AIRCRAFT INVESTIGATION
performance calculations for the Soloviev D-20P aircraft engine
Soloviev D-20P turbofan engine of 49.03 [KN] (11022 [lbf]) thrust
introduction : 6200 country : USSR importance : ***
applications : Tupolev Tu-124V
max. rating (take-off) : 49.03 [KN] (11022 [lbf], 5000 [kgf])
weight engine(s) dry : 1450.0 [kg] = 33.81 [N/kg]
General information :
(normal) turbine inlet temp.: JPT 923 [K]
Max. turbine inlet gas temperature : 1330 [K]
by-pass ratio : 0.0 : 1
gear ratio : 1.0 : 1
overall pressure ratio (OPR) : 13.0 : 1
rpm LP : 8550 [rpm]
rpm HP : 11700 [rpm]
axial flow engine
LP compressor stages : 3 [ ]
HP compressor stages : 8 [ ]
HP turbine stages : 1 [ ]
LP turbine stages : 2 [ ]
stages : 3 + 8 + 1 + 2
fan diameter : 97.6 [cm] engine diameter : 0.0 [cm]
air mass flow : 113 [kg/s]
design hours : 855 [hr] time between overhaul : 427 [hr]
publishe specific fuel consumption (cruise power) :73.0 [kg/KNh]
Literature :
DISCLAIMER Above calculations are based on published data, they must be
regarded as indication not as facts.
Calculated performance and weight may not correspond with actual weights
and performances and are assumptions for which no responsibility can be taken.
Calculations are as accurate as possible, they can be fine-tuned when more data
is available, you are welcome to give suggestions and additional information
so we can improve our program. For copyright on drawings/photographs/
content please mail to below mail address
(c) B van der Zalm 27 June 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4
notes :
D-20P (avid.ru) gives sfc : 0.88 [kg/kgf h]