An Experimental High-Temperature Turbine ( No . 1 : 26 ) • Part I . mThe Cooling Performance of a Set of Extruded Air-Cooled Turbine Blades
Cooling characteristics are given in terms of the variation of average blade temperature at mid-span with cooling-flow rate, Reynolds number, gas/cooling-air absolute temperature ratio, and, for the rotor, gas-stream incidence. Chordwise and spanwise variations of blade temperature are also presented. Measured pressure-drop characteristics indicate that in a gas-turbine engine, with the cooling-air inlet pressure equal to the turbine gas inlet total pressure, cooling flows roughly equal to 1.8 per cent and 3.0 per cent of the main gas flow could be passed through the nozzle and rotor blades respectively, giving average relative temperatures at mid-span of approximately 0.6 in each instance. Comparisons with theoretical estimates of blade temperature show that the external heat-transfer rates to the nozzle blades agreed well with those measured on similar blades in cascade tests. For the rotor blades the external heat-transfer rates appear to have been between those predicted from cascade and earlier turbine test data. From the measured effects of Reynolds number on blade temperature it seems that approximately equal areas of laminar and turbulent boundary layer existed on both nozzle and rotor blades, and that as the turbine inlet temperature was raised, the extent of the turbulent layer tended to increase.
An Examination of the Flow and Pressure Losses in Bfade Rows of Axial ' Flow ' Turbines )
~The design of axial-flo~ turbines has been hampered in the past by a lack of comprehensive data regarding pressure losses and gas deflections through rows of turbine blades. In the present report much of the available information relating to this subject is studied and analysed to determine magnitudes of gas pressure losses and deflections in a wide variety of blade rows and also to determine the separate influences of variables such as blade shape, blade spacing, gas Mach number, Reynolds number, incidence, etc. Of particular importance are the effects of secondary flows on the aerodynamic performance of a blade row and special attention is paid to ' secondary losses ', which form the difference between the total losses occurring in an actual turbine blade row and the smaller two-dimensional flow losses which are usually measured in a blade cascade tunnel. Eff&cts of blade tip clearance are also studied. Resulting from this analysis a number of empirical guiding rules and charts have been derived from which approximate values of the overall pressure losses and gas deflections in a range of blade rows can be deduced. A particularly significant feature brought to light is that the secondary losses can in many instances be large, the loss being generally found to be great when the blading has low reaction.
Main tendencies of religious consciousness development in modern society
The article is devoted to the investigation of the tendencies of religious consciousness development in modern society. At the present stage of development religious consciousness, like any other social and psychological phenomenon, is undergoing significant changes. The development of religious consciousness at the present stage of society evolution leads to the development of common moral norms and requirements. There is a tendency to reduce human ties with the religious community as a translator of religious consciousness. It is possible to speak about the transformation of religious consciousness but not about its disappearance.