United Technologies Corporation

Walter J Baran, Jr

Gary F Chaplin

Vincent P Laurello

Roger J Comeau

A manifold (20) includes a plurality of separate, identical flow channels (28) separated by flow dividers (46). The flow dividers (46) include a thickened boss section (54) for receiving a mounting bolt (50), and are skewed adjacent the manifold outlet for forming a plurality of tangentially directed nozzles (18).

Cooling air manifold for a gas turbine engine

A stage of circumferentially disposed turbine stator vane clusters and arcuate, circumferentially disposed segments of a rotor outer air seal disposed on one side of the stator stage is secured to an annular attachment ring which is integral with a surrounding turbine case. The outer seal segments are trapped axially between stator vane clusters and the radially inner ends of arcuate support segments, and are also radially supported thereby. The radially inner ends of the support segments are trapped axially between the stator vane clusters and the annular attachment ring, and are also supported radially thereby. This boltless attachment reduces the number of parts while providing strong radially support and accurate radial location for the seal segments.

Stator vane support assembly

A stator assembly 20 for a gas turbine engine is disclosed. The stator assembly includes an outer case 22 and an array of stator vanes 32 extending inwardly across an annular flow path 18 for working medium gases. The stator assembly includes a duct 34 which engages the stator vanes and which is trapped between a stator vane and a stator element 38 extending inwardly from the outer case. The duct includes a transition piece 78 which extends axially to shield a portion of the stator vane. In one embodiment the duct includes an extension 80 which extends into proximity with an outer air seal assembly 31 to form a cooling air chamber 36 adjacent to the stator element.

Stator assembly for bounding the working medium flow path of a gas

The first stage turbine vanes in a gas turbine are supported both axially and for torque control in a ring located within the diffuser case such that it is free to expand to minimize thermal stresses. The support ring is modified to permit assembly of all the turbines within the ring.

First stage turbine vane support structure

Stator assembly for bounding the flow path of a gas turbine engine

The stator vanes of an axial flow gas turbine are supported by spaced flanges in the surrounding turbine case one of which flanges supports the upstream end of the outer shroud of the vane radially and also serves to position the blade tip seal segments and the surrounding air seal ring. The other flange engages lugs from the vane shroud and also supports clips for the clip seal segments and the upstream edge of the air seal ring.

Turbine stator assembly

A plug for boroscope access hole located in the turbine section viewing from the outside the internal parts of the engine by cooperating holes formed in concentric casings characterized as free floating and sealing the attendant opening in an axial and radial direction.

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South Glastonbury, CT, United States of America

Walter J Baran, Jr