|
RU95101579A
|
|
Method of replacing assembly of working vanes of turbine stage of gas-turbine engine
|
|
RU94028910A
|
|
Gas-turbine engine exhaust unit
|
|
RU2094705C1
|
|
Combustion chamber of aircraft engine or power gas-turbine engine
|
|
RU2084725C1
|
|
Reduction gear for axially alined shafts rotating in opposite direction with same speed
|
|
RU2098638C1
|
|
Method and device for turbine blade cooling
|
|
RU2073147C1
|
|
Multi-flow two-gearing transmission
|
|
RU2034177C1
|
|
Method of replacement of damaged blades of gas-turbine engine fan
|
|
RU2044131C1
|
|
Method of operation of radial-axial turbine of large divergence and radial-axial flow turbine of large divergence proper
|
|
RU2016119C1
|
|
Dispersive reinforced nickel based alloy
|
|
RU2013568C1
|
|
Method of replacement of axial-flow compressor moving blades
|
|
RU2035595C1
|
|
Method of braking turbine of engine
|
|
RU2009397C1
|
|
Gas-turbine engine fuel injector
|
|
RU1825021C
|
|
Turbine nozzle block
|
|
RU2009331C1
|
|
Turbine part convective cooling device
|
|
RU2018744C1
|
|
Planetary gear train
|
|
RU2028482C1
|
|
Device for automatic control of gas-turbine engine
|
|
RU1828166C
|
|
Whirling arm (its variants)
|
