Fig. 1.7. Relation of instrumentally gauged TC RPM

and inlet air temperature (graph samples from engine log book)

Graph A – Dependence of measured TC RPM on thermo-compensator inlet air

temperature for take-off power setting;

Graph B – Dependence of measured TC RPM on thermo-compensator inlet air

temperature when fuel consumption is constant (330±10 kg per hour);

Graph C – Dependence of measured TC RPM on thermo-compensator inlet air

temperature for maximum continuous power setting.

Graph D – Dependence of measured TC RPM on thermo-compensator inlet air

temperature for maximum fuel consumption limiter operation.

Note:

If Р is different from 760 mm of mercury TC RPM is calculated in the following way:

- for graph А – with the allowance (amendment) according fig. 1.6 or using the formula:

n_TC= n_{TC 760} +0,0222(760–Р_Н);

- for graphs B an D – if TC RPM increases by 0,21% and Р_Н decrease every 10 mm of mercury and opposite;

- for graph С –– if TC RPM increases by 0,15% and Р_Н decrease every 10 mm of mercury and opposite;

Рис. 1.8. График для определения поправок Δn_ТК

для взлетного режима в зависимости от Р_Н по закону регулирования n_ТК= f(Р_Н, t_H), заложенному в ЭРД.

Рис. 1.9. Зависимость максимально допустимой температуры газов

от температуры наружного воздуха при проверке частичной приемистости по термопарам Т–80Т

Fig. 1.8. Graph for Δn_ТК allowance (amendment) calculation

for take off power setting with Р_Н changed by БАРК electronic governor using the formula n_ТК= f(Р_Н, tH)

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