Aircraft engine with stator having varying pitch
Номер патента: CA3198068A1
Опубликовано: 30-11-2023
Автор(ы): Karan ANAND
Принадлежит: Pratt and Whitney Canada Corp
Опубликовано: 30-11-2023
Автор(ы): Karan ANAND
Принадлежит: Pratt and Whitney Canada Corp
Реферат: An aircraft engine, has: an upstream stator having upstream stator vanes circumferentially distributed about a central axis; and a downstream stator having downstream stator vanes circumferentially distributed about the central axis, the downstream stator located downstream of the upstream stator relative to an airflow flowing within a core gaspath of the aircraft engine, a number of the upstream stator vanes being different than a number of the downstream stator vanes, major portions of leading edges of the downstream stator vanes circumferentially overlapped by the upstream stator vanes, the downstream stator vanes including: a first pair of circumferentially adjacent vanes of the downstream stator vanes spaced apart by a first pitch, and a second pair of circumferentially adjacent vanes of the downstream stator vanes spaced apart by a second pitch different than the first pitch.
Aircraft engine with stator having varying pitch
Номер патента: US20230382540A1. Автор: Karan ANAND. Владелец: Pratt and Whitney Canada Corp. Дата публикации: 2023-11-30.