fbpx
Wikipedia

Turbomeca Astazou

January 01, 1970

The Turbomeca Astazou is a highly successful series of turboprop and turboshaft engines, first run in 1957. The original version weighed 110 kg (243 lb) and developed 240 kW (320 shp) 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.

Astazou
Turbomeca Astazou IIA on an SA 318C Alouette II
Type Turboshaft/Turboprop
National origin France
Manufacturer Turbomeca
First run 1957
Major applications Aérospatiale Gazelle
Handley Page Jetstream
FMA IA 58 Pucará

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

Design and development edit

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.

 
Handley Page HP.137 Jetstream, with twin Astazou XIV, showing the distinctive annular air inlet and long reduction gear housing

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 1,075 kW (1,442 hp) in the turboprop application. The XXB derivative, used in the single engine Aérospatiale SA 361H Dauphin, delivered 1,043 kW (1,399 shp).

Variants edit

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 1,100 kW (1,480 shp)
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 mounted

gearbox.

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 edit

Fixed-wing aircraft edit

Helicopters edit

Specifications (Astazou XVI) edit

Data from Aircraft engines of the World 1970[3]

General characteristics

  • Type: Turboprop
  • Length: 2,000 mm (79 in) including propeller
  • Diameter: 546 mm (21.5 in)
  • Frontal area: 0.23 m2 (2.5 sq ft)
  • Dry weight: 206 kg (454 lb)

Components

  • Compressor: 2-stage axial + 1-stage centrifugal
  • Combustors: Annular combustion chamber
  • Turbine: 3-stage axial turbine
  • Fuel type: Aviation Kerosene such as Jet A-1, JP-4 and JP-5
  • Oil system: Pressure spray at 3.0 bar (44 psi) with scavenge

Performance

  • Maximum power output:
  • Take-off power: 811 kW (1,088 shp) (equivalent) (766 kW (1,027 shp) + 0.67 kN (150 lbf)) at 43,000 rpm (static)
  • Max. Continuous power: 743 kW (996 shp) (equivalent) (699 kW (937 shp) + 0.64 kN (145 lbf)) at 43,000 rpm (static)
  • Overall pressure ratio: 8.15:1
  • Air mass flow: 3.35 kg/s (443 lb/min) at 43,000 rpm
  • Specific fuel consumption: 0.30 kg/kWh (0.5 lb/(hp⋅h)) (equivalent)
  • Power-to-weight ratio: 3.9 kW/kg (2.4 hp/lb) (equivalent)
Parameter II[4] IIA IIIC2/N2 X XIVB/F XIVH XIVM XVI[3]
Max output 390 kW (523 shp) 390 kW (523 shp) 480 kW (644 shp) 465 kW (624 shp) 440 kW (590 shp) 440 kW (590 shp) 440 kW (590 shp) 811 kW (1,088 shp)
Length 1,810 mm (71.3 in) 1,427.5 mm (56.2 in) 1,433.5 mm (56.4 in) 1,912 mm (75.3 in) 1,434 mm (56.5 in) 1,470 mm (57.9 in) 1,474 mm (58.0 in) 2,000 mm (79 in)
Diameter 460 mm (18.1 in) 460 mm (18.1 in) 460 mm (18.1 in) 460 mm (18.1 in) 460 mm (18.1 in) 460 mm (18.1 in) 460 mm (18.1 in) 546 mm (21.5 in)
Width 516 mm (20.3 in) 483 mm (19.0 in) 520 mm (20.5 in) 500 mm (19.7 in) 460 mm (18.1 in)
Height 560 mm (22.0 in) 508 mm (20.0 in) 623.5 mm (24.5 in) 565 mm (22.2 in) 570 mm (22.4 in)
Weight 123 kg (271.2 lb) 142 kg (313.1 lb) 150.3 kg (331.4 lb) 128 kg (282.2 lb) 160 kg (352.7 lb) 160 kg (352.7 lb) 160 kg (352.7 lb) 206 kg (454 lb)
Air mass flow 2.5 kg (5.5 lb)/sec 3.35 kg/s (443 lb/min)
Pressure ratio 6:1 7.5:1 8:1 8:1 8:1 8.15:1

