GE H8x – Type Certificate Training Revised Training Presentation
GE PROPRIETARY INFORMATION. The information contained in this document is GE proprietary information and is disclosed in confidence. It is the property of GE and shall not be used, disclosed to others or reproduced without the express written consent of GE, including, but without limitation, it is not to be used in the creation, manufacture, development, or derivation of any repairs, modifications, spare parts, designs, or configuration changes or to obtain FAA or any other government or regulatory approval to do so. If consent is given for reproduction in whole or in part, this notice and the notice set forth on each page of this document shall appear in any such reproduction in whole or in part. The information contained in this document may also be controlled by the U.S. export control laws. Unauthorized export or re-export is prohibited. 2 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8x and M601 powered aircraft
3 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8x
New Work
The H80 free turbine turboprop engines have been designed for commuter, corporate, utility, agricultural, and trainer aircraft. The H8x is a development of the earlier M601 model. This presentation will explain the key characteristics of both families and also highlights the new design features of the H8x.
4 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Engine Operation Limits H80 comparison vs. M601E-11
Atmospheric conditions: temperature - 50⁰C (- 58⁰F) to + 50⁰C (122⁰F) Start at low ambient temperature without pre-heating at Toil ≥ 20⁰C (- 4⁰F) Start at low ambient temperature with pre-heating at Toil ≤ 20⁰C (- 4⁰F)
Shaft power ESHP ESFC Max. gas Propeller Torque Max. generator speed Interturbine Rating (SHP) (ESHP) (lb/ESHP/hr) speed (N.m.) Temperature Ng (%) Nv (rpm) (⁰C ) (lb.ft.) Take-Off (5 min) 800 845 0.587 97.8 2740 674 15 ⁰C (59 ⁰F) 751 798 0.649 98.6 2080 2021 710 Sea level static 800 (670) 844 101.5 2740 780 41 ⁰C (105.8 ⁰F) 751 798 - 100 2080 2021 735 23 ⁰C (73.4 ⁰F) Max. 597 631 357 2740 continuous 800 845 0.587 97.8 2080 2021 674 15 ⁰C (59 ⁰F) 597 629 1700 to 2740
800 844 - 100.1 2080 2021 750 Sea level static 31 ⁰C (87.8 ⁰F) Note: gas generator speed 100% = 36660 rpm M601E-11 numbers in red 2080 propeller rpm = 31023 power turbine rpm 5 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Main Engine Parts
Combustion Power turbine chamber Exhaust rotor Ring gear housing
Reduction gearbox
Accessory Air inlet gearbox case Compressor Compressor Spray ring Exhaust turbine rotor Propeller channel shaft Counter shafts
6 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th H80 Key Highlights
Turbine Fuel slinger Compressor • High temp materials • Even fuel distribution • 3D Aero • Increased thermodynamic power • No fuel nozzle Mx • Enhanced efficiency
Combustor • Annual flow Additional Power • Even thermal loading • New engine sensors • 800 SHP • Digital auto start • Flat rating: 107oF
7 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8x Airworthiness Limitation Airworthiness Limitations
Service Limitations: Number of equivalent flight cycles is calculated acc. to the following formula: Ne=[Ns+Av(Nv-Ns-Np)+Ap*Np]*L Where • Ns ...... No. of engine starts (only starts followed by take-off or several take-offs are considered) • Nv ...... No. of all take-offs • NP ...... No. of repeated take-offs, when the ground idling with propeller in feather position was used before take-off (Ng≥57 %; 830 rpm > Nv ≥ 320 rpm) • AV ...... abbreviated flight cycles coefficient, i.e. the ground idling speeds of both gas generator and propeller were used between successive flights (Ng ≥ 57 %; Nv ≥ 830 rpm) • AP ...... abbreviated flight cycles coefficient, when the ground idling speed of gas generator with propeller in feather position was used between successive flights (Ng ≥ 57 %; 830 rpm > Nv ≥ 320 rpm) • L ...... flight mission coefficient
2.2 Flight cycle definition; values of coefficients AV, AP and L • for abbreviated flight cycles of type V, i.e. engine idling - take-off - flight - landing with reverse - engine idling ...... AV = ref. Table 1 • for abbreviated flight cycles of type P, i.e. engine idling with propeller in feather position - take-off - flight - landing with reverse - engine idling • ...... AP = ref. Table 1 • flight mission coefficient ...... L = ref. Table 1
For each flight cycle it is assumed: • aborted landing frequency ...... 0.05 • total time when take-off rating is used ...... max. 6 % of the TBO • landing with reverse ...... at each landing
9 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th User obligations
To record the following data in the Engine Logbook – Number of starts – Number of take-offs – Number of hours worked
Failure to meet the obligations – Recognition of a higher number of starts/take- offs/hours – Earlier replacement of some parts
