The paper presents results of studies on anti-cavitation properties of propellant-feeding systems of advanced oxygen/hydrogen engines when they operate on boiling hydrogen. It provides a description of an algorithm for conducting cyclic cavitation tests on booster turbopump assemblies. It also provides a schematic of a test setup developed at CADB. Test runs of the setup were preceded by prolonged analytical effort which included profiling of new versions of axidiagonal impellers, CFD flow simulations to evaluate the efficiency of the proposed profilings, constructing a non-stationary model and writing the software that can simulate the operation of the setup. The software made it possible to evaluate the effect of regime parameters on the test setup operation. The final part of the effort was running tests on the setup using hydrogen. The tests provided cavitation characteristics of three booster turbopump assemblies at various flow rates and temperatures of liquid hydrogen. The test results made it possible to update the math model taking into account special profiling features of the axidiagonal impellers. Key words: LOX-LH2 rocket engine, booster turbopump assembly, cavitation, vapor content.

The article presents a review of the results of studies of laser ignition of a cryogenic mixture (gaseous hydrogen and liquid oxygen) in an experimental combustion chamber, carried out at the bench testing facility of KBKhA (Voronezh). A laser ignition module specially designed at the Keldysh Research Centre and with parameters optimized for use in the rocket engine launch system was used during the experiments. Fuel ignition by the laser system occurred directly in the experimental chamber without the use of an ignition device or pre-chamber. To implement this ignition method, inflammation of the fuel in the chamber was carried out by focusing the laser radiation into the mixture, with the initiation of a spark of optical breakdown in the selected area with conditions favorable for the start of combustion. The results of the experiments confirmed the efficiency of the laser module during both standalone and firing tests, including multiple launches of the propulsion unit operated on a cryogenic mixture (gaseous hydrogen and liquid oxygen).