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.