10 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th User & Technical Documentation
11 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th USER & TECHNICAL DOCUMENTATION OF THE H8x AND M601 ENGINES
THE USE AND OPERATION OF THE ENGINE IS CONTROLLED, SUPPORTED, SPECIFIED AND RECORDED BY THE FOLLOWING DOCUMENTS (VALID FOR THE PARTICULAR ENGINE VERSION IN EACH CASE): •TECHNICAL CONDITIONS •INSTALLATION MANUAL •OPERATION MANUAL •MAINTENANCE MANUAL •ILLUSTRATED SPARE PART CATALOGUE •SERVICE BULLETIN •SERVICE LETTER •ENGINE LOGBOOK
12 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Communication and technical support
• The User & Technical Documentation is available and easily accessible in the web client zone at http://www.geaviation.cz/
• You can communicate with the Technical Support Department using the Customer Request Form, also available in the web client zone https://www.geaviation.cz/client- zone.htm
13 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Compressor section
14 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8x – basic parts
15 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th H80 - Compressor
New design of axial/centrifugal compressor for higher efficiency and pressure ratio. Two-stage axial compressor is followed by a single centrifugal stage. The necessary swirl at the axial compressor inlet is provided by compressor inlet case struts. Axial compressor features advanced “blisk” design of both stages. Diffuser vanes, rear compressor wall and straightening vanes forms one integral.
16 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8X cut-away: Compressor section
17 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8X compressor rotor
2nd axial: 23 blades
1st axial: 21 blades Impeller: 16 + 16 vanes
18 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Compressor cutaway
19 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th First and second blisk
First and second blisk real parts
20 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th H80 compressor stator
1st axial stator – 32 vanes
2nd axial stator – 23 vanes
21 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th H80 compressor stator
22 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th First and second axial stator
First and second axial stator real parts
23 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Impeller - real parts
24 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th New designed H8x parts
Axial compressor assembly
Compressor intake
Centrifugal compressor case
25 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8x Air bleed valve
New design Fully closed at ng = 90 ⁺³ % (ISA) Fully open at Idle
26 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Gas Generator (Compressor)
27 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th H80 – basic parts
28 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8x Gas Generator
Centrifugal compressor case
Rear diffuser wall 1st & 2nd axial stator PT stator
Compressor inlet case
GGT rear shaft
GG Turbine
GGT stator
Compressor main shaft Combustor Impeller Compressor shaft thrust bearing assy
29 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Hot Section
30 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8x Hot Section
Exhaust duct GG Turbine
GGT guide vane nozzle
Inner combustion liner Power turbine
PT guide vane nozzle
Outer combustion liner
31 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8X Fuel manifold
Fuel intake to the inner slit
4 x Tangential fuel nozzle
Carbon-metal labyrinth seal pad
32 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8X Centrifugal Slinger ring
4 & 4 calibrated holes
Uniform spray pattern and temperature distribution No fuel nozzle maintenance Eliminates need for Hot Section Inspection
33 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Fuel Distributor
34 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8X Combustion Chamber
Torch igniter
Outer combustion liner Deflector
Slinger ring Inner combustion liner
Fuel manifold
Carbon – metal Stub tube labyrinth seal pad
10x bearing slots Interconnecting tube
Carbon – metal Spark plug labyrinth seal pad
E.P. drain nozzle
E.P. drain canister 35 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8X Torch Igniter Cap Bolt
Screen
Whirl nozzle
Interconnecting (flame) tube
20 – 21.5 mm 6.2 mm 4.1 mm 36 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th H80 Drain valve & E.P. container
37 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Compressor turbine Guide Vane Ring (Gas Generator)
GG Turbine shroud 4⁰55″
Integral cast 23 vanes Air cooled airfoil
38 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Compressor turbine (Gas Generator turbine)
• Single-stage axial turbine • Rotation in the counter- clockwise direction – to the left • Drives the compressor
55 blades New airfoil design New material
39 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Power turbine guide vane ring (Free turb.)
