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.
The Thermodynamics of Cooled Turbines: Part 1—The Turbine Stage

 A procedure has been obtained for calculating the effect of cooling on turbine-stage efficiency by visualizing the flow in the blade passages as one-dimensional compressible flow in a conical tube with heat transfer and friction. The use of Reynolds’ analogy between friction and heat transfer permits the results to be correlated in terms of the blade-profile loss coefficient in low-speed flow, the change of passage area in the blade section and the ratio of average blade-surface temperature to the stagnation temperature of the gas relative to the blades. Simple expressions are obtained for the amount of heat abstracted in a cooled row of blades and the drop in turbine-stage efficiency resulting from cooling. Calculations for some typical stages show that, with blades cooled appreciably below the gas temperature, the amount of heat removed may be as much as 5 per cent of the calorific value of the fuel per row of cooled blades and the decrease in turbine-stage efficiency as much as 3 per cent when both nozzles and blades are cooled appreciably. The use of impulse and low reaction stages reduces to a small fraction of a per cent the effect on the stage efficiency of cooling the rotor blades only.
Fault Diagnosis and CAN Bus/Ethernet Redundancy Design of a Monitoring and Control System
The ship monitoring system is used to monitor and control the working status of various equipment on the ship. The navigational safety of the ship is affected directly by the stable working of the monitoring system. In this paper, a ship monitoring system with fault-type judgment function and bus redundancy is designed to improve system reliability and reduce fault checking cost. A redundant Ethernet/CAN bus communication network is constructed in the system, which connects multiple simulation nodes. The simulation node can simulate the faults that may occur during the communication process and feeds back the fault information to the host computer. The host computer will analyze and display the corresponding fault type on the user interface with the feedback information is received. The system reconfigures the network route autonomously when the simulation node has a communication fault. Routing of fault nodes can be switched to redundant routing, and the load balancing of the communication network can be maintained. Through experimental tests, the system can accurately locate faults and achieve fast switching of redundant routes between buses. Hence, the reliability of data transmission is improved.