| F3 | |
|---|---|
| |
| IHI F3 Turbofan Engine | |
| Type | Turbofan |
| National origin | Japan |
| Manufacturer | IHI Corporation |
| First run | 1981 |
| Major applications | Kawasaki T-4 |
| Number built | ~550[1] |
The Ishikarajina-Harima Heavy Industries (IHI) F3 is a low bypass turbofan engine developed in Japan by Ishikarajina-Harima Heavy Industries for the Kawasaki T-4 trainer aircraft. The first prototype engine, the XF3, was manufactured in 1981 and first flew in the XT-4 in July, 1985.
Design and development edit
Ishikawajima-Harima began developing a small turbofan engine in the late 1970s as a competitor for the new jet trainer aircraft being developed by Kawasaki Heavy Industries . The developmental engine was named the XF3, and it was selected over the SNECMA Turbomeca Larzac in 1982 to power the XT-4 trainer. The early developmental models of the engine produced 2,600 pounds-force (12 kN) of thrust, but later models (including the model selected for the XT-4) produced 3,600 lbf (16 kN) of thrust.[2]
The production engine was designated the F3-30 (alternatively, the F3-IHI-30), and it first flew in the XT-4 aircraft in 1985. Production of the qualified engine also began in 1985.[3]
After the engine and aircraft were in production there were several incidents where one or two of the high pressure turbine blades failed, forcing the aircraft to make emergency landings.[4] An investigation revealed that the turbine section was suffering from a vibration resonance problem, leading to the turbine blade failures. The blades were strengthened modified to dampen the vibrations. The engine, and the aircraft, returned to service in 1990.[5]
Beginning in 1999, IHI began upgrading the fielded engines with a new high pressure turbine to increase their service life. This variant of the engine was known as the F3-IHI-30B.[1]
In 2003, IHI began updating the engine with a more advanced Full Authority Digital Engine Control (FADEC). This updated engine was designated the F3-IHI-30C.[1]
XF3-400 edit
Soon after IHI began working on the XF-3, they began developing a more powerful variant of the engine as a technology demonstrator for a theoretical supersonic fighter. This engine was designated the XF3-400. It was designed to be a higher performance, afterburning version of the XF-3, producing around 7,600 lbf (34 kN) of thrust. One distinctive quality of this engine was that it was to have a thrust-to-weight ratio of 7:1, higher than any similarly sized engine.[6]
Work on this engine began in earnest in 1986, and a demonstrator engine was built and tested in 1987. IHI was formally awarded a contract for the engine in 1992, after spending the previous years developing and testing the engine internally.[6]
The primary difference between the XF3-400 and the standard F3-30 is the inclusion of an afterburner. Adding the afterburner is the primary reason why the maximum thrust of the -400 is much higher than the -30. Other changes included compressor and turbine blades that were aerodynamically optimized using 3D computational fluid dynamics techniques, and improved temperature performance in the high pressure turbine.[6]
A 1998 report revealed that thrust vectoring was also being integrated into the XF3-400.[7]
Design edit
The F3 is two shaft (or two spool) low-bypass turbofan. It features a two stage fan (low pressure compressor) on the low pressure shaft, followed by a five stage high pressure compressor on the high pressure shaft. The engine uses an annular combustor, which feeds a single stage high pressure turbine followed by a single stage low pressure turbine. The XF3-400 variant includes an afterburner after the low pressure turbine, the production F3 does not.[6]
The two stage fan uses wide chord blades, and both the production F3 and the advanced XF3-400 use the same fan.[3][6] Unlike the fan, the five stage compressor differs between the F3 and the XF3-400, with the advanced XF3-400 benefiting from 3D computational fluid dynamics (CFD) improvements.[6]
The high pressure turbine blades are single crystal blades, and they are cooled by a thin film of air from inside of the blades. The low pressure turbine blades, like the high pressure compressor were improved between the F3 and the XF3-400 using 3D CFD.[6]
Both the F3 and the XF3-400 use a FADEC for engine control.[6]
Variants edit
- XF3
- Early developmental designation of what became the F3-IHI-30. Several different configurations were considered in this phase of the program.
- F3-IHI-30
- Production variant of the engine. Used by the Kawasaki T-4.
- F3-IHI-30B
- Production version of the engine with an upgraded high pressure turbine.
- F3-IHI-30C
- Production version of the engine with an improved FADEC.
- XF3-400
- Supersonic technology demonstrator variant of the engine. Much higher thrust than the production F3. Includes an afterburner and several aerodynamic upgrades.
Applications edit
Specifications (F3-IHI-30) edit
Data from [8]
General characteristics
- Type: Turbofan
- Length: 79 in (200 cm)
- Diameter: 25 in (63 cm)
- Dry weight: 750 lb (340 kg)
Components
- Compressor: Axial, 2 stage low pressure compressor, 5 stage high pressure compressor
- Combustors: Annular
- Turbine: Single stage high pressure turbine, two stage low pressure turbine
Performance
- Maximum thrust: 3680 lbf (16 kN)
- Overall pressure ratio: 11:1
- Bypass ratio: 0.9:1[6]
- Specific fuel consumption: 0.7 lbm/lbf-hr
- Thrust-to-weight ratio: 4.9:1
References edit
- ^ a b c IHI F3. Jane's Aero Engines. (subscription page) Edited January 13, 2009. Accessed February 9, 2010.
- ^ Japanese trainer engine selected. (1982, December 11). Flight International, 1677. Accessed February 4, 2010.
- ^ a b Hamada, T., Akagi, M., Toda, D., Shimazaki, H., & Ohmomo, M. (1989). T-4 Inlet/Engine Compatibility Flight Test Results. Presented at the AIAA/ASME/SAE/ASEE 25th Joint Propulsion Conference, Monterey, CA: American Institute of Aeronautics and Astronautics.
- ^ Japan Tackles F3 engine problems. (1989, November 29). Flight International, 16. Accessed February 4, 2010.
- ^ Japan finds fix for T-4 trainer. (1990, January 17). Flight International, 27. Accessed February 4, 2010.
- ^ a b c d e f g h i Kashikawa, I., & Akagi, M. (1995). Research on a High Thrust-to-Weight Ratio Small Turbofan Engine. Presented at the 31st AlAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, San Diego, CA: American Institute of Aeronautics and Astronautics.
- ^ Japan stalls future fighter demonstrator. (1998, October 21). Flight International. Retrieved February 4, 2010.
- ^ "IHI F3". 2010 Aerospace Sourcebook. Aviation Week & Space Technology. (subscription page). Accessed February 2, 2010.
[[Category:Turbofan engines 1980-1989]