See also edit

Related development

Related lists

References edit

  1. ^ Wilkinson, Paul H. (1964). Aircraft engines of the World 1964/65 (20th ed.). London: Sir Isaac Pitman & Sons Ltd. p. 186.
  2. ^ "Aircraft". www.army.mod.uk. Retrieved 24 March 2019.
  3. ^ a b Wilkinson, Paul H. (1970). Aircraft engines of the World 1970 (21st ed.). Washington D.C.: Paul H. Wilkinson. p. 182.
  4. ^ Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.

Further reading edit

 
Wikimedia Commons has media related to Turbomeca Astazou.
  • Gunston, Bill (1986). World Encyclopedia of Aero Engines. Wellingborough: Patrick Stephens. p. 164.

January 01, 1970
turbomeca, astazou, this, article, includes, list, general, references, lacks, sufficient, corresponding, inline, citations, please, help, improve, this, article, introducing, more, precise, citations, july, 2011, learn, when, remove, this, message, highly, su. This article includes a list of general references but it lacks sufficient corresponding inline citations Please help to improve this article by introducing more precise citations July 2011 Learn how and when to remove this message The Turbomeca Astazou is a highly successful series of turboprop and turboshaft engines first run in 1957 The original version weighed 110 kg 243 lb and developed 240 kW 320 shp 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 Astazou Turbomeca Astazou IIA on an SA 318C Alouette II Type Turboshaft Turboprop National origin France Manufacturer Turbomeca First run 1957 Major applications Aerospatiale GazelleHandley Page JetstreamFMA IA 58 Pucara A simplified version was built by Agusta as the Turbomeca Agusta TA 230 Contents 1 Design and development 2 Variants 3 Applications 3 1 Fixed wing aircraft 3 2 Helicopters 4 Specifications Astazou XVI 4 1 General characteristics 4 2 Components 4 3 Performance 5 See also 6 References 7 Further readingDesign and development editThe 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 nbsp Handley Page HP 137 Jetstream with twin Astazou XIV showing the distinctive annular air inlet and long reduction gear housing 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 Turbomeca 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 1 075 kW 1 442 hp in the turboprop application The XXB derivative used in the single engine Aerospatiale SA 361H Dauphin delivered 1 043 kW 1 399 shp Variants editAstazou 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 1 100 kW 1 480 shp 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 mounted gearbox 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 AZ16Applications editFixed wing aircraft edit Dassault Communaute Dassault MD320 Hirondelle 2x Astazou XIV 640 kW 860 hp equivalent Dornier Do27T l 2x Astazou II 419 kW 562 hp equivalent FMA IA 58 Pucara 2x Astazou XVIG 713 kW 956 hp equivalent Handley Page HP 137 Jetstream 2x Astazou XIVC 687 kW 921 hp equivalent Mitsubishi MU 2 Nord Noralpha Pilatus PC 6 A1 H2 Turbo Porter lx Astazou XII 545 kW 731 hp equivalent Potez 840 4x 440shp 328 kW Turbomeca Astazou II Potez 842 4x 600shp 447 kW Turbomeca 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 545 kW 731 hp equivalent SIPA S 2510 Antilope IAI