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Another view of the engine Close up view on cylinder. The Kharkiv model V-2 (Russian: В-2) is a Soviet diesel tank V-12 engine, the V angle at 60°, with dual overhead camshafts per bank, four valves per cylinder opened by bucket-style followers and direct fuel injection.
These offer fuel flexibility and security, but are more expensive than are standard single fuel engines. [6] Portable stoves are sometimes designed with multifuel functionality, in order to burn whatever fuel is found during an outing. [7] Innovative industrial heaters or burners were the subject of multi-fuel research at a Shell plant in 2014. [8]
It is powered by the 1,000 hp 6TD-6-cylinder opposed-piston [28] multi-fuel two-stroke turbo-piston diesel engine, ensuring high fuel efficiency and a long cruising range. The engine support systems make it possible to operate the tank at ambient temperatures of up to 55 °C and ford water obstacles 1.8 m in depth.
The oxygen-rich combustion technology developed for the NK-15 and refined in the NK-33 laid the groundwork for many of the most successful rocket engines in Soviet and Russian history. These include the RD-170, RD-180 and RD-191. While these engines share the oxygen-rich staged combustion cycle, they are not directly related to the NK-33.
The engine was sold by a joint venture between the Russian developer and producer of the engine NPO Energomash and Pratt & Whitney, called RD Amross. The RD-180 was first deployed on the Atlas IIA-R vehicle, which was the Atlas IIA vehicle with the Russian (hence the R) engine replacing the previous main engine.
The 1,000 hp (750 kW) engines are V-92 four stroke, 12 cylinder, multi-fuel diesel while the 1,250 hp (930 kW) engine is V-96. The T-90 export version i.e. modified T-90S is fitted with an increased power multi-fuel 1,000 hp (750 kW) diesel engine with turbochargers. The tank has an air conditioning system for work in hot places.
The RD-8 (Russian: РД-8 and GRAU Index: 11D513) is a Soviet / Ukrainian liquid propellant rocket engine burning LOX and RG-1 (a rocket grade kerosene) in an oxidizer rich staged combustion cycle. [5] [6] It has a four combustion chambers that provide thrust vector control by gimbaling each of the nozzles in a single axis ±33°. [2]
Pages in category "Soviet and Russian aircraft engines" The following 8 pages are in this category, out of 8 total. This list may not reflect recent changes. C.