A gas turbine engine is defined wherein the inlet guide vanes leading into a core engine flow path are sized and positioned such that flow paths positioned circumferentially intermediate the vane are sufficiently large that a hydraulic diameter of greater than or equal to about 1.5 is achieved. This will likely reduce the detrimental effect of icing.
Anti-icing core inlet stator assembly for a gas turbine engine
19.07.2022
Patent
Elektronische Ressource
Englisch
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