Arava 2x Astazou XIV 630 kW 850 hp equivalent UV 23A Dominion Skytrader 2x Turbomeca Astazou XIV Helicopters edit Aerospatiale SA 3180 Alouette II Astazou 1x Astazou IIA 390 kW 523 hp but restricted to 300 kW 400 hp by rotor transmission Aerospatiale SA 319B Alouette III 1x Astazou XIVB 440 kW 590 hp Aerospatiale Gazelle 1x Astazou IIIN 441 kW 592 hp equivalent Aerospatiale Gazelle AH 1 1x Astazou IIIN2 2 Agusta A 105 Agusta A 106 Agusta A 115 Aerospatiale SA 360 Dauphin Dechaux Helicop Jet 1x Astazou IISpecifications Astazou XVI editData from Aircraft engines of the World 1970 3 General characteristics Type Turboprop Length 2 000 mm 79 in including propeller Diameter 546 mm 21 5 in Frontal area 0 23 m2 2 5 sq ft Dry weight 206 kg 454 lb Components Compressor 2 stage axial 1 stage centrifugal Combustors Annular combustion chamber Turbine 3 stage axial turbine Fuel type Aviation Kerosene such as Jet A 1 JP 4 and JP 5 Oil system Pressure spray at 3 0 bar 44 psi with scavenge Performance Maximum power output Take off power 811 kW 1 088 shp equivalent 766 kW 1 027 shp 0 67 kN 150 lbf at 43 000 rpm static Max Continuous power 743 kW 996 shp equivalent 699 kW 937 shp 0 64 kN 145 lbf at 43 000 rpm static Overall pressure ratio 8 15 1 Air mass flow 3 35 kg s 443 lb min at 43 000 rpm Specific fuel consumption 0 30 kg kWh 0 5 lb hp h equivalent Power to weight ratio 3 9 kW kg 2 4 hp lb equivalent Parameter II 4 IIA IIIC2 N2 X XIVB F XIVH XIVM XVI 3 Max output 390 kW 523 shp 390 kW 523 shp 480 kW 644 shp 465 kW 624 shp 440 kW 590 shp 440 kW 590 shp 440 kW 590 shp 811 kW 1 088 shp Length 1 810 mm 71 3 in 1 427 5 mm 56 2 in 1 433 5 mm 56 4 in 1 912 mm 75 3 in 1 434 mm 56 5 in 1 470 mm 57 9 in 1 474 mm 58 0 in 2 000 mm 79 in Diameter 460 mm 18 1 in 460 mm 18 1 in 460 mm 18 1 in 460 mm 18 1 in 460 mm 18 1 in 460 mm 18 1 in 460 mm 18 1 in 546 mm 21 5 in Width 516 mm 20 3 in 483 mm 19 0 in 520 mm 20 5 in 500 mm 19 7 in 460 mm 18 1 in Height 560 mm 22 0 in 508 mm 20 0 in 623 5 mm 24 5 in 565 mm 22 2 in 570 mm 22 4 in Weight 123 kg 271 2 lb 142 kg 313 1 lb 150 3 kg 331 4 lb 128 kg 282 2 lb 160 kg 352 7 lb 160 kg 352 7 lb 160 kg 352 7 lb 206 kg 454 lb Air mass flow 2 5 kg 5 5 lb sec 3 35 kg s 443 lb min Pressure ratio 6 1 7 5 1 8 1 8 1 8 1 8 15 1See also editRelated development Turbomeca Aspin Turbomeca Astafan Related lists List of aircraft enginesReferences edit Wilkinson Paul H 1964 Aircraft engines of the World 1964 65 20th ed London Sir Isaac Pitman amp Sons Ltd p 186 Aircraft www army mod uk Retrieved 24 March 2019 a b Wilkinson Paul H 1970 Aircraft engines of the World 1970 21st ed Washington D C Paul H Wilkinson p 182 Taylor John W R FRHistS ARAeS 1962 Jane s All the World s Aircraft 1962 63 London Sampson Low Marston amp Co Ltd Further reading edit nbsp Wikimedia Commons has media related to Turbomeca Astazou Gunston Bill 1986 World Encyclopedia of Aero Engines Wellingborough Patrick Stephens p 164 Retrieved from https en wikipedia org w index php title Turbomeca Astazou amp oldid 1160199251, wikipedia, wiki, book, books, library,

article

, read, download, free, free download, mp3, video, mp4, 3gp, jpg, jpeg, gif, png, picture, music, song, movie, book, game, games.