Turbine blade clearance control system

F - Mech Eng,Light,Heat,Weapons – 01 – D

Patent

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Details

F01D 11/24 (2006.01)

Patent

CA 2210428

Past gas turbine engines have been manufactured with a variety of systems which have attempted to compensate for the varying radial clearance or interface between a tip of a turbine blade and a surrounding shroud. Such systems have engineered in large clearances, utilized special tips on blades and provided abradable structures. The present system controls a radial clearance or an interface or spaced distance between a tip of a blade and a stationary shroud. The system includes an introduction of a cool fluid or a hot fluid flow or a combination of cool fluid and hot fluid into a support case cavity. The flow is controlled by modulating a flow control apparatus and controlling the expansion of a nozzle support case and a stationary shroud relative to the position of the tip of the turbine blade. The system improves efficiency, longevity and operation of the gas turbine engine.

Les moteurs à turbine à gaz antérieurs comportaient toute une gamme de solutions visant à compenser les variations de jeu radial entre les bouts des ailettes et l'enveloppe de la turbine. Parmi elles figuraient la solution d'un jeu en bout d'ailette généreux, l'utilisation de bouts d'ailette spéciaux ou encore d'éléments abradables. La solution objet de l'invention permet de réguler le jeu radial entre les bouts d'ailette et une enveloppe fixe. Elle fait appel à l'introduction d'un fluide froid, d'un fluide chaud ou d'une combinaison de fluide chaud et de fluide froid dans une cavité de bâti-tuyère. Le débit est régulé par un modulateur et en contrôlant la dilatation du bâti-tuyère et de l'enveloppe fixe par rapport à la position du bout d'ailette de turbine. Cette solution améliore l'efficacité, la longévité et le fonctionnement du moteur à turbine à gaz.

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