Contents

Honeywell TPE331

Turboprop aircraft engine

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TPE331 / T76
TPE331-14
Type	Turboprop
National origin	United States
Manufacturer	Garrett AiResearch Honeywell Aerospace
First run	1960
Major applications	Fairchild Swearingen Metroliner Mitsubishi MU-2 Rockwell Turbo Commander
Number built	13,500+[1]
Developed into	Garrett TPF351

The Honeywell TPE331 (military designation: T76) is a turboprop engine. It was designed in the 1950s by Garrett AiResearch, and produced since 1999 by successor Honeywell Aerospace. The engine's power output ranges from 575 to 1,650 shaft horsepower (429 to 1,230 kW).^[2][3][4]

Design and development[edit]

Garrett AiResearch designed the TPE331 from scratch in 1959 for the military.^[5] “Designed as a 575-horsepower engine it was not a scaled-down version of a larger engine, as competitors were offering.”^[6] The TPE331 originated in 1961 as a gas turbine (the "331") to power helicopters.^[6] It first went into production in 1963.^[7] More than 700 had been shipped by the end of 1973.^[6] It was designed to be both a turboshaft (TSE331)^[8] and a turboprop (TPE331), but the turboshaft version never went into production. The first engine was produced in 1963, installed on the Aero Commander in 1964 and put into production on the Aero Commander Turbo Commander in June 1965.^{[citation needed]}

Performance[edit]

The 715 shp TPE331-6 used in the Beech King Air B100 have a 400-hr. fuel nozzle cleaning interval, 1,800-hr. hot section inspection interval and a 5,400-hr. time between overhaul; approval is possible for 3,000-hr. HSIs and 6,000-hr. overhauls and engine reserves are cheaper than for the PT6A.^[9]

Variants[edit]

Military variants (T76)[edit]

Commercial variants (TPE331)[edit]

Applications[edit]

Fitted with TPE-331s as a replacement for their original engines[edit]

Specifications[edit]

General characteristics

• Type: Single-shaft turboprop with integral gearbox
• Length: 46 inches (1,200 mm) (TPE331-43A),^[7] 42.82 in (1,088 mm) (TPE331-10)^[22]
• Diameter: 21 inches (530 mm) (TPE331-43A)^[7]
• Dry weight: 336 lb (152 kg) (TPE331-43A),^[7] 385 lb (175 kg) (TPE331-10)^[22]

Components

• Compressor: Two-stage centrifugal
• Combustors: Reverse annular
• Turbine: Three-stage axial
• Fuel type: Jet A, Jet B, Jet A-1, JP-8, JP-1, JP-4, JP-5, JP8+100^[23]

Performance

• Maximum power output: 575 hp (429 kW) (TPE331-43A),^[7] 940 hp (700 kW) (TPE331-10)^[22]
• Overall pressure ratio: 10.55:1 (TPE331-10)^[22]
• Specific fuel consumption: 0.534 lb/(hp⋅h) (325 g/kWh) (TPE331-10)^[22]
• Power-to-weight ratio: 1.71 hp/lb (2.81 kW/kg) (TPE331-43A),^[7] 2.44 hp/lb (4.01 kW/kg) (TPE331-10)^[22]

See also[edit]

Comparable engines

• General Electric Catalyst
• Pratt & Whitney Canada PT6
• Walter M601

Related lists

• List of aircraft engines

References[edit]

Bibliography[edit]

External links[edit]

Wikimedia Commons has media related to Garrett TPE331.

• TPE 331 Cost Protection Programs
• TPE 331 Engine Conversions
• Power and fuel flow versus altitude and speed, for version 10. (Archive)

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