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Influence of Thermal Inertia on Dynamic Characteristics of Gas Turbine Impeller Components. [PDF]
Entropy (Basel)Liu Y, Jia Y, Liu Y.
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Performance and cost-benefit analysis of an integrated earth-air heat exchanger and air handling unit system. [PDF]
Sci RepAli NB +7 more
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Deformation investigation of electromagnetic diaphragm pump rubber diaphragm. [PDF]
PLoS OneLiao Y, Wang H, Chen B, Liu Y.
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Aeronautical Quarterly, 1949
It is fairly generally known that if, at any fixed speed of a compressor, either axial or centrifugal, the flow is reduced by throttling the outlet, then a point is eventually reached at which a complete breakdown of the air flow occurs and in most cases an actual flow reversal through the compressor takes place.
H. Pearson, T. Bowmer
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It is fairly generally known that if, at any fixed speed of a compressor, either axial or centrifugal, the flow is reduced by throttling the outlet, then a point is eventually reached at which a complete breakdown of the air flow occurs and in most cases an actual flow reversal through the compressor takes place.
H. Pearson, T. Bowmer
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The Journal of the Royal Aeronautical Society, 1959
The note in the July Journal by H. Pearson and A. B. McKenzie (p. 415) shows that the flow into an axial compressor is nearly at a constant velocity at all points in the entry plane; and that if a wake of low energy air is fed into it, the compressor reduces the static pressure locally in this wake, in such a way as to tend to preserve constant ...
H. Pearson, A. B. McKenzie
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The note in the July Journal by H. Pearson and A. B. McKenzie (p. 415) shows that the flow into an axial compressor is nearly at a constant velocity at all points in the entry plane; and that if a wake of low energy air is fed into it, the compressor reduces the static pressure locally in this wake, in such a way as to tend to preserve constant ...
H. Pearson, A. B. McKenzie
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The Journal of the Royal Aeronautical Society, 1959
I would like to point out a possible ambiguity in the paper by J. Dunham, in the October issue of the Journal. When considering the relative stresses in similar steel and aluminium alloy blades the author states that for blades “ doing the same duty ” the maximum stress in the steel blade is three times that in the aluminium type. This would seem to be
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I would like to point out a possible ambiguity in the paper by J. Dunham, in the October issue of the Journal. When considering the relative stresses in similar steel and aluminium alloy blades the author states that for blades “ doing the same duty ” the maximum stress in the steel blade is three times that in the aluminium type. This would seem to be
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Supercharging with an Axial Compressor
SAE Technical Paper Series, 1987<div class="htmlview paragraph">MANY MULTI STAGE pressure charging techniques are being applied to spark ignition engines in the quest for maximum power and Fuel efficiency with minimum weight, space and cost. This paper describes the experience gained by Lotus Engineering from the application of an axial compressor as the first stage of a ...
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1981
The axial flow compressor is the second type of dynamic compressor, whose general nature and capabilities were introduced in section 1.3. It absorbs energy from an external power source, raising the pressure of a continuous flow of working fluid by means of its blading geometry and motion.
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The axial flow compressor is the second type of dynamic compressor, whose general nature and capabilities were introduced in section 1.3. It absorbs energy from an external power source, raising the pressure of a continuous flow of working fluid by means of its blading geometry and motion.
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Rotating Stall in Axial Flow Compressors
Journal of the Aeronautical Sciences, 1957The classical theories of linearized aerodynamics yields a complete description of the flow field due to the rotating stall in a two-dimensional cascade of airfoils, when the extension of the stalled region is small. The corresponding physical scheme can be used for larger stalled regions, without the limitations of the linearizing assumptions, if no ...
Fabri, Jean, Siestrunck, Raymond
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Axial Compressors and Turbines
2012With the definition of the work coefficient in (6.4a) and (6.4b), we can now write from (4.22a) to (4.22d) the nondimensional azimuthal velocity component expressions as follows: $$ \frac{{{{c}_{\rm{u1}}}}}{u} = \left( {1 - \hat{r}} \right) - \frac{\Psi}{4} $$ $$ \frac{{{{c}_{\rm{u2}}}}}{u} = \left( {1 - \hat{r}} \right) + \frac{\Psi}{4} $$
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