G.
For additional information on the compressor section, refer to
AMM 72-30-00/001.
7. Combustion Section (Fig. 11)
__________________
A. The diffuser and combustor is attached to the high pressure compressor (HPC) rear case. The compressed air flows from the exit of the HPC into the diffuser and combustor section. The airflow is straightened and diffused which reduces the air velocity and increases the pressure of the airflow prior to entering the combustion chamber. Metered fuel is provided to the combustion chamber through 24 fuel injectors. The air-fuel mixture is burned within the combustion chamber. The heat resulting from the combustion process causes the airflow to expand and accelerate rearward to drive the turbines and produce thrust at the exhaust (jet) nozzle.
B. For additional information on the combustion section, refer to
AMM 72-40-00/001.
8. Turbine Section
_______________
A. The turbine section consists of the turbine nozzle, the high pressure turbine (HPT), the low pressure turbine (LPT), and the turbine exhaust case.
B. Turbine Nozzle (Fig. 12)
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SEE A
5 6 7 8 9 10 12 13 14 15
11
10 11 12 13 14
G I 5 6 7 8 9
V
HOLLOW STATOR L-A0702
VARIABLE STATOR VANE STAGES
A
High Pressure Compressor (HPC)
Figure 10
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A
SEE A FWD
DIFFUSER/COMBUSTOR CASE A L-A0274
A
COMPARTMENT NO. 3 BEARING NO. 3 BEARING
STATOR COMPRESSOR EXIT AIRFLOW NOZZLE DIVERGENT DIFFUSER
INNER WALL (NOZZLE) FUEL INJECTOR CHAMBER OUTER COMBUSTION COMBUSTION CHAMBER
L-A0275 CASE DIFFUSER STRUT DIFFUSER CASE DOWELED END A-A RETAINING) BOLT (COMBUSTION CHAMBER OUTER WALL COMBUSTION CHAMBER
Figure 11 Combustion Section
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OUTER COMBUSTION CHAMBER (BULKHEAD)
A
A
SEE A
A
HONEYCOMB SEALS
COOLING AIR NOZZLE
HPT COOLING
DUCT DEFLECTOR
1ST-STAGE HPT (BLADE) COOLING DUCT
INNER COMBUSTION CHAMBER
1ST-STAGE HPT
VANE CLUSTER
OUTER BURNER
LINER OUTSIDE
DIAMETER GUIDE
A-A
L-A0526
Turbine Nozzle
Figure 12
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(1)
The turbine nozzle contains the inner combustion chamber, the 1st-stage HPT (blade) cooling air duct, and the 1st-stage HPT (nozzle guide) vane clusters. The turbine nozzle is located in the rear internal portion of the diffuser case.
(2)
The inner combustion chamber (liner) forms the inner half of the annular combustion chamber (burner). The combustion chamber design is commonly referred to as a double pass flow type burner. The cooling air which is used to insulate the liner from the heat of combustion enters the liner through several small holes at each liner ring into a circumferential groove. The air is then introduced to the inner surface of each liner as a uniform cooling film.
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