Garrett ATF3

The GarrettAiResearch ATF3 ( military designation F104 GarrettAiResearch ) is a turbofan engine of the U.S. producer Garrett AiResearch. It was the first Dreiwellenturbofantriebwerk that was developed in the United States and is characterized by a multiple reversal of the gas flow in the engine. The bypass ratio is 2.88.

The development was conducted by AiResearch in Torrance. 1966 Design and construction were completed. First test runs with a demonstrator were conducted in 1968 and concluded with the U.S. Air Force a delivery contract for the ATF3. First flight tests could take place in 1972 with Vorserienturbinen that provided 18 kN thrust.

In May 1976, the Company announced that the HU -25 should be equipped with the ATF -3. The prerequisite for this was created with the approval of Civil Aviation in 1979.

In addition to the HU -25, the engine was also incorporated into the French aircraft type Dassault Dassault Falcon 200 Gardian and, all of a series. Furthermore, it served as a drive in the Northrop Tacit Blue, and was intended for Ryan YQM - 98A Drone from the Compass Cope program.

The gas flow deviates from the usual pattern in a turbofan engine starting. On the flow rate by a fan and intermediate-pressure compressor, the combustion air is passed through eight -pressure pipes to the engine rear, where it is deflected by 180 °, flows through a radial high-pressure stage from the inside outwards and then enters into a cross-sectionally S-shaped combustion chamber having a short length at the same time large flame length results. Then, the flow enters the combustion chamber twice by 180 °, the direction such that the turbine is traversed opposite to the gas discharge direction.

The hot gas then passes successively the axial turbines for high -pressure compressor, fan and medium-pressure part. It is then deflected again by 180 ° in center comes out about engine, where it mixes with the air flow of the fans to be in a nozzle which extends to the rear, is expanding. In a large tail cone at the rear core engine are all auxiliary equipment.

A total of five versions of the engine were prepared:

The XF104 - GA- 100 for Ryan YQM - 98A with 18 kN thrust, which with ATF3 -6- 2C and -4C with a 36 -blade fan and an aluminum gear housing for the HU -25, the ATF3 -6A -3C a 30 -blade fan and an aluminum gear housing for the French Dassault Gardian and ATF3 -6A -4C, corresponding to the 3C, but a magnesium gear housing and has been used for the Dassault Falcon 200.

The total number of engines delivered to customers amounted to 227

Technical data ( ATF3 -6)

  • Air flow: 73.5 kg / s
  • Pressure ratio: 21:1 on the ground, 25:1 at high altitude
  • Bypass ratio: 2,88:1
  • Fan: single-stage, axial, titanium
  • MD compressor: five-stage, axial, titanium
  • HP compressor: single-stage, radial, titanium
  • HP turbine ( for HP-compressor ): single-stage axial
  • IP turbine ( for fan ): three-stage axial
  • LP turbine ( for MD - compressor ): two-stage axial
  • Length: 2316 mm
  • Diameter: 853 mm
  • Weight: 431 kg
  • Off thrust: 22.46 kN
Torrance, California General Electric J85 General Electric F101 General Electric F110 Rolls-Royce Spey General Electric F118 Williams F121 General Electric F404 General Electric F414
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