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10 September 2005
CFM PROPRIETARY INFORMATION
Subject to restrictions on the cover or first pa ge
• The High Pressure Turbine
Clearance Control system controls
the HPC 4th stage (-5A, 5th stage) &
9th stage air send to the HPT shroud
support.
• The air flows through an HPTCC
Valve.
• The ECU uses the HMU to control
the position of the HPTCC Valve.
• The HMU sends servo fuel pressure
to move the HPTCC valve actuator.
• The HPTCC actuator sends an
electrical position feedback signal to
the ECU.
HPTCC: High Pressure Turbine Clearance Control
Tighter
clearance
SFC
Aiirr Coonnttrrooll Syysstteem
58
Flight Operations Support
10 September 2005
CFM PROPRIETARY INFORMATION
Subject to restrictions on the cover or first pa ge
HPTCC: High Pressure Turbine Clearance Control
Aiirr Coonnttrrooll Syysstteem
59
Flight Operations Support
10 September 2005
CFM PROPRIETARY INFORMATION
Subject to restrictions on the cover or first pa ge
• The Low Pressure Turbine Clearance
Control system controls the amount of
Fan discharge air that goes to the LPT
case.
• The air flows through the LPTCC valve.
• The ECU uses the HMU to control the
position of the LPTCC valve.
• The HMU sends servo fuel pressure to
move the LPTCC valve actuator.
• The LPTCC actuator sends an
electrical position feedback signal to the
ECU.
LPTCC: Low Pressure Turbine Clearance Control
Tighter
clearance
SFC
Aiirr Coonnttrrooll Syysstteem
60
Flight Operations Support
10 September 2005
CFM PROPRIETARY INFORMATION
Subject to restrictions on the cover or first pa ge
LPTCC: Low Pressure Turbine Clearance Control
Aiirr Coonnttrrooll Syysstteem
61
Flight Operations Support
10 September 2005
CFM PROPRIETARY INFORMATION
Subject to restrictions on the cover or first pa ge
• The TBV system improves HPC stall
margin during engine start and
acceleration
• The air flows through the TBV.
• The ECU uses the HMU to control the
position of the TBV.
• The HMU sends servo fuel pressure to
move the TBV actuator.
• The TBV actuator sends an electrical
position feedback signal to the ECU.
LPT stg 1 nozzle
9 stage
X
X X
TBV
HPC
Aiirr Coonnttrrooll Syysstteem
TBV: Transient Bleed Valve
62
Flight Operations Support
10 September 2005
CFM PROPRIETARY INFORMATION
Subject to restrictions on the cover or first pa ge
Block test
Vibration test
Blade containment
Ingestion tests
Water
Hail
Ice slab
Hail stone
Birds (medium & large)
Mixed sand & gravel
Induction system icing test
Overtemperature test
Flight Ops Support
Engine Certification & TTeessttiinngg
63
Flight Operations Support
10 September 2005
CFM PROPRIETARY INFORMATION
Subject to restrictions on the cover or first pa ge
Ennggiinnee Ceerrttiiffiiccaattiioonn
A variety of development and
certification tests are conducted on
CFM56 engines. Ground testing is
primarily accomplished by GEAE’s
Peebles Test Operation in Peebles,
Ohio and by comparable SNECMA
facilities in France like Saclay. Flight
testing is accomplished by GEAE’s
Flight Test Operation in Victorville,
California.
This presentation summarizes some of
these tests and test facilities used.
64
Flight Operations Support
10 September 2005
CFM PROPRIETARY INFORMATION
Subject to restrictions on the cover or first pa ge
Test Objectives
• Demonstrate fan blade containment inside casing
• No fire accepted
• Engine mounting attachments must not fail
• Engine shut-down capacity within 15 sec.
Main goal is to show no hazard to the aircraft
Test description
• Engine running at or above maximum allowed fan speed
• 1 fan blade released : explosive in shank of released blade.
Ennggiinnee Ceerrttiiffiiccaattiioonn
Blade containment test
65
Flight Operations Support
10 September 2005
CFM PROPRIETARY INFORMATION
Subject to restrictions on the cover or first pa ge
To demonstrate the capability of the engine to operate
satisfactorily while ingesting simulated foreign object.
• with no substantial thrust loss
- water : 4% (in weight) of total airflow
- hailstones : 25 x 2 ” + 25 x 1” stones within 5 seconds
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CFFM556 Flight Operations Support(8)
