Device for supporting a turbine ring, turbine having such a device, and turbine engine having such a turbine

Abstract

A device for supporting a ring of a gas turbine, the ring configured to surround mobile blades of the turbine which are driven by a gas stream flowing upstream to downstream. The device includes at least one upstream hook facing upstream, to be housed in an upstream groove of the ring, opened toward the downstream direction, and at least one downstream hook facing downstream, to be housed in a downstream groove of the ring, opened toward the upstream direction. The hooks are protected and clearances at apexes of the blades are more easily controlled. The device further includes, upstream from the upstream hook, a mechanism injecting cooling gas to cool the upstream hook and / or includes, downstream from the downstream hook, a mechanism injecting a cooling gas to cool the downstream hook.

Description

technical field [0001] The present invention relates to the field of gas turbines, in particular to turbine annuli and their support means. Background technique [0002] Typically, a turboshaft engine for an aircraft such as an airplane or a helicopter comprises, from upstream to downstream in the direction of airflow, a fan, one or more compressor stages (such as a low-pressure compressor and a high-pressure compressor), a combustor, a or multiple turbine stages (eg low pressure turbine and high pressure turbine) and gas exhaust nozzles. A turbine may correspond to a compressor, the two being connected together by a shaft so as to form, for example, a high-pressure plate and a low-pressure plate; A second "free" turbine, which is connected to a shaft, such as that used to drive the rotor of a helicopter (the first turbine connected to the compressor is usually designated as a high pressure turbine). [0003] The phrase "high pressure" will hereinafter be denoted by the ab...

AI Technical Summary

Problems solved by technology

[0010] 4. Significant thermal convection from the airflow, which may be exacerbated when a portion of the flow leaks out of the airflow and reaches the level of the junction between the turbine ring and its supporting parts (these Known air flow or split flow can damage the turbine ring, and also reduce the efficiency of the turbine when these side streams separated from the main air flow do not flow in their normal direction but flow in a bypass)

In particular, the modeling associated with said heat convection is complex due to gas rebreathing outside the flow

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