Abstract: An improved rotary labyrinth seal such as may be used in a gas turbine engine. The seal includes a rotor with at least one seal tooth and a stator with an abradable shroud and casing. The first and second members cooperate to inhibit the flow of fluid therebetween. The improvement comprises a conduit for conducting a portion of the fluid through the casing for heat transfer between the fluid and second member. In this manner, the thermal response of the stator is improved.

Abstract: A system is provided inside a turbomachine for controlling operational clearance between a turbine rotor and a surrounding turbine shroud. The system comprises a plurality of control rings, integrated into the turbine casing, that are thermally expanded and contracted to control radial positioning of the turbine shroud. Compressor air is directed through internal passages in the rings to cause the expansion and contraction. The system utilizes the pressure and temperature of compressor air, in combination with size, location, and structure of the control rings to match thermal growth of the control rings and turbine shroud to thermal growth of the turbine rotors, thereby controlling clearance.

Abstract: A fluid-cooled element for partially defining hot gas flow passage extending upstream and downstream of a minimum area throat. A serpentine conduit of fluid communication with a coolant source routes cooling fluid within the downstream portion of the element wall bounding the hot gas passage to an internal pocket upstream of the throat. The coolant is thereafter exhausted upstream of the throat as a film over the wall. The upstream wall portion is cooled by the known impingement and film-cooling technique resulting in an element wherein all of the coolant enters the hot gas passage in a low Mach number region upstream of the throat, thereby minimizing momentum losses due to mixing. In the preferred embodiment, the passage throat is defined by a plurality of turbine nozzle vanes, the fluid-cooled element comprising a nozzle band thereof.

Abstract: An apparatus is provided in a gas turbine engine for eliminating air leakage-induced vibration at natural frequencies in a type of flexible annular seal structure sometimes referred to as a floating fishmouth seal. A floating fishmouth seal has male and female sections arranged to permit axial and radial movement and still maintain a sealing relationship. In a preferred form, the apparatus for eliminating air leakage-induced vibration includes two structures that interact with the male and female sections of the fishmouth seal during engine operation. The first structure is an annular leaf spring assembly that presses a radial flange of the male section of the seal against a stationary wall to obtain frictional damping. The second structure is an annular member attached to an outer surface of the female section of the seal forming a closed-in structure to provide stability and damping. The combined effect of the two structures is to increase the operational life of the fishmouth seal.

Abstract: A high temperature turbine shroud assembly for an aircraft gas turbine engine comprising a plurality of arcuate ceramic blocks arranged in a ring. The blocks are supported by a pair of annular support members which retain the blocks in the assembly. Spring-like fingers associated with the support members apply a preloaded force against a pair of slanted dovetail surfaces on the blocks to force the blocks against rigid stops formed upon the annular support members, thereby establishing their proper radial position within the assembly. The preload applied by the fingers accommodates the thermal expansion differences between the ceramic blocks and the metallic support members. In an alternative embodiment, the blocks are retained between cooperating rigid legs extending from the annular support members and wedged radially inwardly into position by a preloaded spring contacting the back side of the blocks.

Abstract: A cooling slot for passing cooling fluid through a heated plate such as an airfoil blade for use in gas turbine engines is created by forming a first plurality of passages within the blade, and then forming a second plurality of passages within the blade, wherein preselected of the passages of the second plurality intersect at least one of the passages of the first plurality to define a number of nodes between the points of intersection. When cooling fluid is passed through the blade, the nodes act as turbulence promoters and area increasers for improving convective heat transfer between the blade and the cooling fluid.This is a divisional application of application Ser. No. 219,005 now U.S. Pat. No. 3,819,295 issued June 25, 1974 filed Sept. 21, 1972 and assigned to the assignee of the present invention.