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]
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]
^XP-1's inspection report by city council member 2009-02-13 at the Wayback Machine
^"GE - Cowl Opening Systems". GE Aviation Systems. Retrieved 21 January 2009.
External links
This aircraft engine article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them.
January 06, 2023
corporation, redirects, here, keyboard, yamaha, motif, motif, carbine, demro, small, turbofan, engine, developed, specifically, kawasaki, maritime, patrol, aircraft, corporation, f7type, turbofannational, origin, japanmanufacturer, corporationfirst, 2000smajor. XF7 redirects here For the keyboard see Yamaha Motif MOTIF XF For the carbine see Demro TAC 1 The IHI Corporation F7 is a small turbofan engine developed specifically for the Kawasaki P 1 maritime patrol aircraft by IHI Corporation F7Type TurbofanNational origin JapanManufacturer IHI CorporationFirst run 2000sMajor applications Kawasaki P 1 Contents 1 Development 2 Applications 3 Specifications F7 10 3 1 General characteristics 3 2 Components 3 3 Performance 4 See also 5 References 6 External linksDevelopment EditIHI 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 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 Applications EditKawasaki P 1Specifications F7 10 Edit 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 turbinePerformance 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 EditRelated development IHI F3 IHI XF5 IHI XF9Related lists List of aircraft enginesReferences Edit XF7 10 development reference paper permanent dead link p 11 in TRDI Defense Technology Symposium 2007 XF7 10 PFRT reference paper permanent dead link p5 amp 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 Archived 2009 02 13 at the Wayback Machine GE Cowl Opening Systems GE Aviation Systems Retrieved 21 January 2009 External links Edit This aircraft engine article is missing some or all of its specifications If you have a source you can help Wikipedia by adding them Retrieved from https en wikipedia org w index php title IHI Corporation F7 amp oldid 1127943914, wikipedia, wiki, book, books, library,
