It is the "Gas Dynamics Laboratory" that was founded in 1929 in Leningrad. From the 1950s, it produced many rocket engines destined for the main Russian space programs.

-Later it became Energia and now it is Energomash.

-Four engines stand out from this first stage of the GDL design office, the RD-107, RD-119, RD-214 and RD-219.

-The RD-107 is a cluster-type rocket engine with 4 liquid propellant chambers, developed between 1954 and 1967.

-They were used for the Vostok and Voskhod with destinations to the Sun, the Moon, Mars and Venus, as well as many artificial satellites.

“RD-107” (PiP=mw)

-The RD-107 used liquid oxygen and kerosene. With a simple turbo-pump it delivered 102,000 Kgs of thrust approximately.

-It had four main combustion chambers and two small ones mounted on a vernier mechanism to maneuver and stabilize the rocket.

-The RD-119 came into use in 1962, with a single-chamber (see Energomash).

“RD-119” (PiP=mw)

-The RD-119 was used in the second stage of more than a thousand launch rockets for the Cosmos satellites.

-The fuel used was liquid oxygen and dimethyl hydrazine. It delivered a thrust of 110,000 Kgf.

"Two views for the RD-214" (PiP)

-The RD-214 went in the first stage of the Cosmos, with four joined combustion chambers forming a cluster, giving a total thrust of 158,800 lbs.

-A turbo-pump group fed the 4 chambers that burned nitric acid and kerosene.

“RD-219” (PiP)

-The RD-219 is the result of the search for engines whose fuels can remain stored on board, instead of the liquid oxygen that is charged at the last moment as it is a cryogenic oxidizer.

-Thus, this engine uses storable mixtures such as RFNA (nitric acid) and UDMH.

-It is a double engine with a unique turbo-pump. It was designed between 1958 and 1961, and they have been used in programs such as Proton / Zond and also in military rockets.

-It gave 198,440 lbf. of thrust.

From Appendix 6: Gas Dynamics Laboratory was the one that made the well known ORM motors, (Opytnyy Raketnyy Motor = Experimental Rocket Motor). They were the first liquid-fuel rockets in the USSR. They were made from 1930.

-They were designed and built at the GDL Department II (RN II?)

-The first one was the ORM (without number). A simple test chamber without studies of internal forms that could improve mixing and flows. They used electric or pyrotechnic ignition.

“The ORM and its cross-section”

“The ORM-1 and its cross-section”

-The ORM-2 was tested in 1932. In 1934 they tested these rockets from ORM-4 up to ORM-22.

-Actually they were small engines with combustion chambers of 40 mm inside diameter (ORM-4 and ORM-8). The ORM-9 measured 90 mm inner combustor diameter.

“ORM-9 and ORM-12”

-Thanks to a writing from a conference published by the NASM -via AEHS- we have a photo of an ORM-50 trial on a static bench.

“ORM-50 test”

“ORM-52”

“Lateral and plane drawing of the ORM-52”

-A really functional ORM was the ORM-65, with a maximum thrust at sea level of 175 Kgf. The normal thrust was 155 Kgf, with a minimum of 50 Kgf.

“ORM-65”

-Among the ORM-65 applications we have the Korolev 212 winged rocket from the year 1936.

-It was also installed on the RP-318-1 glider (Raketoplaner-318-1) by the same designer.

“Two ORM-65 installations”

-For the operation of the rocket motors, the GG gas generator (Gazo-Generator), which appears in the main text, was made in GIRD. We repeat this now as we have a cross-section drawing.

“GIRD GG gas generator”