An ejector comprises a primary nozzle having an annular wall forming part of an outer boundary of an exhaust portion of a primary flow path of a gas turbine engine. The annular wall has a downstream end defining a plurality of circumferentially distributed lobes. The ejector further comprises a secondary nozzle having an annular wall disposed about the primary nozzle, the primary nozzle and the secondary nozzle defining a secondary flow passage therebetween for channeling a secondary flow. The secondary nozzle defines a mixing zone downstream of an exit of the primary nozzle. A flow guide ring is mounted to the primary nozzle lobes. The ring has an aerodynamic surface extending from a leading edge to a trailing edge respectively disposed upstream and downstream of the exit of the primary nozzle. The aerodynamic surface of the ring is oriented to guide the high velocity primary flow into the mixing zone.

A method of manufacturing an exhaust mixing system may include fabricating an annular lobed mixer attachment flange. The fabricating may include forming a ring having a first leg and a second leg substantially perpendicular to the first leg, and forming a plurality of coupling fingers projecting from the second leg in a direction substantially parallel to the first leg.

A seal assembly includes a seal arc segment that defines first and second seal supports and radially inner and outer sides with the radially outer side including radially-extending sidewalls and a radially inner surface that joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. The seal assembly includes a carriage that defines first and second support members with the first support member supporting the seal arc segment in a first ramped interface and the second support member supporting the seal arc segment in a second ramped interface. The radially inner surface has a higher surface roughness than the radially extending sidewalls.

Aspects of the disclosure are directed an engine having a central longitudinal axis, comprising: a first case that at least partially defines a first flow path, a second case located radially outward of the first case, where the second case and the first case at least partially define a second flowpath, and an assembly that includes a first duct wall, a second duct wall, a finger seal disposed in a gap defined between the first duct wall and the second duct wall such that a first flow in the first flow path is isolated from a second flow in the second flowpath, a stop that projects from the first duct wall towards the second duct wall, and a diaphragm coupled to the second duct wall.

A blade member on a surface of which a groove structure is formed, wherein the groove structure includes a plurality of first groove structures, a plurality of second groove structures, and a third groove structure, the plurality of first groove structures are formed to extend in a first direction, the plurality of second groove structures are formed to extend in a second direction that is different from the first direction, the third groove structure extends along a third direction that is different from the first and second directions, and is formed between one first groove structure and one second groove structure.

A fan blade (1) has a front inflow edge (2) and a rear outflow edge (3). The fan blade (1) also has an at least partially wavy inflow edge (4), that forms a wave (W) having a specific three-dimensional waveform.

An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile having a succession of teeth and depressions. Along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.

A jet engine having a flow duct that is arranged in an engine nacelle and is delimited radially on the inside by a central body and radially on the outside by an outer nozzle wall is described. The free cross section of the flow duct is variable by an elastically embodied, radially variable wall of at least one of these components. The radially variable wall at least regionally has an at least approximately wavelike structure and is connected to at least one adjusting device having an adjusting unit. The variable wall of one of these components is variable in a radial direction at two defined control sections, at least one of which defines an axial wall end of the radially variable wall.

A bearing includes a bearing sleeve with a first portion and a second portion adjacent to the first portion. A bump foil extends along an inner face of the first portion of the bearing sleeve and a metal mesh extends along an inner face of the second portion of the bearing sleeve. A top foil extends along an inner face of the bump foil of the first portion and the metal mesh of the second portion.

The present application provides a gas turbine engine. The gas turbine engine may include a compressor and an inlet air system positioned upstream of the compressor. The inlet air system may include a wetted media pad for evaporative cooling. The wetted media pad may include a contoured configuration.