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Garrett TFE731
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Honeywell TFE731

Honeywell TFE731-60


The Honeywell TFE731 is a family of geared turbofan engines commonly used on business jet aircraft. The engine was originally designed and built by Garrett AiResearch, and due to mergers was later produced by AlliedSignal and then Honeywell Aerospace.

The TFE731 was based on the core of the TSCP700, which was specifically developed for use as the auxiliary power unit (APU) on the McDonnell Douglas DC-10. The design featured two important factors: low fuel consumption, and low noise profiles that met the newly established U.S. noise abatement regulations.

The first test run of the TFE731 occurred in 1970 at Garrett's plant in Torrance, California. The first production model, the TFE731-2, began rolling off the assembly line in August, 1972, and was used on the Learjet 35/36 and Dassault Falcon 10, both of which entered production in 1973.

The TFE731-60 has an inlet diameter of 0.787 m. The fan consists of 22 fan blades, 52 exit-guide vanes, and ten struts, and is driven by a gearbox. The five-stage compressor has four axial (LP) stages and one radial or centrifugal (HP) stage.

The TFE731-3 was developed for use in the Lockheed JetStar re-engining program, and subsequent versions of it have been used on a number of aircraft, including the Learjet 55.

In 1975, the TFE731 was named Aviation Product of the Year by Ziff-Davis Publishing Company.

The -5 model was certified in 1982, and a decade later, an engine utilizing the TFE731-5 power section and a TFE731-3 fan was built and designated the TFE731-4, intended to power the Cessna Citation 650 Citation VII aircraft.

The TFE731-50 version, based on the -60 used on the Falcon 900DX, underwent its flight test program in 2005. Honeywell has developed this engine complete with nacelle as a candidate to retrofit a number of aircraft equipped with older engines.

Since the engine was introduced in 1972, over 11,000 engines have been built, flying over 100 million flight-hours.



CASA C-101
Dassault Falcon 10
FMA IA 63 Pampa
Hongdu JL-8
Learjet 31
Learjet 35/Learjet C-21

Boeing Skyfox
British Aerospace BAe 125 Series 700
Cessna Citation III
Cessna Citation VI
Dassault Falcon 50
Learjet 55
Lockheed 731 Jetstar/Jetstar II
IAI 1124 Westwind I
Hawker HS125 series

Aero L-139 (prototype only)
Cessna Citation VII

Hawker 800/850XP
Dassault Falcon 20 (retrofit)

Learjet 40
Learjet 45

Gulfstream G100/G150 (formerly IAI 1125 Astra SPX)
C-38 Courier
FMA IA 63 Pampa

Hawker 900XP

Dassault Falcon 900DX

IAI 1124A Westwind II



Type: Turbofan
Length: 50 in (127 cm)
Diameter: 39 in (100 cm)
Dry weight: 734 lb (333 kg)
Compressor: 1 stage fan, 4 axial high pressure compressor stages, 1 centrifugal high pressure compressor stage
Combustors: Annular
Turbine: 1 stage high pressure turbine, 3 stage low pressure turbine
Maximum thrust: 3500 lbf (15.6 kN)
Overall pressure ratio: 13:1
Specific fuel consumption: 0.5 lb/lbf-hr
Thrust-to-weight ratio: 4.7:1



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