The thin skin (14) may be bonded to the inner spar structure of the turbine blade airfoil by a transient liquid phase bonding process.
The axial compressor has a two-stage guide-blade cascade (8) at the outlet-side end (5) of the rotor (4).
A turbine blade-cascade end wall which can reduce secondary flow loss incident to cross-flow while reducing the cross-flow, and can improve turbine performance.
According to the invention, the blade (4) comprises a blade body (5) and a blade root (6).
Each of the plurality of vane stages includes a vane guide and at least one window axially aligned with each of the vane guides.
The inventive rotating blade (10) is provided with a front of blade (11) and a footing of blade (12) connected thereto.
The vane element (101) is mounted to the vane platform (102) and the vane root (103) is mounted to the annular rail (105).
Each vane structure includes a curved, axial vane segment extending axially from the shroud.
A blade (44) is composed of a blade body (51) and a blade cover (61).
The vane blank is inspected for material inconsistencies, and material is removed from the vane blank to form a desired guide vane in accordance with one of the plurality of vane classes.
The stator includes a first stator valve face, a second stator valve surface, and a plurality of function compartments opening into the stator valve surfaces.
The invention relates to a gas turbine vane, especially a vane pertaining to an aircraft engine, comprising a blade (11) and a vane footing (12).
The radially outboard portion of the vanes simultaneously include a gradual increase in vane stagger angle, vane camber angle and vane chord.
The rotor includes a first rotor valve surface in communication with the first stator valve surface, and a second rotor valve surface in communication with the second stator valve surface.
The blade shell (7) receives the vane (61) in positive engagement and can be separated from the blade (61).
A cooling fan includes an impeller which comprises a plurality of radially extending blades, each of which includes a blade hub, a blade tip and a blade midspan approximately midway between the hub and the tip.
The blades (24) are attached to the rotatable disk (29), and each one of the plurality of blades has a blade root and a blade tip (25) disposed opposite said blade root.
The main vane is supported by a predetermined member via a vane shaft which is positioned on the vane chord of the main vane and extends in the vane length direction, so as to rotate about the vane shaft.
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,
Traduction Translation Traducción Übersetzung Tradução Traduzione Traducere Vertaling Tłumaczenie Mετάφραση Oversættelse Översättning Käännös Aistriúchán Traduzzjoni Prevajanje Vertimas Tõlge Preklad Fordítás Tulkojumi Превод Překlad Prijevod 翻訳 번역 翻译 Перевод