Power turbine shroud
9x ITT probe socket Piston ring groove
19 vanes 40 Air cooledGE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Power turbine (Free Turbine)
Double knife seal with stellite tip • Single-stage axial shrouded turbine
Left & right blade • Rotation in the counter- clockwise direction– to the left) • Independent of the gas generator rotor • The power turbine drives the reduction gearbox
28 blade pairs
41 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8x Power section 9x ITT probe flange Exhaust case right site 5x Containment ring supporting pin
RGB mounting flange Containment ring
Power turbine
Heat shield
PT shaft housing “C” flange
PT shaft
Supporting cone proper
Exhaust Oil pressure line case left site
Labyrinth air pressure line Exhaust duct Thrust ball bearing (hot & high) Roller bearing 42 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Reduction & Accessory Gearboxes
43 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8x – Basic Parts
44 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8X Reduction Gearbox
Ring gear
RGB case TQ meter valve Tripod rocker
Oil pressure distributor
Propeller shaft
Quill shaft with helical gear and spline
Tripod lifter 3x
Helical sprocket-gear
Satellite gear assy 3x
Planetary gear case Scavenge and TQ pump Tach generator drive Oil screens Drain valve
45 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8X Planetary Gear Case
3x Lifter
Quilt shaft
3x Helical gear TQ meter valve
3x Satellite gear Tripod
46 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8X Reduction Gearbox (H80-100) Front view
Propeller oil distributor Beta control double lever
Over speed governor Propeller governor
Oil pressure transfer line
Scavenge oil transfer line
Scavenge oil line screen
Oil pressure line screen Metal chip signaler 47 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8x – Basic Parts
48 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8X Accessory drive gearbox
Oil separator Oil filling cap
Oil filter cover Drive gear H Oil dipstick Lubrication nozzles of compressor thrust bearing
Oil return line from cooler
Oil filter
Oil press pump Oil press relieve & bypass valve Oil scavenge pump
Scavenge oil from RGB Oil press pump pickup tube Oil press to RGB 49 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8X Accessory drive box rear view
1 2 1 2
4 4 6 3 5
H80-100 H80-200
50 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Shafts & Bearings
PT rotor Compressor rotor Quill shaft
GGT rotor PT shaft
Quill shaft
Prop shaft
1 2 3 4 5 6
51 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Oil System
52 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th AGB & Oil Tank 10 9 8 7 6 3 13 1
I. 7 liters II. III. 5.5 liters
5 2 liters
2 15 14 11 4 12 1. Oil filler cap 8. Accessory gear box 2. Oil dipstick 9. AGB cover (dividing wall to oil tank) 3. De-aerator 10. Compressor intake 4. Magnetic plug 11. Connecting channel 5. Oil pressure pump 12. Oil screen (return oil from GGT bearing) 6. Oil scavenge pump 13. De-aerator pad (breather)
7. Return manifold 14. Compressor bearing 53 GE Proprietary Information: Subject to restrictions on 1st or cover page 15. Oil level signaler 2013/03/04th Lubrication System
1 2 3 4 5 6 7 8 9 10 11 12 13 14
15 16 40 17 18 19
39 38 37 36 35 34 33 32 31 30 29 28 27 26 25 24 23 22 21 20
Oil pressure: • Idle Min. 0.12 MPa = 17.4 PSI • Ng ≥ 80% = 0.18 to 0.27 MPa = 26.1 to 39.16 PSI
• Minimum oil press annunciation at 0.12 MPa 54 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Legend key
