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304 PROCEEDINGS OF THE 29TH TURBOMACHINERY SYMPOSIUM Table 6. Comparison between the Junkers Jumo 004B Engine and the Advanced Heinkel Hirth HeS 011 Turbojet. (Meher-Homji, 1999) Parameter Manufacturer Thrust, Lbs Weight, Lbs T/W Ratio Length Frontal dia. Air mass flow rate, lb/sec Pressure Ratio RPM Compressor configuration Turbine Configuration Fuel Consumption Lb/Lb thrust Turbine inlet temperature, ° F Jumo 004 B Junkers Engine 2000; (8.927 kN) 1650; (750 kg) 1.21 152” (3860 mm) 30”; (760 mm) 46.7; (21.2 kg/sec) 3.1:1 8700 8 stage axial flow 1 stage turbine 1.4-1.48 1427°F; (775°C) HeS-011A Heinkel-Hirth 2863 , (12.75 kN) 1950; (885 kg) 1.44 131.6” (3343 mm) 32”;(805 mm) 64; (29 kg/sec) 4.2:1 10,205 Diagonal stage +3 axial stages 2 stage air cooled 1.35 1427 °F (775°C) Figure 62. The Heinkel Hirth HeS 011 Engine Designed by Hans von Ohain and Max Bentele. (This was the most advanced turbojet at the end of the war, with a pressure ratio of 4.2:1, 64 lb/sec and thrust of 2863 lb.) (Meher-Homji, 1999; Courtesy ASME) Figure 64. Compressor Section of the HeS 011 Engine Showing the Unique Diagonal Mixed Flow Compressor. (Bentele, 1991) Figure 65. Details of the Advanced Air-Cooled Turbine Section Designed by Dr. Max Bentele for the HeS 011 Engine. (Bentele, 1991) The final air-cooled blades designed by Dr. Bentele did not utilize any strategic materials and were called “topfschaufel.” Figure 63. Layout of the HeS 001 Engine. (Neville and Silsbee, 1948) The development of the turbine section was most challenging. Initially solid blades were employed, and stress rupture occurred at the first stage and fatigue failures at the second stage. The resonance failure was traced to the location of four struts of the rear bearing support. These were eliminated by spacing the struts at unequal angles, thus minimizing the forced excitations that were in resonance with the second-stage rotor blades.PDF Image | THE HISTORICAL EVOLUTION OF TURBOMACHINERY
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