GE Honda HF120 Compre

- 18.05

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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.


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Development

Succeeding Honda's original HF118 prototype, the HF120 was undergoing testing in July 2008, with certification targeted for late 2009. The first engines were produced at GE's factory, but in November 2014 production shifted to Burlington, North Carolina. The U.S. Federal Aviation Administration (FAA) awarded Part 33 certification to the HF120 turbofan engine in December 2013, and production certification in 2015.


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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. The HF120 engine's components interact with greater efficiency by incorporating 3D aerodynamic design and its effusion-cooled combustor design emits few NOx, CO and HC. Noise levels are quieter than Stage 4 requirements.

In May 2016 time between overhaul was 2,500 h and should mature to 5,000 h ; a midlife hot-section inspection isn't required and it should remain on wing 40% longer than other engines and have lower operating costs : Honda maintenance plan should run at $139 per engine per hour.


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Applications

The engine was announced as a retrofit to the Cessna CitationJet CJ1 by Sierra Industries, in partnership with GE Honda, besides the Hondajet.


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Specifications

Data from Honda

General characteristics

  • Type: Turbofan engine
  • Length: 44 inches (110 cm)
  • Diameter: maximum: 21.2 inches (54 cm)
  • Dry weight: <400 lb (180 kg)

Components

  • Compressor: One wide-chord fan, two axial low-pressure stages, one centrifugal high-pressure stage.
  • Combustors: compact reverse flow
  • Turbine: One axial high-pressure stage, two axial low-pressure stages.

Performance

  • Maximum thrust: takeoff thrust: 2,050 lbf (9.1 kN)
  • Overall pressure ratio: 24
  • Bypass ratio: 2.9
  • Specific fuel consumption: <0.7 lb/lbf/h (20 g/kN/s)
  • Thrust-to-weight ratio: >5

Source of the article : Wikipedia



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