Patent ID: 11867130
Assignee: GKN AEROSPACE SWEDEN AB
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A gas turbine engine arrangement, comprising:
a gas turbine engine including a bypass channel and an engine core that includes a transition duct arranged to channel air towards one or more compressors and an air flow passage extending from the bypass channel through the core and towards the transition duct;
a first port arranged to fluidly connect the transition duct and the airflow passage and configured to communicate air from the transition duct to the bypass channel; and
a second port arranged to fluidly connect the transition duct and the airflow passage and configured to communicate air from the bypass channel to the transition duct;
wherein the first port and second port are integrally formed in a single circumferentially extending body, or a pair of circumferentially extending bodies arranged to abut one another, wherein the single circumferentially extending body, or the pair of circumferentially extending bodies, each include either a ring or a torus.