Abstract: A gas turbine engine comprising at least one radially extending bleed passage in fluid communication with at least one generally circumferentially extending plenum. A plenum has an upstream end in fluid communication with a bleed passage and an outlet for releasing air from the plenum. A plenum further comprises a downstream surface defining a downstream closed end of the plenum and the downstream surface of one or more plenum is/are provided with an outwardly extending projection extending into the plenum.

Abstract: The present invention relates to a support structure (16) for a gas turbine engine (1). The support structure (16) has an axial extension in an axial direction (A) and a circumferential extension in a circumferential direction (C). Moreover, the support structure (16) comprises a plurality of tubular members (18, 20) of a first material type arranged in sequence in the circumferential direction (C). Each tubular member (18, 20) at least partially delimits a flow guiding passage extending at least partially in the axial direction (A). The support structure (16) comprises a leading portion (22) and a trailing portion (24) in the axial direction (A). Furthermore, the support structure (16) comprises a leading edge member (26) of a second material type, the leading edge member (26) being located at the leading portion (22). At least two of the tubular members (18, 20) are fixedly attached to a leading edge member (26).

Abstract: The present invention relates to a support structure (16) for a gas turbine engine (1). The support structure (16) has an axial extension in an axial direction (A) and a circumferential extension in a circumferential direction (C). Moreover, the support structure (16) comprises a plurality of tubular members (18, 20) of a first material type arranged in sequence in the circumferential direction (C). Each tubular member (18, 20) at least partially delimits a flow guiding passage extending at least partially in the axial direction (A). The support structure (16) comprises a leading portion (22) and a trailing portion (24) in the axial direction (A). Furthermore, the support structure (16) comprises a leading edge member (26) of a second material type, the leading edge member (26) being located at the leading portion (22). At least two of the tubular members (18, 20) are fixedly attached to a leading edge member (26).

Abstract: The invention relates to a device (20) for moving at least one moveable element (19) in a gas turbine engine (1) between a first and a second position. The device includes a linkage (21) that connects a pivotable annular member (18) with the moveable element (19) in such a way that the movement of the moveable element (19) between the two positions is accomplished when the annular member (18) is pivoted. The linkage (21) has a link member (22) connected to the moveable element (19) via a first articulation joint (23). The device also has a support member (24) that supports the link member (22) at a distance from the first articulation joint.

Abstract: The invention relates to a device (20) for moving at least one moveable element (19) in a gas turbine engine (1) between a first and a second position. The device includes a linkage (21) that connects a pivotable annular member (18) with the moveable element (19) in such a way that the movement of the moveable element (19) between the two positions is accomplished when the annular member (18) is pivoted. The linkage (21) has a link member (22) connected to the moveable element (19) via a first articulation joint (23). The device also has a support member (24) that supports the link member (22) at a distance from the first articulation joint.