1 – Propeller governor 22 – AGB metal chip detector 2 – Torque metering valve 23 – Oil temperature sensor 3 – Oil screen on press line to RGB 24 – Scavenge oil pump 4 – Oil flow dumper 25 – Magnetic plug 5 – TQ pressure line 26 – Scavenge oil pump 6 – Oil pressure to the prop governor &RGB 27 – Oil screen 7 – Oil dipstick 28 – Oil level signaler 8 – Filling cap 29 – Scavenge oil pump 9 – Oil pressure bypass valve 30 – Oil press pump pickup tube with screen 10 – Oil screen 31 – Oil pressure pump 11 – Oil screen 32 – Oil pressure relieve valve 12 – AGB breather line 33 - De-aeration oil sump 13 – Oil filter 34 – Scavenge oil transfer line 14 – Air pressure valve 35 – Oil screen 15 – Minimum oil pressure switch 36 – TQ pressure oil pump 16 – TQ transmitter 37 – Oil screen 17 – Oil pressure transmitter 38 – RGB metal chip detector 18 – Oil separator 39 – Scavenge oil pump 19 – Impending bypass signaler 40 – Oil pressure from prop governor to the 20 – Oil cooler propeller 21 – Thermostatic valve
55 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Oil system basic
Annunciation panel Auto feather switch
Annunciation panel TQ limiter transmitter
Impending bypass oil press Minimum oil signaler press switch TQ transmitter
Oil cooler
Oil Fuel heat exchanger
AGB chip detector RGB chip detector Annunciation panel Annunciation panel
56 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Oil Pressure Transducers
GE H80-100 Pressure Transducesr • New state of art Kulite pressure probes
KULITE Low Oil Pressure Switch
Oil Pressure Port
Torque Pressure Port KULITE Oil Impending By-Pass Signaller
57 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Suitable oil and amount
AERO SHELL TURBINE OIL 500 (acc. to MIL-L 23699C) AERO SHELL TURBINE OIL 560 (acc. to MIL-L 23699C) MOBIL JET OIL II (acc. to MIL-L 23699C) Synthetic oil B3V (acc. to TU 38-101295-85) BP TURBO OIL 2380 (EXXON TURBO OIL 2380) CASTROL 599
The contamination of oil poured into the engine can be max. in class 8 in accordance with NAS 1638 or max. in class 11 in accordance with GOST 17216-71 standard.
Total amount of oil includes the oil in the oil cooler and propeller hub. And is approx. 11.5 liters
58 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Accessory gearbox
filling
main filter cover
dipstick
59 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Checking the oil filter
60 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Maintenance procedures
Replacement of the oil filter element and changing oil
• After the first 300 hours of flight operation
• During every second inspection of type 3 or after 12 months (Operation Manual)
When replacing the units of the reduction gearbox and the accessory gearbox perform an engine test and flight test of the aircraft
61 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Maintenance procedures
Replenishing oil based on actual consumption • 0.1 l / 1 flight hour
If the chip detector in the pilot cockpit lights up, check: • electromagnetic detectors • magnetic plug • filter element of the oil filter • protective strainers
62 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Possible Oil Leakage
63 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Auxiliary Air Systems
Auxiliary Air systems
64 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Auxiliary Air Systems
65 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Fuel System
66 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Fuel system basic
1 Electric fuel pump boost pressure 0.15 - 0.3 MPa (21.8 – 43.5 PSI)
2 Torch igniter fuel pressure 0.15 ± 0.01 MPa (21.75 PSI)
3 Fuel pump pressure 2.0 ─ 0.1 MPa (308 PSI)
4 Fuel pressure to slinger ring 1.2 MPa max. Annunciation panel (174 PSI) 5 Impending bypass fuel pressure drop 0.025 ± 0.005 MPa (3.62 ± 0.725 PSI) Impending bypass signaler 4 3 2
5 PCL Torch igniter
Fuel tank
Firewall fuel filter 1 Condition level Auto start 4
67 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Fuel Control Unit Fuel Control Unit LUN 6590.05-8
69 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Fuel Control Unit
EHT (Electro Hydraulic Transducer
High altitude aneroid
α1 - power lever
Main fuel pressure
α2 - condition lever(ECV)
ECV solenoid
P2 air pressure Fuel drain fitting Starting circuit
70 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Fuel Pump
Single stage gear pump
Fuel inlet
Fuel to torch igniters
Starting (torch igniters) fuel solenoid
Starting (torch igniters) constant fuel pressure Fuel filter housing valve
