Use of an axial compressor (1) is also disclosed.
For assembly, the outer compressor airfoil assemblies (56) are moved toward the axial compressor rotor (46) and then inserted into the compressor case (50).
The axial compressor duct 34 guides air delivered from the front housing section 32 towards the axial compressor 24.
A tip turbine engine (10) provides an axial compressor (22) having a compressor case (50) from which extend radially inwardly a plurality of outer compressor airfoils (54).
By rotatably driving alternating stages of compressor blades in opposite directions, the efficiency of the axial compressor (22) is increased and/or the number of stages of compressor blades can be reduced.
The blades (1) for an axial flow compressor are, for example, stator blades for a gas turbine.
The Mamba has a 10-stage axial flow compressor supplying 6 combustion chambers and a two-stage turbine.
The invention relates to an annular flow duct for an axial flow compressor (12), in which blades 36, 44 of two blade rings 32, 42 are attached to the outer delimiting wall 22.
Blades (1) for an axial flow compressor are used by being disposed on a circle centered at an axis and are each provided with a base section (2) and a blade section (3).
The solution according to the invention relates to an axial untreated air compressor having an electrical drive.
…and improvement of centrifugal and axial-flow compressors.
Additionally, the design of the disclosed supercharger avoids the need for guide vanes between the axial compressor and the radial compressor.
The first compressor stage includes an axial compressor (4) while the second compressor stage includes a radial compressor (6).
The invention relates to a compressor (2) comprising a first compressor stage (4) and a downstream second compressor stage (6).
The present invention relates to an axial compressor for aircraft engines that comprises at least two stages arranged in series.
An Axial compressor has axial flow, the air or gas passes along the compressor shaft through rows of rotating and stationary impellers.
An axial compressor has axial flow, whereby the air or gas passes along the compressor shaft through rows of rotating and stationary blades.
In this manner, the axial compressor rotor (46) is driven in a direction opposite the direction of the outer compressor airfoils (54), thereby increasing the compression provided by the compressor without increasing the number of airfoils.
The present invention relates to an apparatus for preventing an axial-flow compressor from stalling by employing a casing treatment.
The air is supplied to these passages by an axial compressor comprising an air inlet zone (22), a compressor portion(25) and an annular diffuser (33) which leads into the passages (15).
Multistage axial compressor, within the scope of the CREATE test bench: LMFA.
The auxiliary turbine engine (80) has an axial compressor (100), a fan, a combustor, and an axial turbine.
With this configuration, a tip turbine engine can be more easily provided with variable compressor vanes for the axial compressor.
It is possible by means of said geometry to generate low-loss gap vortices, in order to increase the overall efficiency of an axial compressor comprising said compressor blades (10).
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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