Abstract: The invention relates to a propelling nozzle for a turbofan engine on a supersonic aircraft, the propelling nozzle including: a propelling nozzle wall, a duct, which is radially outwardly bounded by the propelling nozzle wall, and a central body arranged in the duct. According to the invention, the central body is connected to the propelling nozzle wall via at least one brace.

Abstract: An exhaust nozzle of a gas turbine engine includes: a nozzle wall, a centerbody arranged in a flow channel, and two struts connecting the centerbody to the wall. One of the struts is connected to the wall by a coupling arrangement that includes two first brackets and a third bracket, the brackets being spaced in an axial direction and being connected either directly to the wall or to a sliding element that is arranged in a displaceable manner in the wall. The brackets each have a first, highest stiffness in a first direction and smaller stiffnesses in a second and third direction. The brackets are oriented such that with the two first brackets, the first direction is aligned with a circumferential direction of the nozzle and that with the third bracket, the first direction is aligned with the axial direction of the nozzle.

Abstract: Aspects of the disclosure regard an exhaust nozzle of a gas turbine engine which includes an outer nozzle wall, a flow channel, a centerbody arranged in the flow channel, at least two struts connecting the centerbody to the nozzle wall, a thrust reverser unit, and a plurality of actuators, wherein each actuator is associated with a strut for displacing the strut in the axial direction. The struts are connected to a structure of the outer nozzle wall that forms part of the thrust reverser unit. For allowing axial relative movement between the struts and the outer nozzle wall, each strut includes a sliding element extending radially from the radial outer end of the strut, wherein the sliding element is arranged in a receiving slot that extends in the axial direction in the nozzle wall. It is provided that the sliding element comprises an interaction structure that interacts with one of the actuators for effecting relative axial movement between the strut and the nozzle wall.

Abstract: Aspects of the disclosure regard an exhaust nozzle for a gas turbine engine that includes an outer nozzle wall, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, and at least two struts connecting the centerbody to the nozzle wall. One of the struts is connected to the nozzle wall by a first connection, the first connection constraining movement of the strut relative to the nozzle wall in the radial direction and in the circumferential direction. The at least one other strut is connected to the nozzle wall by a second connection, the second connection constraining movement of the strut relative to the nozzle wall in the circumferential direction but allowing movement of the strut relative to the nozzle wall in the radial direction.

Abstract: An exhaust nozzle of a gas turbine engine includes an outer nozzle wall, a centerbody arranged in a flow channel, and two struts connecting the centerbody to the wall. A first strut is connected to the wall by a first connection allowing movement of the strut relative to the nozzle wall in the axial direction. Another strut is connected to the wall by a second connection allowing movement of the strut relative to the wall in the radial and axial directions. The second connection is formed by a sliding element and a receiving slot, wherein the sliding element includes an interaction zone interacting with an actuator for axial movement. The interaction zone has a radial length such that the interaction between the actuator and the interaction zone is maintained when the sliding element is moved in the radial direction by radial thermal expansion of the strut and/or the centerbody.

Abstract: An exhaust nozzle of a gas turbine engine which includes a nozzle wall, the nozzle wall including an upstream, fixed structure and a downstream, translatable structure that is translatable relative to the fixed structure, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, at least one strut connecting the centerbody to the nozzle wall, a thrust reverser unit that comprises blocking doors, a first actuation system for deployment of the blocking doors into a deployed position for thrust reversal, and a second actuation system for translating the translatable structure between a stowed, upstream position and a fully deployed, downstream position. It is provided that the at least one strut is connected to the fixed structure, that the blocking doors are connected to the translatable structure, and that the first actuation system and the second actuation system are independent actuation systems.

Abstract: An exhaust nozzle of a gas turbine engine which includes an outer nozzle wall, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, and exactly one strut connecting the centerbody to the nozzle wall. The strut is connected to the nozzle wall by means of a connecting structure that is displaceable in the axial direction of the outer nozzle wall. At least one actuator is provided interacting with the connecting structure or the outer nozzle wall for displacing the strut in the axial direction.

