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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:
07.12.2018
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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.
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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 |
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| Group |
Combustor (1)
|
Blocks |
Engine
|
Combustor
|
Turbopump
|
RD-215 (single) |
RD-216M (complete)
(R-14-M) |
| 1 |
RD-215M (8D613)
|
2 |
=RD-216M |
 |
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| Group |
Combustor (2)
|
Blocks |
Engine
|
Combustor
|
Turbopump
|
RD-217 (single) |
RD-218 (complete)
(R-16) |
| 2 |
RD-217 (8D515)
|
3 |
=RD-218 |
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no image
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no image
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| Group |
Combustor
(2) |
Blocks |
Engine
|
Combustor
|
Turbopump
|
RD-225 (single)
|
RD-224 (complete)
(R-26)
|
| 3 |
RD-225
(8D721) |
2 |
=RD-224 |
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no image
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| Group |
Combustor (2)
|
Blocks |
Engine
|
Combustor
|
Turbopump
|
RD-250 (single)
|
RD-251 (complete)
(R-36)
|
| 4 |
RD-250 (8D518)
|
3 |
=RD-251 |
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| Group |
Combustor
(2) |
Blocks |
Engine
|
Combustor
|
Turbopump
|
RD-250PM (single)
|
RD-261 (complete)
(Tsiklon)
|
| 4 |
RD-250PM |
3 |
=RD-261 |
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