The disclosure relates to a nozzle (12) for cooling a jet engine (2) for maintenance, wherein the jet engine (2) comprises an exhaust channel (21) for the exit of exhaust gases of the jet engine (2), the nozzle (12) comprises a suction adapter (121) having a round shape adapted to be connected in sealed manner to the exhaust channel (21) for sucking air from the exhaust channel (21), and a suction channel (122) in fluid connection with the suction adapter (121) for sucking air from the suction adapter (121), wherein the suction channel (122) is arranged to be connected to an air suction device (13).

The disclosure relates also to an apparatus (1) for cooling a jet engine (2) for maintenance and a method for maintenance of a jet engine (2).

An apparatus comprising a housing, seal, and energy storing device. The housing is coupled to a structure in an exhaust system of an aircraft. The structure is positioned relative to a surface within the exhaust system such that a gap is present between the surface and structure. The seal has an end positioned in contact with the surface to reduce a flow of exhaust through the gap and is coupled to the housing such that the seal extends within the housing. The energy storing device is coupled to the housing and engaged with the seal to allow the seal to translate in a first direction relative to the housing when the gap increases and in a second direction opposite the first direction relative to the housing when the gap decreases such that the seal continues to reduce the flow of exhaust through the gap as the gap changes in size.

Disclosed is an exhaust nozzle for a gas turbine engine, the exhaust nozzle comprising an outer frame extending along a longitudinal direction, a convergent petal pivotably attached to the frame and extending axially downstream and radially inward from the pivot, radially within the frame, and a sealing hinge arrangement between an upstream member and a downstream member of the exhaust nozzle. One of the upstream member or the downstream member defines a cylindrical socket having an opening along a cylinder axis which receives a corresponding cylindrical hinge element the other of the downstream member or upstream member, where the upstream member is defined by the frame and the downstream member is the convergent petal; or the exhaust nozzle further comprises a divergent petal downstream of the convergent petal and pivotably attached to the convergent petal, the upstream member being the convergent petal and the downstream member being the divergent petal.

A coupling adapted for use with a gas turbine engine includes a first flange, a second flange, and a seal assembly. The first flange is coupled with an exhaust end of the gas turbine engine. The second flange is coupled with ducting downstream of the gas turbine engine. The seal assembly extends between the first flange and the second flange and is configured to block the gases from passing radially between the first flange and the second flange.

Isolation seals for gas turbine engines are described. The isolation seals include an elastomer body configured to be attached to a first case structure at a first end and a second case structure at a second end and a seal shield configured to be attached to the first case structure, the seal shield having a shielding member configured to define a protected space between the shielding member and the elastomer body.

A seal assembly can accommodate deflection between two components through a cartridge that is slidingly engaged with a slide plate.

Methods and apparatus for sealing variable area fan nozzles of jet engines are disclosed. An apparatus in accordance with the teachings of this disclosure includes a frame and a seal to be coupled to the frame. The seal to enclose petals of a variable area fan nozzle to substantially prevent airflow between the petals.

A variable area fan nozzle for a turbofan aircraft engine includes a first structure defining a forward portion of a bypass duct of the turbofan aircraft engine and a second structure defining an aft portion of the bypass duct. The second structure is movable relative to the first structure between a deployed position where a porting flow passage defined between the forward portion of the bypass duct and the aft portion of the bypass duct is open, and a stowed portion where the porting flow passage is closed. The movable second structure comprises a vane and a slat attached to the vane and disposed forward of the vane. The porting flow passage extends between the slat and the vane when the second structure is in the deployed position.

Isolation seals for gas turbine engines are described. The isolation seals include an elastomer body configured to be attached to a first case structure at a first end and a second case structure at a second end and a seal shield configured to be attached to the first case structure, the seal shield having a shielding member configured to define a protected space between the shielding member and the elastomer body.

Isolation seals for gas turbine engines are described. The isolation seals include a first interface member configured to be fixedly attached to a first case structure, the first interface member being a full-hoop structure, a housing configured to be mounted to a second case structure, a connector pin arranged within the housing and moveable relative to the housing, and a second interface member located on an end of the connector pin, the second interface member being a full-hoop structure. The first interface member and the second interface member are engageable to form a seal therebetween.