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时间:2011-04-16 10:02来源:蓝天飞行翻译 作者:航空
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////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
OIL TANK (REF)
ACCESS PORT AP-8 (225`) SEE B-B
IDG COOLING OIL TUBE (REF)
FUEL INJECTOR ECS BLEED TUBES (REF) FWD SUPPLY MANIFOLD (REF)
D
ACCES PORT 
AP-8 (338`) 
SEE B-B  FUEL INJECTOR 
SUPPLY MANIFOLD 
(REF)  OVERHEAT 
DETECTOR 
ACCESS PORT 
AP-8 (277`) 
SEE B-B 
FWD 

ECS BLEED TUBES (REF)  TURBINE CASE (REF) COOLING TUBE 
FWD  F 
Figure 614 (Sheet 3) Combustion Chamber Access Port Locations 

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COMBUSTION CHAMBER  INNER COMBUSTION 
FUEL INJECTOR  BULKHEAD  CHAMBER ASSEMBLY 
(24 LOCATIONS) 

ID SIDE OF OUTER 1ST-STAGE
COMBUSTION HPT
CHAMBER COMBUSTION OR VANE DILUTION HOLE (REF) (EXAMPLE) LOUVER LIP
OUTER(EXAMPLE)
COMBUSTION CHAMBER SEE AASSEMBLY
COMBUSTION CHAMBER CROSS-SECTION
AP-8 
BORESCOPE 
LOUVER GAP  ACCESS PORT (EXAMPLE)  BORESCOPE  BORESCOPE AP-9  OD SIDE (COLD SIDE) OF OUTER 
(EXAMPLE)  LOOKING  ACCESS PORT  COMBUSTION CHAMBER 
LOUVER KNUCKLE  FORWARD  (OPTIONAL, 93`) 
AREA (EXAMPLE)
L-A3330 (0395) 

A
DILUTION HOLES (EXAMPLE)  OUTER COMBUSTION CHAMBER LOUVERCOMBUSTION HOLES (EXAMPLE) (NO. 4, 5, 6 LOUVERS) SURFACE (EXAMPLE)(NO. 3 LOUVER)
OUTER BURNER LINER 1ST-STAGE BULKHEAD SURFACE HPT VANES
FUEL INJECTOR (24 LOCATIONS)
FUEL INJECTOR GUIDE AND HEATSHIELD DILUTION HOLES (24 LOCATIONS) (EXAMPLE)
(NO. 5, 6 LOUVERS)
FWD SLIP JOINT SEAL INNER COMBUSTION
COMBUSTION L-A3336 HOLES (EXAMPLE)
CHAMBER LOUVER SURFACE (NO. 3 LOUVER) (EXAMPLE) COMBUSTION CHAMBER INTERNALS VIEW LOOKING CIRCUMFERENTIALLY Combustion Chamber Components Figure 615
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////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
LOUVER IDENTIFICATION NUMBERS DIM
2  3  4  5  6  7  8  9 
1  DIM  DIM 
B  D 
FWD 

DIM A
C
12 O'CLOCK
POSITION
24
23
FUEL INJECTORS
22
(24 LOCATIONS) 21
20
19
18 MOUNT LUG LOCATIONS
17 (12
16
LOCATIONS) 15
14
13
6 O'CLOCK
POSITION
12
11
10
9
8
IGNITER PLUG LOCATIONS 7 (2
6
LOCATIONS)
5
4
3
2
1 POSITION 12 O'CLOCK
PLANVIEW - COMBUSTION CHAMBER INTERNAL SURFACE
Outer Combustion Chamber Figure 616
360`
330`
DIM A = 300` DIM B =
270` DIM C = DIM D =
240`
210`
180`
150`
120`
90`
60`
30`
0`
CLOCKWISE FROM THE REAR
CIRCUMFERENTIAL
AXIAL
RADIAL
1.42 INCHES REF
(36.068 mm)

0.97 INCH REF
(24.638 mm)
1.24 INCHES REF
(31.496 mm)

0.98 INCH REF
(24.892 mm)
L-A3337 (0597)
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CIRCUMFERENTIAL
DIM C  AXIAL
DIM B 
 
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