Rolls-royce Corporation

Johnathan H Wilshaw

Crispin David Bolgar

A compressor section for a gas turbine engine, the compressor section including a circumferential row of stator vanes, a circumferential row of rotor blades, and a casing arrangement. A row of bleed ports are provided in the casing arrangement. Each of the bleed ports extends radially and is curved such that an outlet of the port is rearward of and is circumferentially offset in a direction of rotation of the rotor blades from an inlet of the port.

Compressor

A gas turbine engine has two connected parts that rotate together during use. The two parts have a tensile loading that acts to separate the two parts in use. The two parts may be neighbouring rotating stages of a gas turbine engine. The two parts are connected together using both a mechanical fastener and an interlocking feature. The interlocking feature may be, for example, interlocking conical surfaces and/or interlocking protrusions.

Connection of rotatable parts

A variable stator vane assemblywhere two downwardly inclined engagement facesare provided on the top of the stator vane upper stem, extending for part of the width thereof. A pair of projectionswith inwardly inclined surfacesare provided on the underside of the lever arm. The surfacesare only engageable with the facesin one axial alignment, and otherwise the lever armwill be raised relative to the stator vaneto clearly indicate incorrect mounting thereon.

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Barlaston, United Kingdom

Johnathan H Wilshaw