RTD-1, A.M.Lyulka
I
n 1938 A.M.Lyulka who was working in
Kharkov aviation institute (KhAI) in a team developing steam turbine for A.N.Tupolev
heavy bomber, worked out a design of a turbojet RTD-1 with 500kg thrust with one- or two-stage centrifuge compressor
driven by a gas turbine.
The characteristic feature of that engine was relatively low turbine inlet temperature (650-7000C). The
implemented design decisions and thermodynamic parameters of the RTD-1 ensured that it could be developed in
relatively short time using construction materials fully mastered by that time by the industry.
Estimations made by A.M.Lyulka showed that a single-seat fighter powered by the RTD-1 engine could reach the speed
of 900km/h....The order adopted by the Defence Committee of the USSR's Council of People's Commissars [then the name
of the Soviet Government] on 12 July 1940 the necessity to continue the work
on the turbojet engine of A.M.Lyulka's design was stressed with the aim to test the engine on a test rig already in December
1940".
In the war years the work on development of A.M.Lyulka's RTD-1 engine continued.... In
1943 under the leadership of
M.I.Goudkov (one of the designers of the known
LaGG-3 piston-engined fighter), a variant of the LaGG-3 powered by the
RTD-1 engine was being designed. The engine was to be
installed in the "step" layout at the bottom of the fuselage with jet exhaust under the tail
[Yak-15 look-alike]. The maximum speed of the modified LaGG-3 was
estimated at 900km/h".
| RTD-1 |
1938 |
turbojet |
500kg |
- |
Based on "Samoliotostroyenie v SSSR (1917-1945)" [Aircraft Development in the USSR], Vol 2, published by TsAGI in 1994.
Prepared by Alexander Velovich;
Found at the Russian Aviation Page ;
