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performance calculations for the Gnome Rhone Titan 5K aircraft engine
Titan 5K on display at the SNECMA museum at Villaroche, France.
Gnome Rhone Titan 5K air-cooled 5 -cylinder radial engine 240 [hp](179.0 KW)
introduction : 1928 country : France importance : ***
applications : Tupolev ANT-9
normal rating : 240 [hp](179.0 KW) at 1800 [rpm] at 0 [m] above sea level
take-off power : 285 [hp] (212.5 [KW]) at 2000 [rpm]
no reduction, direct drive, valvetrain : overhead valves, pushrod operated
weight engine(s) dry : 240.0 [kg] = 1.34 [kg/KW]
General information : further development of the license built Bristol Titan engine
fuel system : fuel type : octane grade no. 79 oil system :
engine starter type : electric
bore : 146.0 [mm] stroke : 165.0 [mm]
valve inlet area : 39.0 [cm^2] two inlet and two exhaust valves in cylinder head
gas speed at inlet valve : 29.8 [m/s]
throttle : 91.0 /100 open, mixture :13.0 :1
compression ratio: 5.80 :1
stroke volume (Vs displacement): 13.800 [litre]
compression volume (Vc): 2.877 [litre]
total volume (Vt): 16.689 [litre]
overall engine diameter: 123.0 [cm]
calculated engine length: 112.13 [m]
specific power : 13.0 [kW/litre]
torque : 949 [Nm]
engine weight/volume : 17.4 : [kg/litre]
average piston speed (Cm): 9.9 [m/s]
intake manifold absolute pressure (MAP) at 0 [m] altitude Pi : 0.92 [kg/cm2]
(26.63 [inHg])
mean engine pressure (M.E.P.) at 0 [m] altitude Pm : 7.13 [kg/cm2]
compression pressure at 0 [m] altitude Pc: 8.28 [kg/cm2]
estimated combustion pressure at 0 [m] Pe : 33.06 [kg/cm2]
exhaust pressure at 0 [m] Pu : 3.61 [kg/cm^2 ]
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compression-start temperature at 0 [m] Tic: 361 [°K] (88 [°C])
compression-end temperature at 0 [m] Tc: 548 [°K] (275 [°C])
average engine wall temperature at 0 [m] : 476 [K] (202 [°C])
caloric combustion temperature at 0 [m] Tec: 2238 [°K] (1965 [°C])
polytroph combustion temperature at 0 [m] Tep : 2190 [°K] (1917 [°C])
estimated combustion temperature at 0 [m] Te (T4): 2185 [°K] (1912 [°C])
polytrope expansion-end temperature at 0 [m] Tup: 1176 [°K] (903 [°C])
exhaust stroke end temperature at 0 [m] Tu: 1116 [°K] (843 [°C])
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calculations for take-off/emergency power at sea level
average piston speed : 11.0 [m/s]
gasspeed at inlet valve : 33.1 [m/s]
caloric combustion temperature at sea level Tec: 2214 [°K] (1941 [°C])
emergency/take off rating at 2000 [rpm] at sea level : 285 [hp]
Thermal efficiency Nth : 0.356 [ ]
Mechanical efficiency Nm : 0.764 [ ]
Thermo-dynamic efficiency Ntd : 0.272 [ ]
design hours : 1741 [hr] time between overhaul : 360 [hr]
dispersed engine heat by cooling air : 2763.25 [Kcal/minuut/m2]
required cooling surface : 7.57 [m2]
weight cooling ribs : 20.43 [kg]
fuel consumption optimum mixture at 1800.00 [rpm] at 0 [m]: 60.01 [kg/hr]
specific fuel consumption thermo-dynamic : 221 [gr/epk] = 297 [gr/kwh]
estimated specific fuel consumption (cruise power) at 0 [m] optimum mixture : 309 [gr/kwh]
estimated sfc (cruise power) at 1875 [m] rich mixture : 311 [gr/kwh]
specific fuel consumption at 0 [m] at 1800 [rpm] with mixture :13.0 :1 : 335 [gr/kwh]
specific fuel consumption (volume*rpm) intake pressure = 1.0 kg/cm2 at 1800 [rpm] : 393 [gr/kwh]
estimated specific oil consumption (cruise power) : 25 [gr/kwh]
Literature :
Handbook of aeronautics vol.II aero engines page 13
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 28 November 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4
notes :