Engineering:IHI Corporation F7
The IHI Corporation F7 is a small turbofan engine developed specifically for the Kawasaki P-1 maritime patrol aircraft by IHI Corporation.
Development
IHI started development work on the high bypass ratio turbofan engine in 1998, based on the low bypass ratio engine XF5-1. and the first prototype XF7-1 was tested from 2000 to 2002. The flight test XF7-10's testing started in 2002.[1]
XF7-10's PFRT (Preliminary Flight Rating Test) started in second quarter 2002, and was completed August 2007 before the XP-1 first flight. PFRT was based on the Military Specification MIL-E-5007D and the original standard about the FADEC system.[2]
_F7-10_turbofan_engine(left_wing,_inside)_left_front_view_at_Tokushima_Air_Base_September_30,_2017.jpg){kind=spacer}
Take off thrust is 60 kN (13,000 lbf), bypass ratio is 8.2, and SFC is 0.34 kg/h/daN.[3] Exhaust emission is under the ICAO's standard, NOx is 54%, CO is 33%, UHC is 0.5%, smoke is 74% when standard is 100%.[4]
Strong alloy materials were selected for high corrosion resistance in salt environments, and a sound absorbing panel is mounted.[5] Noise level is 5~10dB lower than P-3's T56, measurements is 76 dB when idling, 70.6 dB at take off.[6]
P-1's F7-10 is installed thrust reversal with GE's cowl opening systems.[7]
Variants
- XF7-1: early prototype, rated at 12,000 lbf (53 kN).[8]
- XF7-10: flight prototype with up to 13,500 lbf (60 kN) thrust.[9][10]
- F7-10: serial production.
Applications
Specifications (F7-10)
_F7-10_Engine_in_Iwakuni_Air_Base_20140914-02.JPG)
General characteristics
- Type: Turbofan
- Length: 2.7 m (8 ft 10 in)
- Diameter: 1.4 m (4 ft 7 in) (Fan)
- Dry weight: 1,240 kg (2,730 lb)
Components
- Compressor: 1-stage fan, 2-stage low pressure compressor, 8-stage high pressure compressor axial
- Combustors: annular
- Turbine: 2-stage high pressure turbine, 4-stage low pressure turbine
Performance
- Maximum thrust: 60 kN (13,000 lbf)
- Overall pressure ratio: Fan Pressure Ratio=1.6:1;Overall Pressure Ratio=27:1
- Bypass ratio: 8.2:1
- Turbine inlet temperature: 1,500 deg C rated
- Power-to-weight ratio:
See also
Related development
Related lists
References
- ↑ XF7-10 development reference paper p. 11 in TRDI Defense Technology Symposium 2007
- ↑ XF7-10 PFRT reference paper p5&p7 in TRDI Defense Technology Symposium 2007
- ↑ XF7-10 development reference paper p7
- ↑ XF7-10 PFRT reference paper p13
- ↑ XF7-10 development reference paper p8
- ↑ XP-1's inspection report by city council member
- ↑ "GE - Cowl Opening Systems". GE Aviation Systems. http://www.geaviationsystems.com/Products--/Mechanical-Systems/Engine-Systems/Cowl-Opening-Systems/. Retrieved 21 January 2009.
- ↑ "Japan tests XF7-1 turbofan" (in en). https://www.flightglobal.com/japan-tests-xf7-1-turbofan-/41850.article.
- ↑ "AEDC Completes Tests Of XF7-10 Engine | Aviation Week Network". https://aviationweek.com/aedc-completes-tests-xf7-10-engine.
- ↑ "Japan's P-1 patrol aircraft faces delays". https://www.spacedaily.com/reports/Japans_P-1_patrol_aircraft_faces_delays_999.html.
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