A variable stator vane assembly for a gas turbine engine includes a variable stator vane and a non-structural fairing on the variable stator vane.
A stator vane for a compressor is described.
A stator vane has an outer platform with a notch.
A wear liner for a stator vane includes a shaped member, comprising a U-shaped portion that receives a foot of a stator vane.
A variable stator vane is arranged upstream from the high pressure compressor.
The seal is formed within a trench cavity (150) defined between a rotor blade (126) and a stator blade (128).
The turbine or motor may comprise a stator (30) comprising at least one stator blade (20) extending within the fluid passage.
Thus, the area of elastic contact between the elastic contact portion (28) and the inner surfaces (21, 22) of the blade members (17, 18) is increased, enabling a reliable suppression of flattering in a stator blade.
The stator blades have stator blade bodies and outer shrouds.
A stator blade (10) of a compressor comprises a seal mechanism (12) for sealing airtight between the upstream side of the radial inner end and the outer surface of a rotary body.
The platforms are provided with flanges on opposed ends thereof, and the flanges are fastened to corresponding flanges of an adjacent one of the plurality of stator vanes.
In a further embodiment of any of the foregoing stator vane embodiments, the vane is a cantilevered vane.
The stator vanes are arranged circumferentially around the axis, and include a first stator vane that extends radially into the aperture and is fastened to the first vane platform.
Provided is a gas turbine wherein an axial space between a stator vane and a rotor vane and the end faces of the vanes can be effectively cooled.
The vane segments are fastened together and form an adjustable stator vane that pivots about a variable vane axis.
An adjustable stator vane for a turbine engine includes a shaft, a flange and a stator vane body that pivots about a variable vane axis.
The present invention provides a nonlinearly stacked low noise turbofan stator vane (11).
In a further embodiment of the foregoing stator vane assembly embodiment, the circumferential edge includes a portion that is aligned with an axis of the turbomachine.
A turbine engine stator vane is provided that rotates about an axis, and includes an airfoil, a flange and a shaft.
A stator vane for a gas turbine engine includes a first platform and a second platform radially spaced apart from one another.
The purpose of the present invention is to provide a low aspect ratio turbine stator vane capable of reducing lateral wall loss and improving stage efficiency.
A trough (27) adjacent the outlet directs cooling air from the outlet towards a downstream stator vane to cool the stator vane.
A flow directing element (such as a rotor blade (34) or a stator vane (44)) for the turbine section (16) of a rotary machine is disclosed.
A stator vane assembly for a gas turbine engine is disclosed and includes a plurality of vanes received within channels defined within a case.
The housing has an opening adapted to receive an actuator assembly (220) that includes a central stationary shaft (310) having at least one stator vane (312a, 312b).
Requêtes fréquentes français :1-200, -1k, -2k, -3k, -4k, -5k, -7k, -10k, -20k, -40k, -100k, -200k, -500k, -1000k,
Requêtes fréquentes anglais :1-200, -1k, -2k, -3k, -4k, -5k, -7k, -10k, -20k, -40k, -100k, -200k, -500k, -1000k,
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