Page 220 - The Jet Engine

Thrust distribution

Therefore given that the turbine--

OUTLET Area (A) = 480 sq.in.
Pressure (P) = 21 lb. per sq.in.
(gauge)
Velocity (v J ) = 888 ft. per sec.
Mass flow (W) = 153 lb. per sec.

The thrust
= ( A x P ) + WV J − 55 , 417
g
153 x 888
= ( 480 x 21 ) + − 55 , 417
32

Combustion chambers = 14,326 - 55,417
14. The conditions at the combustion chamber inlet
are the same as the conditions at the diffuser outlet, = -41,091
i.e. 21,235 lb. Therefore, given that the combustion
chamber- This negative value means a force acting in a
OUTLET Area (A) = 580 sq.in. rearward direction.
Pressure (P) = 93 lb. per sq.in.
(gauge)
Velocity (v J ) = 309 ft. per sec.
Mass flow (W) = 153 lb. per sec.
The thrust
= ( A x P ) + WV J − 21 , 235
g
153 x 309
= ( 580 x 93 ) + − 21 , 235
32
= 55,417 - 21,235

= 34,182 !b. of thrust in a forward direction.

Exhaust unit and jet pipe
16. The conditions at the inlet to the exhaust unit
are the same as the conditions at the turbine outlet,
i.e. 14,326 lb.
Therefore, given that the jet pipe--
OUTLET Area (A) = 651 sq.in.
Turbine assembly Pressure (P) = 21 lb. per sq.in.
15. The conditions at the turbine inlet are the same (gauge)
as the conditions at the combustion chamber outlet, Velocity (v J ) = 643 ft. per sec.
i.e. 55,417 lb. Mass flow (W) = 153 lb. per sec.

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