72-50-00
ALL ú ú N01 Page 1 ú Feb 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
OUTER COMBUSTION CHAMBER (BULKHEAD)
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
A
A
SEE A
A
HONEYCOMB SEALS
COOLING AIR NOZZLE
DEFLECTOR OF THE
HPT COOLING DUCT
COOLING DUCT OF THE
1ST-STAGE HPT (BLADE)
INNER COMBUSTION CHAMBER
VANE CLUSTER
OF THE
1ST-STAGE HPT
OUTSIDE DIAMETER
GUIDE OF THE OUTER
BURNER LINER
A-A
L-A0526
Turbine Nozzle
Figure 1
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-50-00
ALL ú ú N01 Page 2 ú Feb 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
SEE A A
A
TURBINE FRONT SEALS KNIFE-EDGE HUB (1ST-STAGE) THE 2ND-STAGE AIRSEAL OF ROTATING HPT TURBINE INTERMEDIATE HUB (2ND-STAGE)
THREE KNIFE-EDGE CONFIGURATION
TURBINE CASE 1ST-STAGE HPT BLADE DUCT SEGMENT OF THE 1ST-STAGE HPT 2ND-STAGE HPT BLADE DUCT SEGMENT OF THE 2ND-STAGE HPT
A-A 2ND-STAGE VANE CLUSTER 1193 L-A0524
High Pressure Turbine (HPT) Figure 2 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-50-00
ALL ú ú N01 Page 3 ú Jun 10/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
COOLING MANIFOLDS FOR THE HPT CASE
COOLING MANIFOLDS FOR THE HPT CASE
LEGEND HPT COOLING
12TH-STAGE AIR A-A
15TH-STAGE AIR
COMBINED 12TH- AND 15TH-STAGE AIR
FAN DISCHARGE AIR
L-A0525
High Pressure Turbine (HPT)
Figure 2 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-50-00
ALL ú ú N01 Page 4 ú Feb 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
B. The high pressure turbine (HPT) consists of the 1st- and 2nd-stage turbine rotors, a case and vane assembly, and an inner airseal. These items are housed within the HPT case and are air cooled. The HPT case is cooled by the cooling manifolds of the HPT case.
C. The 1st-stage turbine rotor consists of a nickel alloy hub and 60 blades which are made of a single crystal material. Cooling air to the 1st-stage turbine blades is metered by the cooling air duct in the turbine nozzle through holes in the disk. Cooling air flows through blade passages for internal surface cooling and through a series of leading edge holes to provide film cooling for the airfoil external surfaces.
D. The 2nd-stage turbine rotor consists of a nickel alloy hub, splined in tandem behind the turbine front hub on the rear compressor hub. The 2nd-stage rotor has 82 directionally fixed shroudless blades which are cooled from a mixture of 12th-stage compressor and diffuser case air. Cooling air for the 2nd-stage rotor blades is modulated to reduce flow at cruise conditions in order to improve performance. Cooling air flows through the internal surfaces of the blade cavity, to cool the airfoil. A single retaining plate of the rear blade engages a segmented flange to retain the 2nd-stage blades in the hub. The plate is then locked in place to prevent circumferential movement.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747-400 AMM 飞机维护手册 发动机 ENGINE 2(97)
