The R-16 (8K64) first stage engine "Glushko RD-218" and its derivative

--  RD-216, RD-224, RD-251 and RD-261 --

 

Norbert Brügge, Germany

Update: 
26.10.2017

In the 1960s, some first stage engines were created for ICBM's in the KB Glushko, who have a special design. There are engines with two combustors that operate with a common gas-generated turbopump. This turbopump is mounted in a horizontal position between the nozzles on a platform. The combustion chamber is relatively small and the nozzle is very elongated.

There are four groups of design:
The first group includes the engines RD-215 and RD-215M. The small combustion chamber has a long nozzle. The chamber pressure is 7.35 MPa, the thrust 370 kN (s.l.). Two of a total of four combustion chambers are supplied by a common turbopump. The turbopumps are so positioned that the exhaust of the gas-generator flows from the center of the arrangement to the periphery by double-pipes. These engines were installed in the first stages of the R-14 and "Kosmos-3" (2x = RD-216). The fuel combination is UDMH / AK-27. The engines of the R-14M and "Kosmos-3M" SLV (2x = RD-216M) are equipped with a new turbopump.

The second group includes the engines RD-217. The small combustion chamber has a long nozzle again. The turbopump is associated with two combustors again. The chamber pressure is 7.35 MPa, the thrust 740 kN (s.l.). The turbopumps are so positioned that the exhaust of the gas-generator is flows out at the periphery of the arrangement. The supply of fuel to the nozzle takes place in the center of the arrangement. These engines were installed in the first stage of the R-16 (3x = RD-218). The fuel combination is UDMH / AK-27.

The third group includes the engines RD-225. It was intended for the unrealized R-26 (2x = RD-224). The engine is a twin again. The combustion chambers are wide as at the engines of the fourth group. Turbopump, nozzle and propellant corresponding to the features of the second group. The chamber pressure is 8.33 MPa, the thrust 760 kN. This twin-combustor engine should be installed twice. The fuel combination is UDMH / AK-27.

The fourth group includes the engines RD-250 and 250PM. Together is a wider chamber and a modified nozzle (the ring for the fuel supply is positioned lower). The chamber pressure is 8.33 MPa, the thrust 788 kN. Now (contrary to the R-16), the turbopumps are so positioned so that the exhaust of the gas generators takes place in the center of the arrangement. The supply of fuel in the nozzle is on the periphery of the arrangement. These engines were installed in the first stages of the R-36 (3x = RD-251) and Tsiklon (3x = RD-261). The fuel combination is now UDMH / N2O4.
 

Group

Combustor (1)

Blocks

Engine

Combustor

Turbopump

RD-215 (single) RD-216 (complete)
(R-14)
1

RD-215 (8D513)

2 =RD-216

 
Group

Combustor (1)

Blocks

Engine

Combustor

Turbopump

RD-215 (single) RD-216M (complete)
(R-14-M)
1

RD-215M (8D613)

2 =RD-216M

 
Group

Combustor (2)

Blocks

Engine

Combustor

Turbopump

RD-217 (single) RD-218 (complete)
(R-16)
2

RD-217 (8D515)

3 =RD-218

no image

no image

 
Group Combustor (2) Blocks

Engine

Combustor

Turbopump

RD-225 (single)

RD-224 (complete)
(R-26)

3 RD-225 (8D721) 2 =RD-224

no image

 
Group

Combustor (2)

Blocks

Engine

Combustor

Turbopump

RD-250 (single)

RD-251 (complete)
(R-36)

4

RD-250 (8D518)

3 =RD-251

 
Group Combustor (2) Blocks

Engine

Combustor

Turbopump

RD-250PM (single)

RD-261 (complete)
(Tsiklon)

4 RD-250PM 3 =RD-261

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The R-16 (8K64) second stage engine "Glushko RD-219" and its derivative

--  RD-252 and RD-262 --

Upload: 02.10.2016

In the 1960s, second stage engines were created for ICBM's in the KB Glushko, who have a special design again. There are engines with two combustors that operate with a common gas-generated turbopump. This turbopump is mounted in a horizontal position between the nozzles again (but not on a platform). The special feature of the engine is that the exhaust of the gas-generator in a nozzle-like tube flows, which obviously has the priority to stabilize the attachment of the turbopump.

There are two designs:
The first design includes the engine RD-219. The turbopump is associated with two combustors. The chamber pressure is 7.35 MPa, the thrust 90 kN (vac). These engine were installed in the second stage of the R-16. The fuel combination is UDMH / AK-27.

The second design includes the engines RD-252 and RD-262. The turbopump is associated with two combustors. But, the combustor is visibly changed. The combustion chamber is shorter and the nozzle is larger. The chamber pressure is 8.92 MPa, the thrust 96 kN (vac). These engines were installed in the second stage of the R-36 and Tsiklon. The fuel combination is now UDMH / N2O4.

Note: Significantly different (as in the first stage) are the engine frameworks in the R-16 and R-36.

Combustor (2)

 

RD-219 (8D713)

 

Combustor (2)

 

RD-252 (8D724)

 

Combustor (2)

 

RD-262 (11D26)