ASYMMETRIC INLET PARTICLE SEPARATOR FOR GAS TURBINE ENGINE

An asymmetric inlet particle separator (200) for a gas turbine engine (100) includes an inlet (202) having a first cross-sectional shape, and a duct (204) downstream of the inlet. The duct includes a bend (238) upstream from a splitter (226), a scavenge branch (228) and an engine airflow branch (230...

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Bibliographische Detailangaben
Hauptverfasser:	JUDD, Zedic, SHEORAN, Yogendra, TUCKER, Bradley, HOLLINGSHEAD, Douglas, PEARSON, John
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	An asymmetric inlet particle separator (200) for a gas turbine engine (100) includes an inlet (202) having a first cross-sectional shape, and a duct (204) downstream of the inlet. The duct includes a bend (238) upstream from a splitter (226), a scavenge branch (228) and an engine airflow branch (230). The splitter is outside of a line of sight from the inlet and the splitter separates the scavenge branch from the engine airflow branch. The asymmetric inlet particle separator includes an annulus (206) downstream of the engine airflow branch configured to be coupled to the gas turbine engine. The annulus has a second cross-sectional shape, and the engine airflow branch transitions from the first cross-sectional shape to the second cross-sectional shape.