Turbomeca Astazou Explained

The Turbomeca Astazou is a highly successful series of turboprop and turboshaft engines, first run in 1957. The original version weighed 1100NaN0 and developed 240abbr=onNaNabbr=on at 40,000 rpm. It was admitted for aviation service on May 29, 1961, after a 150-hour test run. The main developing engineer was G. Sporer. It was named after two summits of the Pyrenees.

A simplified version was built by Agusta as the Turbomeca-Agusta TA.230.

Design and development

The Astazou IIA version was derived from the original Astazou powerplant for use in helicopters. By 1993, 2,200 had been built. As of 2007, it was still in production. However, many aircraft initially equipped with it, especially the heavier ones, have since been upgraded with more powerful engines.

The early single-shaft Astazou has a two-stage compressor, with the first stage an axial and the second stage a radial design. It has an annular combustion chamber, after which the combustion gases enter a three-stage axial turbine.

Engines have a reduction gearbox in front of the air inlet, with an output speed suitable for a propeller or, for helicopters, as the first stage only of the much bigger reduction required for a rotor. Fuel to the gas generator is adjusted automatically to maintain a constant propeller or rotor speed as blade pitch varies.

As of the Astazou X, the engine received a second axial compressor stage. This was the engine for the Potez 840. The Astazou XIV and XVI were also marketed by Rolls-Royce Turboméca International Ltd under the names AZ14 and AZ16, respectively.

Power was steadily increased over the years, with the Eurocopter Dauphin's dual Astazou XVIII developing 783 kW each. The Astazou XX received a third axial stage, raising compression even further to achieve a projected output of in the turboprop application. The XXB derivative, used in the single engine Aérospatiale SA 361H Dauphin, delivered 1043kW.

Variants

Astazou I:

Astazou II:Single-stage axial plus single-stage centrifugal compressor, annular combustor, three-stage turbine

Astazou IIA:

Astazou III:

Astazou IIIA:

Astazou IIIC:

Astazou IIIC2:

Astazou IIIN:

Astazou IIIN2:

Astazou VI:Coupled Astazou

Astazou X:The X and subsequent engines had a second axial compressor stage added.

Astazou XII:

Astazou XIV:Two-stage axial plus single-stage centrifugal compressor, annular combustor, three-stage turbine. Integral front mountedgearbox.

Astazou XIVA:

Astazou XIVB:

Astazou XIVD:

Astazou XIVC:

Astazou XIVH:

Astazou XIVM:

Astazou XVI:

Astazou XVIG:

Astazou XVIII:

Astazou XVIIIA:

Astazou XX:A third axial compressor stage added for increased pressure ratio.

Astazou XXB:

Turbomeca-Agusta TA.230:(aka TAA-230)A simplified version built by Agusta.^[1]

Rolls-Royce Turbomeca AZ14: The Astazou XIV marketed by Rolls-Royce Turbomeca International Ltd as the AZ14

Rolls-Royce Turbomeca AZ16: The Astazou XVI marketed by Rolls-Royce Turbomeca International Ltd as the AZ16

Applications

Fixed-wing aircraft

• Dassault Communauté
• Dassault MD320 Hirondelle 2x Astazou XIV 860abbr=onNaNabbr=on equivalent.
• Dornier Do27T-l 2x Astazou II 562abbr=onNaNabbr=on equivalent.
• FMA IA 58 Pucará 2x Astazou XVIG 956abbr=onNaNabbr=on equivalent.
• Handley Page HP.137 Jetstream 2x Astazou XIVC 921abbr=onNaNabbr=on equivalent.
• Mitsubishi MU-2
• Nord Noralpha
• Pilatus PC-6/A1-H2 Turbo Porter lx Astazou XII 731abbr=onNaNabbr=on equivalent.
• Potez 840 4x 440shp (328 kW) Turboméca Astazou II
• Potez 842 4x 600shp (447 kW) Turboméca Astazou XII
• SFERMA Nord 1110
• SFERMA SF-60 Marquis 2x Astazou X
• SFERMA PD-146 Marquis 2x Astazou IIA
• Short SC.7 Skyvan series II 2x Astazou XII 731abbr=onNaNabbr=on equivalent.
• SIPA S-2510 Antilope
• IAI Arava 2x Astazou XIV 850abbr=onNaNabbr=on equivalent.
• UV-23A Dominion Skytrader 2x Turboméca Astazou XIV

Helicopters

• Aérospatiale SA.3180 Alouette II Astazou 1x Astazou IIA 523abbr=onNaNabbr=on (but restricted to 400abbr=onNaNabbr=on by rotor transmission).
• Aérospatiale SA.319B Alouette III 1x Astazou XIVB 590abbr=onNaNabbr=on.
• Aérospatiale Gazelle 1x Astazou IIIN 592abbr=onNaNabbr=on equivalent.
• Aérospatiale Gazelle AH.1 1x Astazou IIIN2^[2]
• Agusta A.105
• Agusta A.106
• Agusta A.115
• Aérospatiale SA 360 Dauphin
• Dechaux Helicop-Jet 1x Astazou II

Specifications (Astazou XVI)

Parameter	II^[3]	IIA	IIIC2/N2	X	XIVB/F	XIVH	XIVM	XVI
Max output	390abbr=onNaNabbr=on	390abbr=onNaNabbr=on	480abbr=onNaNabbr=on	465abbr=onNaNabbr=on	440abbr=onNaNabbr=on	440abbr=onNaNabbr=on	440abbr=onNaNabbr=on
Length	1810abbr=onNaNabbr=on	1427.5abbr=onNaNabbr=on	1433.5abbr=onNaNabbr=on	1912abbr=onNaNabbr=on	1434abbr=onNaNabbr=on	1470abbr=onNaNabbr=on	1474abbr=onNaNabbr=on
Diameter	460abbr=onNaNabbr=on	460abbr=onNaNabbr=on	460abbr=onNaNabbr=on	460abbr=onNaNabbr=on	460abbr=onNaNabbr=on	460abbr=onNaNabbr=on	460abbr=onNaNabbr=on
Width		516abbr=onNaNabbr=on	483abbr=onNaNabbr=on		520abbr=onNaNabbr=on	500abbr=onNaNabbr=on	460abbr=onNaNabbr=on
Height		560abbr=onNaNabbr=on	508abbr=onNaNabbr=on		623.5abbr=onNaNabbr=on	565abbr=onNaNabbr=on	570abbr=onNaNabbr=on
Weight	123abbr=onNaNabbr=on	142abbr=onNaNabbr=on	150.3abbr=onNaNabbr=on	128abbr=onNaNabbr=on	160abbr=onNaNabbr=on	160abbr=onNaNabbr=on	160abbr=onNaNabbr=on
Air mass flow	2.5abbr=onNaNabbr=on/sec
Pressure ratio	6:1			7.5:1	8:1	8:1	8:1	8.15:1

Further reading

• Book: Gunston, Bill . World Encyclopedia of Aero Engines . 1986 . Patrick Stephens . Wellingborough . 164 .

Notes and References

1. Book: Wilkinson, Paul H. . Aircraft engines of the World 1964/65 . 1964 . Sir Isaac Pitman & Sons Ltd. . London . 20th . 186.
2. Web site: Aircraft . www.army.mod.uk . 24 March 2019.
3. Book: Taylor, John W.R. FRHistS. ARAeS. Jane's All the World's Aircraft 1962-63. 1962. Sampson, Low, Marston & Co Ltd. London.