71 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Fuel Control Unit (FCU)
High altitude aneroid Power lever (α1)
Fly weight governor
Electro-hydraulic transducer
Measuring valve
ECV Solenoid
Drain valve
Starting circuit
72 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Ignition, Auto Start, Limiter
73 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8X Ignition System
Torch igniter
Spark plug
Fuel pump
Starting fuel solenoid
Starting fuel supply Ignition exciter box line
74 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8X Auto-start System
75 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Starter Generator
Starter / Generator
Working voltage 27 to 28,5 V Working voltage by overloading, by rated 26 to 29V
Rated current continuously 200 A Short-time overloading for 5s 400 A (by speed over 7 000 min-1)
Continuous overloading by temperature +30°C 220A
Motor-regime (starter): Maximal voltage 28 V DC Pick starting current approx. 700 A The minimal power 2,9 kW is reached with the terminal voltage 20V by speed of 2 500 min-1
76 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Auto-start and Limiter Unit
Engine parameters FCU
Exciter
STG
Run Pump
77 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th H80 Auto start and Limiter Unit – Limiter unit
• Auto start module controls Fuel Pump • Starter generator power supply
Solenoid valve Torch
• Exciter and torch igniter power supply Igniters
• Fuel pump solenoid valve to torch
igniters
• FCU solenoid valve for fuel slinger ring citer
x
E
Starter Generator
• At auto start, limiter module Interrupting
• Monitors ITT exceeding and ITT gradients • Controls fuel supply Time Sequence
• Auto start benefits
AutoStart
• Automatic sequence after pilot
initiation – reduce workload
RUN
Plugs
Check 28VDC • Reduced chance of ITT exceeding Motoring during start • Compatible with aircraft avionics suite 78 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8x Auto start and Limiter Unit
. Dual function ELU system FCU Fuel Pump
• Auto start module Solenoid valve Solenoid valve • Limiter module . Built-in test capability • Individual circuit test
Ng • Cockpit or external test
Np Limit
. Pilot control of ELU ITT •
Ground only Tq Limiter • Ground and in-flight OAT Controller
BETA AirframeInterface ElectronicEngine
Interrupting
RUN Starter Generator
Time Sequence Exciter AutoStart 79 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Single acting propeller system
80 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Propeller System
Propeller System • Single acting system
Propeller • Hartzell Propeller – 4 blades • AVIA Propeller V508H – 3 blades
Propeller Governor • AVIA P/N P-W11-1
Over-speed Governor • Jihostroj P/N O-112-002/M1
81 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Propeller System Propeller Governor P-W11-1
Low Pitch BETA Control • Compatible with wide range of 3 or 4 blades Adjustment (BC) Connection propellers: • Hartzell • Avia 508H
• Feathering pump is not required • Comprises of prop speed sensor • Low required loads to: Speed • BETA/Power Control Sensor • Propeller Control • Easy ajustement • Low Pitch Angle • Max Prop Speed • BETA switch – separate device
BETA PCL (RN) Feedback Arm Connection Max. Prop BETA Valve Speed Stop 82 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Propeller System
PROP GOVERNOR
OVERSPEED GOVERNOR
83 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Propeller System – Over speed governor
Pilot Valve
• Feathering Speed Governor Solenoid Valve
• Test Solenoid Governor Spring Valve
TEST PROCEDURE • Passive Magnetic Speed Sensor 1. The ECL is set in Ground Idle, The PCLis set in “Feathering” 2. Set PCL maximum speed 3. Test Solenoid Energizing 4. ECL selection to such position that the propeller speed max. 1600±30RPM is achieved. MaxTq = 100% (Tq=2740Nm = 2021ft-lb) shell not beexceed. Path Criteria: The Propeller speed, when theTest Solenoid is energized, shell be within the range 1570 RPM to 1630RPM 5. The ECL is set in Ground Idle 6. Disengage the Test Solenoid.
