Turbine with contra-rotating turbine for aircraft

Abstract

A turbine (10) with a counter rotating turbine for an aircraft, the turbine comprising a counter rotating turbine (22), a first rotor (22a) of the counter rotating turbine being configured to rotate in a first direction of rotation and connected to a first turbine shaft (36), a second rotor (22b) of the counter rotating turbine being configured to rotate in an opposite direction of rotation and connected to a second turbine shaft (38), the first rotor comprises turbine discs staggered between turbine discs of the second rotor, said first shaft (36) being guided by at least two guide bearings (60, 62) mounted between the first shaft and the stator housing, and said second shaft (38) being guided by at least two guide bearings (56, 58) mounted between the second shaft and the other stator housing (28).

Description

technical field [0001] The present invention relates to a turbine with a counter-rotating turbine for an aircraft. Background technique [0002] In particular, the prior art includes documents US-A1-2019 / 085701, EP-A1-3 447 243, EP-A1-2 975213 and WO-A1-2013 / 147977. [0003] Typically, an aircraft's turbine includes a fan, a low-pressure compressor, a high-pressure compressor, an annular combustor, a high-pressure turbine, and a low-pressure turbine from upstream to downstream in the direction of gas flow. The rotor of the low pressure compressor is driven by the rotor of the low pressure turbine, and the rotor of the high pressure compressor is driven by the rotor of the high pressure turbine. [0004] Maximizing the rotational speed of the low pressure turbine is advantageous from an engine performance and fuel consumption point of view, as this results in a higher efficiency of the turbine. However, increasing the speed of the turbine means increasing the centrifugal fo...

AI Technical Summary

Problems solved by technology

[0009] The architecture is complex due to its mechanical integration: the mechanical reduction gear is located downstream of the turbine, radially inside the stator casing (known as the exhaust casing)

[0010] Existing integrated solutions are particularly complex due to the presence of many inter-shaft bearings which are particularly difficult to lubricate

The radial load of the turbine is likely to pass through the gearbox holding the two shafts radially, which is extremely detrimental to the good performance of the reduction unit

Finally, the space requirements are not optimized, especially in the presence of bearings below the planetary or sun gears of the reduction unit, which limits the radial integration of the reduction unit

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