MECHANICAL FLANGE JOINT FOR A GAS TURBINE ENGINE

A joint for a gas turbine engine to reduce thermal gradients across the joints component parts includes, an annular component such as an inner nozzle support (66) having an annular, radially-extending flange 68; an annular second component such as a diffuser having an annular, radially-extending sec...

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Bibliographische Detailangaben
Hauptverfasser: SASIKUMAR MUTHUSAMY, PAUL ALEXANDER INTEMANN, RYAN MICHAEL JASKO, JARMO TAPANI MONTTINEN, KENNETH EDWARD SEITZER
Format: Patent
Sprache:eng
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Beschreibung
Zusammenfassung:A joint for a gas turbine engine to reduce thermal gradients across the joints component parts includes, an annular component such as an inner nozzle support (66) having an annular, radially-extending flange 68; an annular second component such as a diffuser having an annular, radially-extending second flange 64 abutting the first flange 68; a plurality of generally radially-extending channels 80,75 passing through at least one of the flanges; a plurality of generally axially-extending channels 92 extending through the second flange 64 and communicating with one of the radial channels 80,75; and a plurality of bolts 74 clamping the flanges together. The exterior surfaces of the annular components are exposed to high temperature gases which can pass from the exterior through the central components of the flange and exit via the axial channels 90. Tabs 104 connected to the fasteners 74 may deflect the flow of hot gas as it exits the axial channels.