Question: The Energia Lunar Expedition was a project during 1988 to create a lunar base using the Energia booster, initiated by which Soviet engineer, and designer of rocket engines during the Soviet/American Space Race?

Context articles: Energia Lunar Expedition
Energia
Buran programme
Rocket engine
Valentin Glushko
Saturn V-D
Zvezda (moonbase)
Zenit (rocket family)
Soyuz (spacecraft)
RD-0120

The Energia Lunar Expedition was a project that was initiated by Valentin Glushko during 1988 to create a lunar base using the Energia booster.
 The moon base was to be eventually used for mining helium 3 from the lunar surface.
Energia (Russian: Энергия , "Energiya" , "Energy") was a Soviet rocket that was designed by NPO Energia to serve as a heavy-lift partially recoverable launch system for a variety of payloads including the Buran spacecraft.
 Control system main developer enterprise was the NPO "Electropribor".
 The Energia used four strap-on boosters each powered by a four-chamber RD-170 engine burning kerosene/LOX, and a central core stage with 4 one-chamber RD-0120 (11D122) engines fueled by liquid hydrogen/LOX.
The Buran programme (Russian: Бура́н , ] , "Snowstorm" or "Blizzard"), also known as the VKK Space Orbiter programme (Russian: Воздушно Космический Корабль , "Air Space Ship"), was a Soviet and later Russian reusable spacecraft project that began in 1974 at the Central Aerohydrodynamic Institute and was formally suspended in 1993.
 In addition to being the designation for the whole Soviet/Russian reusable spacecraft project, "Buran" was also the name given to Orbiter K1, which completed one unmanned spaceflight in 1988 and was the only Soviet reusable spacecraft to be launched into space.
 The Buran-class space shuttle orbiters used the expendable "Energia rocket" as a launch vehicle.
 They are generally treated as a Soviet equivalent of the United States' Space Shuttle but in the Buran project, only the airplane-shaped orbiter itself was theoretically reusable, and while Orbiter K1 was recovered successfully after its first orbital flight in 1988, it was never reused.
A rocket engine is a type of jet engine that uses only stored rocket propellant mass for forming its high-speed propulsive jet.
 Rocket engines are reaction engines, obtaining thrust in accordance with Newton's third law.
 Most rocket engines are internal combustion engines, although non-combusting forms (such as cold gas thrusters) also exist.
 Vehicles propelled by rocket engines are commonly called rockets.
 Since they need no external material to form their jet, rocket engines can perform in a vacuum and thus can be used to propel spacecraft and ballistic missiles.
Valentin Petrovich Glushko (Russian: Валенти́н Петро́вич Глушко́ , "Valentin Petrovich Glushko"; Ukrainian: Валентин Петрович Глушко , "Valentyn Petrovych Hlushko"; born 2 September 1908 – 10 January 1989), was a Soviet engineer, and designer of rocket engines during the Soviet/American Space Race.
The Saturn V-D was a conceptual booster with the ability to launch three times as much payload as the Russian Energia booster.
 Studied in 1968, it was considered to be the mightiest of the proposed varitions of the Saturn V rocket, rehased as one of the boosters from the Boeing 1967 Saturn studies and utilizing the stage and a half Saturn V-C, four 100 ft tall SRBs, and the ordinary second and third stages of the original Saturn V.
 This booster never flew, but if it had been manufactured it would have had the capability to launch all the necessary components for a space station in one shot.
Zvezda moonbase (Russian: звезда , ""star""), also called DLB Lunar Base was a Soviet plan and project from 1962 to 1974 to construct a crewed moonbase as successor to the N1-L3 crewed lunar expedition program.
 Zvezda moonbase was canceled with the rest of the Soviet crewed lunar programs.
Zenit (Ukrainian: Зеніт , Russian: Зени́т ; meaning "Zenith") is a family of space launch vehicles designed by the Yuzhnoye Design Bureau in Dnipro, Ukraine, which was then part of the Soviet Union.
 Zenit was originally built in the 1980s for two purposes: as a liquid rocket booster for the Energia rocket and, equipped with a second stage, as a stand-alone middle-weight launcher with a payload greater than the 7 tonnes of the Soyuz but smaller than the 20 tonnes payload of the Proton.
 The last rocket family developed in the USSR, the Zenit was intended as an eventual replacement for the dated R-7 and Proton families, and it would employ propellants which were safer and less toxic than the Proton's nitrogen tetroxide/UDMH mix.
 Zenit was planned to take over manned spaceship launches from Soyuz, but these plans were abandoned after the dissolution of the Soviet Union in 1991.
Soyuz (] , Russian: Союз , 'Union' ) is a series of spacecraft designed for the Soviet space program by the Korolyov Design Bureau (now RKK Energia) in the 1960s that remains in service today.
 The Soyuz succeeded the Voskhod spacecraft and was originally built as part of the Soviet manned lunar programs.
 The Soyuz spacecraft is launched on a Soyuz rocket, the most frequently used and most reliable launch vehicle in the world to date.
 The Soyuz rocket design is based on the Vostok launcher, which in turn was based on the 8K74 or R-7A Semyorka, a Soviet intercontinental ballistic missile.
 All Soyuz spacecraft are launched from the Baikonur Cosmodrome in Kazakhstan.
The Soviet RD-0120 (also designated 11D122) was the Energia core rocket engine, fueled by LH2/LOX, roughly equivalent to the Space Shuttle Main Engine (SSME).
 These were attached to the Energia core rather than the orbiter, so were not recoverable after a flight, but created a more modular design (the Energia core could be used for a variety of missions besides launching the shuttle).
 Baselined from the more mature American hydrogen–oxygen engine technology, but considerably modified with Russian innovations and methods, the RD-0120 and the SSME have both similarities and differences.
 The RD-0120 achieved nearly identical specific impulse and combustion chamber pressure with reduced complexity and cost, as compared to the SSME, primarily at the expense of lower thrust-to-weight ratio.
 It uses fuel-rich staged combustion cycle and a single shaft to drive both the fuel and oxidizer turbopumps.
 Some of the Russian design features, such as the simpler and cheaper channel wall nozzles, were evaluated by Rocketdyne for possible upgrades to the SSME.
 It achieved combustion stability without the acoustic resonance chambers that the SSME required.