US 11,867,130 B2
Reversible bleed configuration
Peter Johansson, Trollhättan (SE)
Assigned to GKN Aerospace Sweden AB, Trollhättan (SE)
Appl. No. 17/609,824
Filed by GKN Aerospace Sweden AB, Trollhättan (SE)
PCT Filed May 7, 2020, PCT No. PCT/EP2020/062737
§ 371(c)(1), (2) Date Nov. 9, 2021,
PCT Pub. No. WO2020/229305, PCT Pub. Date Nov. 19, 2020.
Claims priority of application No. 1906638 (GB), filed on May 10, 2019.
Prior Publication US 2022/0220903 A1, Jul. 14, 2022
Int. Cl. F02C 9/18 (2006.01); F02C 6/08 (2006.01); F02K 3/075 (2006.01); F04D 29/54 (2006.01)
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
OG exemplary drawing
 
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.