Abstract: An engine nacelle for a turbofan engine, having a nacelle wall and an engine inlet, wherein the nacelle wall has a stationary downstream section and an upstream section that is displaceable in the axial direction, and the displaceable upstream section is displaceable between a first upstream position and a second downstream position. A ring-shaped seal is provided, formed between the stationary section and the displaceable section of the nacelle wall, wherein, in the first position of the displaceable section, the engine nacelle forms a ring-shaped additional flow channel that extends from the outer side of the nacelle wall to the engine inlet and via which ambient air can flow into the engine inlet, and the ring-shaped additional flow channel is closed in the second position of the displaceable section, wherein the stationary section, the ring-shaped seal and the displaceable section adjoin each other.

Abstract: The invention regards an asymmetric submerged air intake in a surface of a structure, wherein the air intake includes a submerged ramp extending from the surface. The ramp has a front end, a rear end, a ramp floor and two ramp side walls. The ramp floor is inclined with respect to the surface. At the rear end an entrance to an internal duct of the structure is provided. It is provided that one of the ramp side walls is a straight wall extending straight in the longitudinal direction of the ramp and that the other of the ramp side walls is a curved wall that diverges from the straight wall along the length of the ramp.

Abstract: An exhaust nozzle of a gas turbine engine which includes an outer nozzle wall, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, and exactly one strut connecting the centerbody to the nozzle wall. The strut is connected to the nozzle wall by means of a connecting structure that is displaceable in the axial direction of the outer nozzle wall. At least one actuator is provided interacting with the connecting structure or the outer nozzle wall for displacing the strut in the axial direction.

Abstract: The invention regards an asymmetric submerged air intake in a surface of a structure, wherein the air intake includes a submerged ramp extending from the surface. The ramp has a front end, a rear end, a ramp floor and two ramp side walls. The ramp floor is inclined with respect to the surface. At the rear end an entrance to an internal duct of the structure is provided. It is provided that one of the ramp side walls is a straight wall extending straight in the longitudinal direction of the ramp and that the other of the ramp side walls is a curved wall that diverges from the straight wall along the length of the ramp.

Abstract: Aspects of the disclosure regard an exhaust nozzle for a gas turbine engine that includes an outer nozzle wall, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, and at least two struts connecting the centerbody to the nozzle wall. One of the struts is connected to the nozzle wall by a first connection, the first connection constraining movement of the strut relative to the nozzle wall in the radial direction and in the circumferential direction. The at least one other strut is connected to the nozzle wall by a second connection, the second connection constraining movement of the strut relative to the nozzle wall in the circumferential direction but allowing movement of the strut relative to the nozzle wall in the radial direction.

Abstract: An exhaust nozzle of a gas turbine engine which includes a nozzle wall, the nozzle wall including an upstream, fixed structure and a downstream, translatable structure that is translatable relative to the fixed structure, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, at least one strut connecting the centerbody to the nozzle wall, a thrust reverser unit that comprises blocking doors, a first actuation system for deployment of the blocking doors into a deployed position for thrust reversal, and a second actuation system for translating the translatable structure between a stowed, upstream position and a fully deployed, downstream position. It is provided that the at least one strut is connected to the fixed structure, that the blocking doors are connected to the translatable structure, and that the first actuation system and the second actuation system are independent actuation systems.

Abstract: Aspects of the disclosure regard an exhaust nozzle of a gas turbine engine which includes an outer nozzle wall, a flow channel, a centerbody arranged in the flow channel, at least two struts connecting the centerbody to the nozzle wall, a thrust reverser unit, and a plurality of actuators, wherein each actuator is associated with a strut for displacing the strut in the axial direction. The struts are connected to a structure of the outer nozzle wall that forms part of the thrust reverser unit. For allowing axial relative movement between the struts and the outer nozzle wall, each strut includes a sliding element extending radially from the radial outer end of the strut, wherein the sliding element is arranged in a receiving slot that extends in the axial direction in the nozzle wall. It is provided that the sliding element comprises an interaction structure that interacts with one of the actuators for effecting relative axial movement between the strut and the nozzle wall.