84 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Single Acting System GE H80-100
BETA Mode
• Range of operation from PBA to full revers 5. Spool stops oil bleeding 5. • Pilot is allowed to manually control the prop pitch • Prop blade is controlled via BETA Valve and BETA push/pull control 1.ECL/BETA Lever Movement to BETA Mode 1. 4. Servopiston,BETA ring and BATA valve moves 4. forwardmoves backward
2.BETA Valve 4. Retraction 3. Oil Bleeding
2. 3. 85 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Single Acting System GE H80-100 On Speed Condition
Speeder Spring Load = Centrifugal force
Pilot Valve stops bleeding oil to prop dome
86 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Flyweight governor • Sensing of propeller speed • Produce centrifugal force Single Acting System acts against Speeder Spring • Controls Pilot Valve Prop Control Lever GE H80-100 • Control prop speed via Speeder Spring BETA Control Lever • Control pitch during BETA mode Speeder Spring • Combined with • Act against Flyweights Engine Control • Selects prop speed , higher the tension higher the speed Lever via Reversing Cam BETA Nut Prop Servo-Piston Pilot Valve • Moves up and down in response to prop speed • Oil distribution to prop dome
BETA Valve Feathering Spring • Setting of PBA • Oil distribution during BETA ring BETA feedback system BETA Mode
87 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Propeller governor P-W11-1 Basic setting
Beta valve basic setting
Feather stop
Prop max. RPM stop ¼ rev = 25 RPM 88 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th BETA Switch & Feedback Arm
Propeller Beta Ring BETA Feedback Arm Support
BETA Carbon Block
BETA Switch
BETA Feedback Arm
89 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Beta switch and Beta carbon block
BETA Switch
BETA Carbon Block
Propeller Beta Ring
90 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Dual Acting Propeller System
91 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Dual Acting System – GE H80-200
Propeller System • Dual Acting System Propeller • AVIA V725– 5 blades – new model • AVIA V510– 5 blades Propeller Governor • AVIA p/n P-W22-1 • Jihostroj p/n LUN 7816-8 Over-speed Governor • Allocated at the tip of the propeller servo-piston
92 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Daul Acting System – GE H80-200
Propeller Governor P-W22-1 vs. LUN 7816-8
P-W22-1 LUN 7816-8
93 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Dual Acting system – GE H80-200
No provision which protects propeller from going below Jihostroj minimum flight pitch LUN 7816-8
Propeller AVIA V725
• Lock Pitch Solenoid AVIA V725 • Protection of blades from • No Lock Pitch Spool AVIA going below min flight vs. P-W22-1 pitch (PBA) AVIA V 510 • Lock Pitch Spool
94 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Dual Acting System – GE H80-200 Propeller Governor P-W22-1 • Weight 2,9kg (Jihostroj 3,8 kg) Primary BETA Control • Lock Pitch Solenoid Blade Pitch Adjustable o Protection from going below Bolt PBA to full reverse • BETA switch • Synchronizing/Sychrophasing – optional • Simple calibration of o Primary Blade Angle o Max Prop Speed
Prop Speed BETA Control Lever Max Prop BETA Valve Speed Stop 95 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Dual Acting System: H80-200 Flyweight governor • Sensing of propeller speed • Produce centrifugal force Propeller governor P-W22-1 acts against Speeder Spring • Controls Pilot Valve Prop Servo-Piston Prop Control Lever BETA Control Lever • Control prop speed • Control pitch during Gear Pump-Engine Driven via Speeder Spring BETA mode • Max 380 PSI • Combined with Engine Overspeed Control Lever via Governor Reversing Cam Pilot Valve • Moves up and down in response to prop speed • Oil distribution to prop dome
Speeder Spring • Act against Flyweights • Selects prop speed, higher the tension higher the speed
BETA Valve • Setting of PBA • Oil distribution during BETA ring BETA Mode
BETA Switch Lock Pitch Solenoid • Provides signaling when BETA feedback system • Protection blades blades go below PBA from going below PBA
96 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Dual Acting System – GE H80-200 Propeller governor P-W22-1 • Primary Blade Angle • Over-speed Governor
