a second flow path (F). The first and second flow paths (F) intersect at an intersection point (94) to form a sheet of air (S).