Abstract: An exhaust nozzle of a gas turbine engine includes: a nozzle wall, a centerbody arranged in a flow channel, and two struts connecting the centerbody to the wall. One of the struts is connected to the wall by a coupling arrangement that includes two first brackets and a third bracket, the brackets being spaced in an axial direction and being connected either directly to the wall or to a sliding element that is arranged in a displaceable manner in the wall. The brackets each have a first, highest stiffness in a first direction and smaller stiffnesses in a second and third direction. The brackets are oriented such that with the two first brackets, the first direction is aligned with a circumferential direction of the nozzle and that with the third bracket, the first direction is aligned with the axial direction of the nozzle.

Abstract: An exhaust nozzle of a gas turbine engine includes an outer nozzle wall, a centerbody arranged in a flow channel, and two struts connecting the centerbody to the wall. A first strut is connected to the wall by a first connection allowing movement of the strut relative to the nozzle wall in the axial direction. Another strut is connected to the wall by a second connection allowing movement of the strut relative to the wall in the radial and axial directions. The second connection is formed by a sliding element and a receiving slot, wherein the sliding element includes an interaction zone interacting with an actuator for axial movement. The interaction zone has a radial length such that the interaction between the actuator and the interaction zone is maintained when the sliding element is moved in the radial direction by radial thermal expansion of the strut and/or the centerbody.

Abstract: There is provided a jet engine air inlet arrangement having a front annular casing arrangement and a heating pipe arrangement. The heating pipe arrangement is supported onto an annular internal bulkhead, wherein the annular internal bulkhead provides a back wall to the cavity. The annular internal bulkhead is fabricated from deformed metal sheet, and includes a plurality of radially disposed stiffening projections and recesses in the back wall, and wherein the annular internal bulkhead includes inner and outer circumferential flanges that engage onto inside surfaces of the front annular casing arrangement behind the back wall. The plurality of radially disposed stiffening projections and recesses result in the flanges being disposed at a distance of more than 60 mm behind the plurality of radially disposed stiffening projections and recesses.

Abstract: A mixer assembly group for a turbofan engine, having a primary flow channel extending along a central axis of the turbofan engine and a secondary flow channel. The mixer assembly group includes a mixer for guiding a first fluid flow from the primary flow channel and a second fluid flow from the secondary flow channel in the direction of an exhaust of the turbofan engine, as well as for intermixing the first and second fluid flows, and a connection appliance, which has at least one connection component that is fixated at the mixer and by means of which the mixer assembly group is to be fixated at two different first and second engine components of the turbofan engine, with are subject to operating temperatures of different heights during operation of the turbofan engine.

Abstract: The invention relates to a propelling nozzle for a turbofan engine on a supersonic aircraft, the propelling nozzle comprising: a propelling nozzle wall (20), a duct (15), which is radially outwardly bounded by the propelling nozzle wall (20), and a central body (5) arranged in the duct (15). According to the invention, the central body (5) is connected to the propelling nozzle wall (20) via at least one brace (31, 32).

Abstract: It is provided a mixer for an engine, that for the mixing of fluid flows from a primary flow channel and a secondary flow channel of the engine, respectively has multiple first and second guide elements that alternate along a circumferential direction and extend along a central axis, wherein the first guide elements are formed in a diffusor-like manner with at least one radially outwardly extending section, and the second guide elements are formed in a nozzle-like manner with at least one radially inwardly extending section, and the mixer is made of a composite material with at least two separate material layers. The at least two material layers are arranged with their edges along the central axis in an overlapping manner and/or edge to edge, and namely in an area of the mixer in which the first and second guide elements are provided.