• Spool moves up BETA valve stops • Bleeding oil from bleeding oil to prop prop dome to drain dome 97 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Dual Acting System – GE H80-200 Speeder Spring Load Propeller governor P-W22-1 = Centrifugal force • On Speed Condition Pilot Valve stops bleeding oil to prop dome
98 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Dual Acting System – GE H80-200 Propeller governor P-W22-1 • Under Speed Condition Speeder Spring Load Is greater Centrifugal force
Pilot Valve bleeds oil to prop dome
Backward movement of servo piston
99 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Dual Acting System – GE H80-200 Speeder Spring Load Propeller governor P-W22-1 Is lower Centrifugal force • Over Speed Condition Pilot Valve bleeds oil to prop dome
Forward movement of servo piston
100 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Dual Acting System – GE H80-200
Propeller governor P-W22-1 Elektro-Hydraulic Servovalve • Automatic Feathering • Oil goes directly to prop
Governing function is canceled
Feathering Pump • Airframe device • Supply oil to prop
101 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Dual Acting System – GE H80-200 Further movement Circuit opening Propeller governor P-W22-1 disconnect ECL switch
• Lock Pitch Lock Pitch Solenoid Solenoid is disabled
Activation by BETA Switch Lock Pitch Solenoid is • Spool stops oil engaged bleeding to prop 102 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Dual Acting System – GE H80-200 Propeller governor P-W22-1 • BETA Mode
BETA valve stops bleeding oil to prop
2. Servopiston, BETA ring and BETA valve moves backward 3. Movement of BETA 1. Control and consequently BETA valve extension
Oil supply to prop 103 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Engine Controls
104 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8x – Controls
Throttle quadrant Double Lever BC Lever BETA Control Cam
– –
PCL RN Lever
Condition Level
105 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H8X – BETA control
106 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Instruments for monitoring
Speed sensing
107 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th H80 - 100 (single acting propeller)
H80 Propeller Speed Sensing • Two Passive Speed Sensors: – Prop speed limiting during Reverse. Speed exceeding annunciation – Instrument panel
H80 Gas Turbine Speed Sensing Passive Speed Sensor • Two Passive Speed Sensors Propeller Governor Instrument panel Passive
Speed Sensor GT speed exceeding Speed annunciation
Over-speed Speed Governor GT Speed Speed Sensor
Autostart kit/ Limiter unit
Passive Speed GT Speed Exceeding Sensor STATUS LIGHT PT Speed Exceeding STATUS LIGHT 108 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th GE H80 Accessories – Dual Acting
Pressure Torquemeter Pressure Switch Starter-Generator Electrohydraulic Switch- Pressure for ELU LUN 2132.02.-8 Actuator Feathering Transmitter LUN 1476-8 LUN 7880.01-8 System LUN 1540.02-8 Min Oil LUN 3280-8 Pressure Switch LUN 1581-8
Prop Governor LUN 7816-8 Fuel Control Unit LUN 6590.05-8
Fuel Pump LUN 6290.04.-8 NP Speed Transmitter LUN 1333.12B-8
Oil Filter Impending By-Pass Switch LUN 1493.03-8 ITT Transmitter LUN 1377-8
Oil quantity Exciter UNISON Oil Temperature Signaler Transmitter GT Speed Transmitter LUN 1581-8 LUN 1358-8 LUN 1333.12B-8 109 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th ITT, Oil Temp Sensing
ITT Sensing Oil Temp Sensing • Thermocouple Type K • Nickel Resistive Sensor • High Resistance of Limiter unit and Glass Panel • Calibration is performed by means of software of o Compensation Harness is not Required Engine Data Recorder/Glass Panel • Additional Compensation not required • Cold Junction Compensation in the EDC Connector by means of Silicon Temp Devices • Calibration is performed by means of software of Engine Data Recorder/Glass Panel Limiter Unit
STATUS LIGHT
Oil Probe
Cr-Al TC wire ENGINE DATA CONVERTER
ITT Thermocouples
110 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th ITT System
Harness in parallel wiring 9x ITT probe P/N LUN 1377-8
111 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Engine Inspections and Troubleshooting Maintenance Schedule
Planned Inspections – Line maintenance: Planned inspection procedures can be distinguished by program and scope into the following types:
A. Inspection of Type 1 This inspection of Type 1 is carried out daily before launching the flight program. Inspection of Type 1 can be performed by a pilot.
