United Technologies Corporation

Francis L DeTolla

Gary F Chaplin

Henry Bispham Brown

James G Griffin

Gary J Vollinger

Eugene Cantor

Bertrand Hirsch Brown

Dale Robert Reilly

A seal member for a gas turbine engine is disclosed. Various construction details which ensure an adequate fatigue life and increase the sealing effectiveness of the member during engine operation are developed. A metal diaphragm extends from a nonrotating structure inwardly of the engine flow path to engage the stator vanes at engine operating temperature.

Temperature actuated turbine seal

A support structure for an outer air seal of a gas turbine engine is disclosed. Various construction details which improve the sealing effectiveness of the outer air seal are developed. The outer air seal is held in close proximity to the rotor blades by the circumferentially adjacent support segments.

Outer air seal support structure for gas turbine engine

Methods and apparatus for controlling the radial clearance between the rotor and stator elements in the turbine section of a gas turbine engine is disclosed. A cooling air valve is operatively disposed at the upstream end of the turbine section to control the admission of cooling air to the turbine in response to engine operating temperatures. In one specific embodiment the thermal growth of the case and the stator elements supported thereby is controlled by the valve. At low power conditions the case and the supported elements grow radially with the rotor in response to increasing gas path temperatures. At elevated conditions cooling air is flowable to the case to retard the thermal growth of the case and allow the rotor to grow radially toward the stator elements.

Method and apparatus for controlling stator thermal growth

Apparatus for cooling the nozzle guide vanes in the turbine section of a gas turbine engine is disclosed. A plurality of guide vanes is cantilevered from the turbine case and extends radially inward across the path of working medium gases flowing through the turbine. A ring which is deformable in response to pressure forces is disposed between the vanes and the turbine case forming an annular chamber from which air is metered to the vanes during operation of the engine for cooling. In one embodiment platform cavities and airfoil cavities are alternately disposed between the vanes and the ring to isolate airfoil cooling air from platform cooling air.

Turbine cooling

Apparatus forming a portion of the outer wall of the flow path for working medium gases in the turbine section of a gas turbine engine is disclosed. The vanes of each turbine stage are grouped into a plurality of vane clusters which are circumferentially disposed in adjacent relationship about the flow path. A shroud which surrounds the tips of the rotor blades immediately upstream of the vane clusters is segmented in integral ratio to the number of vane clusters. The gap between each pair of adjacent vane clusters is circumferentially positioned in axial alignment with one of the gaps between adjacent shroud segments.

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Vernon, CT, United States of America

Francis L DeTolla