United Technologies Corporation

Vincent P Laurello

Gary F Chaplin

Robert F Brodell

Walter J Baran, Jr

A coolant system uses a first quantity of high temperature air at cruise power and a second larger quantity of cooler air at high power. Relatively high rotating clearances are achieved at high power and low clearance achieved at cruise power.

Turbine cooling and thermal control

Thrust balance in a gas turbine engine of the thrust balance seal is modulated by judiciously locating a seal between the inner diffuser case and the rear of the high compressor rotor shaft and bleeding air out of the cavity between both seals. The bled air is utilized to cool a portion of the high pressure turbine rotor. Cool air bled from mid-stage compressor is fed downstream of the second seal to cool the bearing compartment.

Thrust balancing and cooling system

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 structure 34 for supporting an outer air seal 46 is disclosed. Various construction details which adapt the stator structure to evenly move inward and outward in response to the impingement of cooling air are developed. In one embodiment an upstream support ring and a downstream support ring for the outer air seal are attached together.

Stator structure for supporting an outer air seal in a gas turbine engine

A stator structure 88 for supporting a pair of outer air seals 62, 72 and an array of stator vanes 82 from two axial locations A.sub.1, A.sub.2 on a coolable outer case is disclosed. Various construction details which enable the structure to respond to the movement of coolable rails are disclosed. In one embodiment, a pair of support rings 96, 100 and a pair of support rings 122, 124 extend between the outer case and the outer air seal and array of stator vanes 82.

Stator structure for a gas turbine engine

A gas turbine engine has conduits leading from the compressor to the turbine for bleeding a portion of compressor air through the turbine blades for cooling or other purposes. A radial pump in the conduits formed by a tangential accelerator and a rotating diffuser transmits the air from the non-rotating environment in the engine to the rotating environment of the turbine rotor. The tangential accelerator accelerates the bleed air to a tangential speed higher than that of the rotor, and the radial diffuser is designed to recover the dynamic pressure or relative velocity of the air over the rotor.

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Guilford, CT, United States of America

Vincent P Laurello