New light super-heat-resistant powder Ni3Al and NiAl-based alloys (of the Ni-Al-Mo-B,
Ni-Al-Fe-La, and Ni-Al-Y2O3 systems), as well as a new technology for preparing and processing
them have been developed. The density of the alloys was 7.3-7.5 and ~6 g/cm 3, respectively. The
Ni3Al sheets were used to prepare shields for combustion chambers in gas-turbine engines by roomtemperature
deformation; the shields are intended for the long-term operation at 1100-1200°C and
for the short-term use at 1300°C. The activated NiAl powders alloyed with Fe+La were used to
produce sintered complex-shape articles, such as combustion stabilizers in a jet unit of combustion
chamber of the gas-turbine installation, heat sources, etc. capable of operating at t≤1500°C under
low mechanical stresses. At 1100, 1300, and 1500°C, the 100-h strength of the heat-resistant NiAl-
(2-7.5) vol. % Y2O3 alloys subjected to directional recrystallization is 70, 35 and ≥10 MPa,
respectively. The vanes, in which the length of recrystallized grain is smaller than the vane length
by a factor of 1.5-2, were manufactured from these alloys.
661.762 At the end of the 1960s, the Central Scientific Research Institute of Ferrous Metallurgy (TsNIIchermet) began research in a new direction -the powder metallurgy of special alloys and composites. The studies and projects undertaken in this area were oriented toward the development of qualitatively new powder structural and functional materials and technologies for producing such powders, as well as semifinished products and finished products made from them.Operating within this framework, the Institute of Powder Metallurgy of TsNIIchermet has made rapid strides in the creation of powder alloys and composites that resist heat, scaling, corrosion, and wear. A prominent portion of this research has been devoted to studies of intermetallic compounds -a new class of structural and functional materials having unique physico-chemical properties.The development of a new generation of aerospace technology and the successful introduction of hypersonic aircraft are requiting a special set of materials for the airframes and power plants of these vehicles. The materials must be able to work for long periods of time under heavy thermal loads in an oxidizing medium comprised of supersonic and hypersonic gas flows with a temperature of 1000-1600~The materials must also be of low density and have a high melting point. The use of commercial heat-and scaling-resistant nickel alloys in the elements of thermally loaded structures is limited by certain physico-chemical properties of these materials: the instability of the structure and phase composition, the catastrophic reduction in resistance to gaseous corrosion and softening at temperatures above 900ol 100~ relatively high density (8.3-8.9 g/cm3), and low solidus temperature (1265-1380~The intermetallides Ni3A1 and NiA1 and alloys of the system Fe-Cr-AI occupy a special place among the metallic materials characterized by high heat resistance, high melting point, and low density. The heat resistance of these materials, determined on the basis of the gain in weight in air over 100 h at 1200~ is 4--10 times greater them that of the well-known nickel superalloys, their density (p) is 10025% lower, the melting point is 1200375~ higher than the solidus temperature of the superalloys (Table 1), and the allowable working temperatures are hundreds of degrees higher than the working temperatures of titanium alloys, steels, and nickel superalloys (Fig.
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