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- Q17011775 subject Q7153753.
- Q17011775 subject Q8875428.
- Q17011775 abstract "For any kind of turbomachine operation at very high ranges of speed, it is mandatory to bear substantial compressibility effects. High compressibility effects lead to high variation in density of the flow medium. Although high Mach number signifies high mass flow per unit area as well as high pressure ratios across the stage, but excessive increase can result in shock wave generation which decreases the efficiency of the Turbo-machine owing to entropy generation. As we are dealing with compressors which majorly concerns with pressure variation across the stage, so for that analysis, the empirical formulation to be used isp2/ p1 = 1+(Cp*γ*M2/2)where p = Static pressure Cp = Pressure drop or rise coefficient γ = Specific heat of gas M = Mach numberFor high subsonic flows, the Critical Mach number (M1cr) is a characteristic value of considerable importance. It is the Mach number for which sonic conditions are reached locally in flow field i.e. there will be no shocks. So as to minimize shock losses and profile losses, the turbo-machine should be operated below M1cr. The Mach number range can also be extended beyond M1cr by carefully designing blade shapes.As the relative Mach number increases, so does the value of Cp, leading to an increase in static pressure in compressors, and, in turn, rises in the boundary-layer thickness and losses. So for a given incidence, off-design losses will increase with increasing Mach number and there will be an drastic increase close to a critical Mach number, resulting in shock waves inside passage.".
- Q17011775 thumbnail Shock_loss_coefficient_vs_Mach_number.png?width=300.
- Q17011775 wikiPageExternalLink ETD1.PDF.
- Q17011775 wikiPageExternalLink 9780471855460.
- Q17011775 wikiPageWikiLink Q1048872.
- Q17011775 wikiPageWikiLink Q1058834.
- Q17011775 wikiPageWikiLink Q130760.
- Q17011775 wikiPageWikiLink Q160669.
- Q17011775 wikiPageWikiLink Q1660471.
- Q17011775 wikiPageWikiLink Q17155089.
- Q17011775 wikiPageWikiLink Q1777346.
- Q17011775 wikiPageWikiLink Q178898.
- Q17011775 wikiPageWikiLink Q189452.
- Q17011775 wikiPageWikiLink Q190132.
- Q17011775 wikiPageWikiLink Q190688.
- Q17011775 wikiPageWikiLink Q193010.
- Q17011775 wikiPageWikiLink Q5462112.
- Q17011775 wikiPageWikiLink Q627111.
- Q17011775 wikiPageWikiLink Q7075180.
- Q17011775 wikiPageWikiLink Q7153753.
- Q17011775 wikiPageWikiLink Q7241680.
- Q17011775 wikiPageWikiLink Q752193.
- Q17011775 wikiPageWikiLink Q8875428.
- Q17011775 wikiPageWikiLink Q975211.
- Q17011775 comment "For any kind of turbomachine operation at very high ranges of speed, it is mandatory to bear substantial compressibility effects. High compressibility effects lead to high variation in density of the flow medium. Although high Mach number signifies high mass flow per unit area as well as high pressure ratios across the stage, but excessive increase can result in shock wave generation which decreases the efficiency of the Turbo-machine owing to entropy generation.".
- Q17011775 label "Effects of Mach number and shock losses in turbomachines".
- Q17011775 depiction Shock_loss_coefficient_vs_Mach_number.png.