| H-Series | |
|---|---|
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| Let L-410NG H85 installation | |
| Type | Turboprop |
| National origin | Czech Republic/United States |
| Manufacturer | GE BGA Turboprops |
| First run | 2009 |
| Major applications | Thrush Model 510 Let L-410NG Technoavia Rysachok |
| Developed from | Walter M601 |
TheGeneral Electric H-Series is a family ofturbopropaircraft engines produced byGE BGA Turboprops. The initial H80 is an updated derivative of theWalter M601, while the H75 and H85 are later derivatives.
The H80 was launched in 2009 based on the M601. GE added a new compressor,blisks, blades and new stators to enhance power by 3% and boost efficiency by 10%.[1]It reaches 597 kW (801 hp) (shaft horsepower) from the M601-F's 580 kW (780 hp),[2] and improveshot and high performance.
The H80 was certificated by EASA at 13 December 2011, followed by the FAA at 13 March 2012.[3] Its Russian type certificate was received in October 2012, and the engine also approved by Brazilian Civil Aviation agency (ANAC) and the Argentine Administración Nacional de Aviación Civil.[4]
ItsElectronic Engine and Propeller Control (EEPC) system received EASA type certification in late 2016.TheDiamond Dart 550 military trainer is due to fly it in early 2018 and it will be certified on theThrush 510G crop duster in this year.[1]
The two-shaft, reverse flow design is derived from theWalter M601: its core features a two-stageaxial and single-stagecentrifugal compressor, anannular combustor and a singleturbine stage, and its propulsion section is powered by a single-stage turbine driving a two-stageplanetary gearbox.GE redesigned the compressor with3D aero to improve itspressure ratio and upgraded the hot section and turbine stages with modern metal alloys for higher temperatures with the same durability.[5]
The H75-100 weighs 94 lb (43 kg) more than the equivalentPT6 but pioneers single lever electronic propeller andengine control in general aviation, for an initialTBO of 4,000 hr which could be increased with experience.[5]It promises 10% better fuel burn, 10% longer overhaul and lower maintenance costs than the PT6A-135 for theNextant G90XT.[6]
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| Variant | H75 | H80 | H85 |
|---|---|---|---|
| Dimensions (L×W×H) | 1,670×560×580 mm (66×22×23 in) | ||
| basic dry | 390 lb (180 kg) | ||
| Compressor[13] | 2-stageaxial + 1-stagecentrifugal | ||
| Combustor[13] | Annular with fuel slinger | ||
| turbine[13] | 1-stage axial gas.gen + 1-stage axial power | ||
| fuel type | Jet-A/A1 | ||
| Shaft power | 751 hp (560 kW) | 800 hp (597 kW) | 850 hp (634 kW) |
| Eq. shaft power | 795 hp (593 kW) | 845 hp (630 kW) | 898 hp (670 kW) |
| Power-to-weight ratio | 1.93 | 2.05 | 2.18 |
| gas gen. RPM | 35,524 | 35,854 | 36,183 |
| Shaft RPM | 2,080 | ||
| airflow | 8.1 lb (3.7 kg)/s | 8.2 lb (3.7 kg) | 8.4 lb (3.8 kg) |
| TBO | 4,000 h | ||
| Overall pressure ratio | 6.7:1[14] | ||
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