An engine has a blade stage (10) and a circumferential array of blade outer air seal segments (66). A support ring (70) carries the blade outer air seal segments (66). The support ring (70) has a low-CTE member (72) and a high-CTE member (90) intervening between the blade outer air seal segments (66) and the low-CTE member (72).

Blade clearance control using high-CTE and low-CTE ring members

According to one aspect of the invention, an exhaust gas diffuser (200) includes an outer casing (202) disposed about a center line (205) of the exhaust gas diffuser (200), a hub (204) disposed about the center line (205), and an end portion (214) of the hub (204) comprises a recess (216) configured to cause a flow of exhaust gas toward the center line (205) as the exhaust gas flows in a downstream direction (207).

Exhaust gas diffuser

An example gas turbine engine shroud (28) includes a first annular ceramic wall (30) having an inner side (38) for resisting high temperature turbine engine gases and an outer side (40) with a plurality of radial slots (36). A second annular metallic wall (32) is positioned radially outwardly of and enclosing the first annular ceramic wall and has a plurality of tabs (34) in communication with the slot of the first annular ceramic wall. The tabs of the second annular metallic wall and slots of the first annular ceramic wall are in communication such that the first annular ceramic wall and second annular metallic wall are affixed together.

Ceramic gas turbine shroud

A turbine exhaust section comprises a turbine exhaust case (36) having radially outer (40) and inner (38) ducts defining therebetween an annular exhaust portion for the hot exhaust gases, and an exhaust mixer (32) projecting axially rearwardly from the turbine exhaust case (36) for mixing the hot exhaust gases with a cooler bypass duct flow. The upstream end (44) of the exhaust mixer (32) surrounds a downstream end (46) of the outer duct (40) and defines therewith an axially extending overlap joint with a radial play between the outer duct and the exhaust mixer (32). A sliding attachment in the radial direction is provided between the outer duct (40) and the exhaust mixer (32) for accommodating differences in thermal growth during engine operation. The sliding attachment includes a circumferential array of sliding guides (54) extending radially through the axially extending overlap joint. A resilient sealing ring seals the radial play between the outer duct (40) and the exhaust mixer (32) at the overlap joint.

Exhaust section for bypass gas turbine engines

A flange connection for an exhaust section of a gas turbine engine. The flange connection includes a stub flange attached to an exhaust manifold. The stub flange has a first axial face for engagement with the axial face of a cylinder flange extending radially from an exhaust cylinder. A plate structure attached to the cylinder flange is configured to provide axial retention of the stub flange to the axial face of the cylinder flange. The plate structure includes a resilient beam portion extending radially inwardly and engaging a second axial face of the stub flange. The stub flange is retained between the cylinder flange and the beam portion of the plate structure in an interference fit to provide three degrees of freedom of the stub flange relative to the exhaust cylinder.

Exhaust manifold flange connection

An inner mounting ring ( 20 ) for gas turbine flow path components such as shroud ring segments ( 24 ). The inner ring ( 20 ) may be mounted to an outer ring ( 22 ) on radially slidable mounts ( 26, 28 ) that maintain the two rings ( 20, 22 ) in coaxial relationship, but allows them to thermally expand at different rates. This allows matching of the radial expansion rate of the inner ring ( 20 ) to that of the turbine blade tips ( 32 ), thus providing reduced clearance ( 33 ) between the turbine blade tips ( 32 ) and the inner surface of the shroud ring segments ( 24 ) under all engine operating conditions. The inner ring ( 20 ) may be made of a material with a lower coefficient of thermal expansion than that of the outer ring ( 22 ).

Inner ring with independent thermal expansion for mounting gas turbine flow path components

Aspects of the invention are directed to an interface (10) between an exhaust cylinder (20) and an exhaust diffuser (22) in a turbine engine. The interface (10) allows relative radial movement of the exhaust diffuser (22) and the exhaust cylinder (20). According to aspects of the invention, the diffuser (22) and the cylinder (20) are operatively connected about their peripheries by a plurality of connecting members, which can be tie rods (40). Each connecting member can be pivotally connected at a first end (42) to a joint bolt (80) affixed to the exhaust cylinder (20) and at a second end (44) to an exhaust diffuser (22). Thus, the connecting members can join the cylinder (20) and the diffuser (22) in the axial direction, while allowing for the differential thermal expansion of the two components. Relative circumferential movement between the cylinder (20) and the diffuser (22) can be reduced by positioning neighboring connecting members at opposing angles in relation to one another.

Brian H. Terpos

Papers

Inner ring with independent thermal expansion for mounting gas turbine flow path components

Radially expanding turbine engine exhaust cylinder interface

Exhaust manifold flange connection