The GTDE is a turboshaft engine with a free
turbine, has a modular design, with the turbocompressor module being
one-shaft with centrifugal compressor and one-stage turbine. The
reduction gear of the power turbine is executed according to the
two-stage multi-flow scheme. The purpose is to provide the independent
pre-flight aircraft preparation without starting the main engines and
their subsequent startup.
The gas turbine engine-power unit differs by a relatively small mass at
high available power, is produced in several modifications for a number
of domestic and foreign planes. The main modifications – GTDE-117 and
GTDE-117-1 are installed on MiG-29, MiG-29К, Su-27, Su-30, Su-33, Su-35,
etc.
|
|
MAIN TECHNICAL
SPECIFICATIONS |
|
GTDE-117 |
GTDE-117-1 |
VK-100/VK-100V/VK-100N |
GTDE-117M
GTDE-117-1M (VK-100-1M) |
|
Developer |
Klimov Corporation |
Krasny Octiabr
Klimov Corporation |
|
Type |
Turboshaft, with free turbine |
|
Inlet air temperature, ° С |
From –60 to +60 |
|
Power in the starter mode, h.p.: |
|
|
at Н=0 and ISA. |
90+8 |
90+8 |
100+8 |
110+10 |
|
at Н=2,5 km and ISA +300C |
65+9 |
65+9 |
75+7 |
88+7 |
|
at Н=3,5 km and ISA +300C |
Is not discussed |
Is not discussed |
70+7 |
83+7 |
|
Power in the power-unit mode, h.p. |
70+3 |
mode is not provided. |
mode is not provided. |
90+5 |
|
Fuel |
RT, TC-1 and
others |
|
Fuel flow-rate, not more than,
kg/hour
|
|
|
in the starter mode
|
67 |
67 |
70 |
70 |
|
in the power-unit mode |
57 |
mode is not provided. |
mode is not provided |
70 |
|
Overall dimensions, LхØ, mm |
680х260 |
|
Mass, kg |
40+2% |
|
