Nova Patents
EP1632648A3

Gas turbine flow path

Abstract

The invention relates to a flow structure for a gas turbine, in particular for an aircraft engine, in a transition channel (10) between two compressors or in a transitional channel between two turbines or in a transition duct of a turbine exhaust casing downstream of a low pressure turbine, with in the transition channel (10) positioned in Circumferential direction of the transition channel spaced support ribs (15). According to the invention, a channel wall (19) bounding the transition channel (10) radially inside and / or a channel wall (20) bounding the transition channel (10) radially in the region of the flow outlet edges (17) of the support ribs (15) are inwardly into the transition channel (10) pulled into it.

EP1632648A3, drawing sheet 1
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Term

Term ended

Projected expiry passed 26 August 2025, 1.1 years ago.

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