Each stage is formed from a fixed vane ring having a number of vanes and from a rotating blade ring having a number of blades.
The aim of the invention is to ensure an especially reliable cooling of the turbine vanes, especially the impeller vanes (12), while reducing the cooling air requirements.
The flowing water is accelerated in the distributor by the adjustable guide vanes and directed onto the blades.
Fan blades, compressor blades, blades and vanes, titanium, superalloys and stainless steels – the sheer variety of blades and metallic materials used in aircraft engines and stationary gas turbines is formidable.
The inner casing(9), the rotor shaft(4), the bearing(7), the stator vanes(31) and the moving blades(32) are integrally assembled, and the assembled members are inserted into the outer casing(2).
Proposed is a method for producing a rotor for a Francis turbine, which rotor comprises a rotor base, a rotor ring and rotor blades.
Software specially designed to design the internal cooling passages of aero gas turbine blades, vans and tip shrouds
Software specially designed to design the internal cooling passages of aero gas turbine blades, vans and tip shrouds
software specially designed to design the internal cooling passages of aero gas turbine blades, vans and tip shrouds
f. Software specially designed to design the internal cooling passages of aero gas turbine blades, vans and tip shrouds
The invention relates to a turbomachine having passive rotor blade adjustment.
The apparatus also includes moving paddles that urge the material through each tray.
This steam turbine aims at preventing such vibrations from causing damage to the moving blades.
At least one measuring element (6) is arranged in the area of the rotor blades, said measuring element being intended for measuring an electrical and/or magnetic field strength caused by charge distribution on the surface (5) of the rotor blades (4).
In the contact region, the power is transmitted between the moving blade ends (13).
The electrically conductive material of the rotor blades (4) is electrically connected to a reference potential.
Preferably one or both of the compressor (42) and motor (44) are positive displacement rotary sliding vane devices.
The invention relates to a rotor (10) comprising at least two stages (11, 12), each stage (11, 12) having a rotor disc (14, 15) with moving blades (17) that are fixed to said disc.
The turbine assembly (1) also includes blade controlling means (11) adapted to control the orientation of 10 the movable blades (5) between the active configuration and the passive configuration.
The surfaces of the stationary blades (6) and the surfaces of the moving blades (5) are treated at least partially thereof to suppress the surface roughness which might otherwise be increased by oxidation.
The protective layer is thus particularly suitable for parts of a gas turbine exposed to overheated flue gas, for example guide blades, moving blades or thermal shields.
The aim of the invention is to configure said turbine rotor blade assembly in such a way that turbine rotor blades (2) can be inserted at helix angles which are greater than currently achieved.
As a result of the casing being processed in this way, the efficiency of the moving-blade wheel is optimized and the surge margin is improved.
Said rotor base (11) is made of an MMC material while the impeller blades form an integral part of the rotor.
It was determined that all 58 blades in the compressor turbine (CT) section were broken.
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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