|Honeywell TFE731-60 on a NASA test stand|
|National origin||United States|
|Major applications||CASA C-101
Cessna Citation III
|Developed into||Honeywell/ITEC F124/TFE1042/TFE1088|
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 currently Honeywell Aerospace.
Since the engine was introduced in 1972, over 11,000 engines have been built, flying over 100 million flight-hours.
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 -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 most recent version is the TFE731-50, based on the -60 used on the Falcon 900DX, which 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.
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.
Variants and applications
- AIDC AT-3
- 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
- Dassault Falcon 20 (retrofit)
- Learjet 55
- Lockheed 731 Jetstar/Jetstar II
- IAI 1124 Westwind I
- Hawker HS125 series
Data from 
- 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
- Related development
- Comparable engines
- Related lists
- "TFE731". Honeywell.
- Schoneberger, William A.; Scholl, Robert R. H. (1985). Out of Thin Air: Garrett's First 50 Years. Phoenix: Garrett Corporation. p. 205. ISBN 0-9617029-0-7.
- Schoneberger, p. 204.
- "An Historical Look at the TFE731 Engine" (PDF). Duncan Debrief. Summer 2001. p. 11.
- "Honeywell TFE731-50 Turbofan Engine Completes First Flight" (Press release). Honeywell. 2005-05-18. Retrieved 2006-12-05.
- "Gas Turbine Engines" (PDF). Aviation Week & Space Technology Source Book. 2009. p. 119.
- Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. ISBN 0-7509-4479-X.
- Leyes II, Richard A.; William A. Fleming (1999). "10". The History of North American Small Gas Turbine Aircraft Engines. Washington, DC: Smithsonian Institution. ISBN 1-56347-332-1.