Turbomeca Astazou
The Turbomeca Astazou is a wave of the French manufacturer Turbomeca turbine for driving the propeller aircraft with the designation Astazou II of this engine was a version Astazou IIA derived for helicopters. By 1993, more than 2,200 pieces of them were already made and even today (12/ 2007) is still in production. The name comes from two mountain peaks in the Pyrenees.
The original version of the engine, Astazou I ran in 1957 and performed at 40,000 min-1 235 kW. It was approved by a 150 - hour run on May 29, 1961. In charge of the development was G. Sporer.
The single-shaft engine has in its basic configuration, a two-stage compressor, with the first stage operates axially, but the second is performed radially. The combustion occurs in an annular combustion chamber, from where the hot gas hits on a three-stage axial flow turbine. The maximum permissible speed of the turbine had now been increased to 43,500 min -1.
In production engines the reduction gear is mounted in front of the air inlet, which is designed for the propeller speed of 1,800 min -1 2.080 min -1 2.200 min-1 2.400 min-1 or. The output speed in the helicopter engines is 6,000 min -1. The engine is automatically regulated so that only the speed must be set by the pilot.
The Astazou II was used in the Potez 840, the SFERMA Marquis, the Mitsubishi MU- 2 and the Pilatus PC -6 Turbo Porter A. For flight tests, individual aircraft North 1110 and Dornier Do 27 were Astazou engines. With the execution of the IIA helicopter Aérospatiale 318 C Alouette II was a worldwide success.
After the execution of Astazou X a second axial compressor stage was installed. This engine was supplied for the Potez 840. The Astazou XIV and XVI were also Rolls- Royce Turbomeca International Ltd.. distributed under the terms of AZ14 AZ16 respectively. When running Astazou XVIIIA the performance could be increased up to 783 kW. The Aerospatiale / Eurocopter SA 360 Dauphin is so equipped.
The execution XX has a third axial step and thus even higher compression. As a turboprop power of 1075 kW was configured. It was used as XXB in the SA 361H Dauphin and made 1043 kW.
Technical design ( Astazou XVI)
The annular air intake behind the reduction gear has a Heißluftenteisung. The two axial compressor stages of the compressor are made of steel in the blisk technique. The shaft runs in ball bearings. The annular combustion chamber is passed through an S-shape. Fuel is supplied by a rotary atomizer in the radial direction. The blades are also manufactured as a blisk of the three -stage turbine are internally cooled by air. The nozzle is movable and has an inner cone. The auxiliary equipment drives are located on a mounting plate behind the air intake. There connectors for starter generator, oil and fuel pump, speed controller and tachometer are available. It is also possible to apply an alternating current generator and a hydraulic pump. The engine is Suspended by three points, each with a journal left and right at the front of the turbine housing and a. At the bottom in the rear area The power is controlled by varying the injected amount of fuel with automatic speed control. A short-term overload operation is made possible by a thermal monitoring. Lubrication is ensured by a pressure oil supply.
Specifications
Astazou II IIA III C2/N2 X XIV B / F XIV H / M Power KW 390 390 480 465 440 440 Length mm 1810 1427.50 1433.50 1912 1434 1470/1474 Diameter 460 mm Width mm 516 483 520 500 / 460 Height mm 560 508 623.50 565/570 Weight kg 123 142 150.3 128 160 160 Air flow kg / s 2.5 6:1 compression 7.5 swell
- Jane's all the world 's aircraft, various years