General Electric F414

GE evolved the F404 into the F412-GE-400 non-afterburning turbofan for the McDonnell Douglas A-12 Avenger II. After the cancellation of the A-12, the research was directed toward an engine for the F/A-18E/F Super Hornet. GE successfully pitched the F414 as a low-risk derivative of the F404, rather than a riskier new engine. The F414 engine was originally envisioned as not using any materials or processes not used in the F404, and was designed to fit in the same footprint as the F404.[3]

The F414 uses the core and full-authority digital engine control (FADEC) from the F412, and the low-pressure system from the YF120 engine developed for the Advanced Tactical Fighter competition. One of the major differences between the F404 and the F414 is the fan section. The F414 fan is larger than that of the F404, but smaller than the F412 fan.[4] The larger fan increases the engine airflow by 16% and is 5 inches (13 cm) longer. To keep the F414 in the same envelope, or space occupied in the airframe, as the F404, the afterburner section was shortened by 4 in (10 cm) and the combustor shortened by 1 in (2.5 cm). Also changed from the F404 is the construction of the first three stages of the high-pressure compressor which are blisks rather than separate discs and dovetailed blades, saving 50 pounds (23 kg) in weight.[3] The F414 uses a "fueldraulic" system to control the area of the convergent-divergent nozzle in the afterburner section. The nozzle actuators use engine fuel whereas the F404 uses an engine hydraulic system. "Fueldraulic" actuators for afterburner nozzles have been used since the 1960s on the Pratt & Whitney J58[5] and Rolls-Royce Turbomeca Adour,[6] for example. They are also used to swivel the VTOL nozzle for the Rolls-Royce LiftSystem.[7]

The F414 continues to be improved, both through internal GE efforts and federally funded development programs. By 2006 GE had tested an Enhanced Durability Engine (EDE) with an advanced core. The EDE engine provided a 15% thrust increase or longer life without the thrust increase. It has a six-stage high-pressure compressor (down from 7 stages in the standard F414) and an advanced high-pressure turbine.[8] The new compressor should be about 3% more efficient. The new high-pressure turbine uses new materials and a new way of delivering cooling air to the blades. These changes should increase the turbine temperature capability by about 150 °F (83 °C).[9] The EDE is designed to have better foreign object damage resistance, and a reduced fuel burn rate.[10][11]

The EDE program continued with the testing of an advanced two stage blade-disk or "blisk" fan. The first advanced fan was produced using traditional methods, but future blisk fans will be made using translational friction welding with the goal of reducing manufacturing costs.[9] GE touts that this latest variant yields either a 20% increase in thrust or threefold increase in hot-section durability over the current F414.[8] This version is called the Enhanced Performance Engine (EPE) and was partially funded through the federal Integrated High Performance Turbine Engine Technology (or IHPTET) program.[10][12]

Other possible F414 improvements include efforts to reduce engine noise by using either mechanical or fluidic chevrons and efforts to reduce emissions with a new trapped vortex combustor.[9] Chevrons would reduce engine noise by inducing mixing between the cooler, slower bypass air and the hotter, faster core exhaust air. Mechanical chevrons would come in the form of triangular cutouts (or extensions) at the end of the nozzle, resulting in a "sharktooth" pattern. Fluidic chevrons would operate by injecting differential air flows around the exhaust to achieve the same ends as the mechanical variety. A new combustor would likely aim to reduce emissions by burning a higher percentage of the oxygen, thereby reducing the amount of oxygen available to bond with nitrogen forming the pollutant NO_x.

As of 2009, the F414-EDE was being developed and tested, under a United States Navy contract for a reduced specific fuel consumption (SFC) demonstrator engine.[13][14] In addition, General Electric has tested F414 engines equipped with a second low-pressure turbine stage made from ceramic matrix composites (CMC). The F414 represents the first successful use of a CMC in a rotating engine part. The tests proved CMCs are strong enough to endure the heat and rotational stress inside the turbine. The advantage CMC offers is a weight one third that of metal alloy and the ability to operate without cooling air, making the engine more aerodynamically efficient and fuel efficient. The new turbine is not yet ready for a production aircraft, however, as further design changes are needed to make it more robust.[15]

As of 2023, over 1,600 F414 engines have been delivered.[2]

Data from GE Aviation,[32] Deagal.com,[33] and MTU Aero Engines[34]

• Type: Afterburning turbofan
• Length: 154 in (391 cm)
• Diameter: 35 in (89 cm)
• Dry weight: 2,445 lb (1,110 kg) max weight

• Compressor: axial compressor with 3 low-pressure stages and 7 high-pressure stages
• Combustors: annular
• Turbine: 1 low-pressure stage and 1 high-pressure stage

• Maximum thrust:
  
• 13,000 lbf (57.8 kN) military thrust
• 22,000 lbf (97.9 kN) with afterburner
• Overall pressure ratio: 30:1
• Bypass ratio: 0.25:1
• Air mass flow: 170 lb/s (77.1 kg/s)
• Specific fuel consumption: 14,700 lb @ 0.840 lb/HR/lb st (w/o afterburner); 22,000 lb (afterburner) @ 1.850 lb/HR/lb st
• Thrust-to-weight ratio: 9