CPC F02C 9/18 (2013.01) [F02K 3/075 (2013.01); F02C 6/08 (2013.01); F04D 29/545 (2013.01); F05D 2220/323 (2013.01); F05D 2260/606 (2013.01); F05D 2270/101 (2013.01)] | 17 Claims |
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.
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