GE Honda HF120
Turbofan manufactured in Japan and the US From Wikipedia, the free encyclopedia
The GE Honda HF120 is a small turbofan for the light business jet market, the first engine to be produced by GE Honda Aero Engines.
| HF120 | |
|---|---|
| |
| Type | Turbofan |
| National origin | Japan/United States |
| Manufacturer | GE Honda Aero Engines |
| First run | 2009[1] |
| Major applications | Honda HA-420 HondaJet |
Development
Succeeding Honda's original HF118 prototype, the HF120 was undergoing testing in July 2008, with certification targeted for late 2009.[2] The first engines were produced at GE's factory, but in November 2014 production shifted to Burlington, North Carolina.[3] The U.S. Federal Aviation Administration (FAA) awarded Part 33 certification to the HF120 turbofan engine in December 2013, and production certification in 2015.[4]
Design
The engine has a wide-chord swept fan, two-stage low-pressure compressor and counter rotating high-pressure compressor based on a titanium impeller, for a 2,050 lbf (9.1 kN) takeoff thrust.[5] The HF120 engine's components interact with greater efficiency by incorporating 3D aerodynamic design, and its effusion-cooled combustor design emits low NOx, CO and HC. Noise levels are quieter than Stage 4 requirements.[6]
In May 2016 time between overhaul was 2,500 h, which was expected to mature to 5,000 h; a midlife hot-section inspection is not required, and it is expected to remain on wing 40% longer than other engines and have lower operating costs.[7]
Operational history
Besides the HondaJet, HF120 was announced as a retrofit to the Cessna CitationJet CJ1 by Sierra Industries,[8] in partnership with GE Honda.[9]
In addition, Spectrum Aeronautical has announced it is planning to use HF120 for its upcoming S-40 Freedom.[10]
Applications
Specifications
Data from Honda[11]
General characteristics
- Type: Turbofan engine
- Length: 59.5 in (151 cm) (end-to-end)
- Diameter: 25.8 in (66 cm)
- Dry weight: 211.3 kg (466 lb) with basic accessories and optional equipment[12]
Components
- Compressor: One wide-chord fan, two axial LP stages, one centrifugal HP stage.
- Combustors: Compact reverse flow annular
- Turbine: One axial HP stage (48,777 rpm), two axial LP stages (19,055 rpm).
Performance
- Maximum thrust: 2,050 lbf (9.1 kN) (Takeoff)
- Overall pressure ratio: 24:1
- Bypass ratio: 2.9:1
- Turbine inlet temperature: 1,580 °F (860 °C) (Takeoff)
- Specific fuel consumption: <0.7 lb/lbf/h (71 kg/kN/h)
- Thrust-to-weight ratio: 4.4
See also
Related lists
References
External links
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