B. Inspection of Type 2 This inspection should be carried out every 100±10 hours of flight operation. NOTE: GEAC recommends to the operators to include inspection Type 2 if the engine is left un- operated for a period of 90 days or longer.
C. Inspection of Type 3 Inspection of Type 3 is carried out after 300 ±30 hours of flight operation or at the expire of a period specified by the manufacturer of the individual accessories (Refer to the Table 604), whichever comes first.
D. Inspection of Type 4 Inspection of Type 4 is carried out at the expire of 900 ±30 hours in flight operation or at period specified by the manufacturer of the individual accessories (Refer to the Table 604), whichever comes first.
113 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Inspection Schedule
114 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Inspection Schedule
115 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Inspection Schedule
116 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Inspection Schedule
117 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Planned engine inspections
Engine inspection examples Type 1 Engine mount Type 2 Checking the oil filter check Oil refill Type 3 and its space Oil check and oil Type 4 consumption Every inspection of a higher type automatically calculation includes the lower types
Starter- generator brush wear
Measurement of Check of fire Checking Electric Elmg. chip detector Elmg. chip thermocouples of bulkheads the fixation installation check detector Ignition unit the temperature of the wiring check check transmitter exhaust
screen 118 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Planned engine inspections
Check and flushing of the high-pressure fuel filter
Check of adjustment of the engine Adjustment of the control transmitter and switches on levers the monitoring unit Z800 or Z8001 Check of adjustment of Check of the exhaust the engine control elbows for cracks and levers deformations
119 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th
Planned inspections
Adjustment of the switches, transmitter
and indicator on the Monitoring unit Z800 with monitoring units Z800 and Z8001 a pressure pump
Monitoring unit Z8001
Example of adjustment of the transmitter and torque indicator 120 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Performance evaluation
121 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Performance Diagram No. 501
122 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Unplanned Inspections
• Unplanned inspections follow either an unplanned replacement of any engine part (in extreme, the whole engine), or any accessory. Among further reasons for unplanned inspections belong unusual stress or operating conditions, exceeds operating limitations, unsatisfactory performance of engine. These cases are detailed in chapter Table 605. • As far as the engine parameters worsened significantly, it is necessary to carry out unplanned inspection of the axial-flow compressor 1st stage blades (Ref. 72-30-01 AXIAL-FLOW COMPRESSOR, Para 1. Inspection/Check ). • If an inspection/check of the parts or accessories of the engine or engine function check is required after parts or accessories replacement then prescribed procedure is presented in the applicable chapter MAINTENANCE PRACTICES, Inspection/Check and Adjustment/Test. • Inspections and tests checking the engine condition after some part replacement concern the whole power unit; therefore they are dealt with in 71-00-00 POWER UNIT - MAINTENANCE PRACTICES, Para 2. Inspection and Testing Procedures after Parts Replacements. • In case of accident, it is necessary to contact the organization authorized to technical services or immediately the engine manufacturer.
123 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Unplanned Inspections
As far as the inter-turbine temperature, torque or propeller speed have exceeded the operation limits, ref. the following paragraphs A., B. and C.
A. Over temperature In case of ITT exceeding either at engine start or in operation it is necessary to investigate this event. Proceed in compliance with enclosed diagrams (Figs. 601, 602 and 603).
B. Over torque. In case of max. torque exceeding record its value and time interval. Proceed in compliance with enclosed diagram (Fig. 604).
C. Propeller Over speed As far as the propeller speed limit has been exceeded, proceed in compliance with Table 606.
124 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Unplanned Inspections
125 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Unplanned Inspections
126 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Unplanned Inspections
127 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Unplanned Inspections
128 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Troubleshooting
The recommended engine troubleshooting procedures are described in the form of flow charts in the tables below. These tables contain operation experience that can be useful for the diagnostic and remedy of various errors occurring during operation in the engine or its systems.
129 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Troubleshooting – example
130 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Maintenance liquids and chemicals
131 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Maintenance liquids and chemicals
132 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Maintenance liquids and chemicals
133 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Questions and Answers Questions and Answers
135 GE Proprietary Information: Subject to restrictions on 1st or cover page 2013/03/04th Feedback on Training Feedback on Training
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