Siemens Energy, Inc.

David Charles Radonovich

Anthony L Schiavo

Malberto Gonzalez

Douglas A Keller

Jay Alan Morrison

Gary Brian Merrill

Steven James Vance

Stefan Mazzola

Kuangwei Huang

An apparatus includes a metal shell () surrounding a body () that is made of a ceramic matrix composite (CMC) material () The metal shell defines a space () adapted to contain the body and includes at least one protrusion () adapted to contact the body. A compliant porous element () is adapted to fit in the space between the metal shell and the body. A preload spring () is provided in an urging orientation with the body wherein the preload spring is positioned against a first region () of the body and is adapted to urge the body toward one of the protrusions positioned against a second region () generally opposite the first region, and also to preload the compliant porous element. One of the protrusions may be a hard stop, and in the preload, one of the protrusions may be loaded.

Apparatus comprising a CMC-comprising body and compliant porous element preloaded within an outer metal shell

A metal vane core or strut () is formed integrally with an outer backing plate (). An inner backing plate () is formed separately. A spring () with holes () is installed in a peripheral spring chamber () on the strut. Inner and outer CMC shroud covers () are formed, cured, then attached to facing surfaces of the inner and outer backing plates (). A CMC vane airfoil () is formed, cured, and slid over the strut (). The spring () urges continuous contact between the strut () and airfoil (), eliminating vibrations while allowing differential expansion. The inner end () of the strut is fastened to the inner backing plate (). A cooling channel () in the strut is connected by holes () along the leading edge of the strut to peripheral cooling paths () around the strut. Coolant flows through and around the strut, including through the spring holes.

CMC vane assembly apparatus and method

Aspects of the invention are directed to a ring seal segment having a base portion and a frame portion. The base portion and the frame portion are a unitary structure. The frame portion is made of four unitary side walls: a forward wall, an aft wall and a pair of transverse side walls. The side walls can be arranged in a rectangular configuration. At least a part of the base portion can be coated with a thermal insulating material. A ring seal segment according to aspects of the invention is well suited to withstand the expected operational loads in the turbine section. The transverse side walls can provide bending strength to the base and can strengthen the forward and aft side walls. Transition regions between the side walls and the base portion are strengthened by three perpendicular planes that cooperate to provide structural strength to the ring seal segment.

Ceramic matrix composite turbine engine components with unitary stiffening frame

A ceramic ring segment for a turbine engine that may be used as a replacement for one or more metal components. The ceramic ring segment may be formed from a plurality of ceramic plates, such as ceramic matrix composite plates, that are joined together using a strengthening mechanism to reinforce the ceramic plates while permitting the resulting ceramic article to be used as a replacement for components for turbine systems that are typically metal, thereby taking advantage of the properties provided by ceramic materials. The strengthening mechanism may include a bolt or a plurality of bolts designed to prevent delamination of the ceramic plates when in use by keeping the ceramic plates in compression.

Stacked laminate bolted ring segment

A CMC wall (F) may be attached to a metal wall (F) by a plurality of bolts (A,B,C) passing through respective holes (A,B,C) in the CMC wall (F) and holes in the metal wall (F), clamping the walls (F,F) together with a force that allows sliding thermal expansion but does not allow vibrational shifting. Distal ones of the holes (A,B) in the CMC wall (F) or in the metal wall (F) are elongated toward a central one of the bolts (C) or at alternate angles to guide differential thermal expansion (T) of the CMC wall (F) versus the metal wall (F) between desired cold and hot geometries. A second CMC wall (R) may be mounted similarly to a second metal wall (R) by pins (A,B,C) that allow expansion of the CMC component () in a direction normal to the walls (F,R).

CMC to metal attachment mechanism

A ceramic ring segment for a turbine engine that may be used as a replacement for one or more metal components. The ceramic ring segment may be formed from a plurality of ceramic plates, such as ceramic matrix composite plates, that are joined together using a strengthening mechanism to reinforce the ceramic plates while permitting the resulting ceramic article to be used as a replacement for components for turbine systems that are typically metal, thereby taking advantage of the properties provided by ceramic materials. The strengthening mechanism may include a ceramic matrix composite overwrap or plurality of overwraps designed to help prevent delamination of the ceramic plates when the ceramic article is in use by placing the plates in compression.

Stacked laminate fiber wrapped segment

Aspects of the invention are directed to a multi-layer ring seal segment that can incorporate a plurality of material systems. The ring seal segment can include an inner layer, a central layer and an outer layer. The inner layer can be attached to one side of the central layer, and the outer layer can be attached to an opposite side of the central layer. The inner and outer layers can be made of a ceramic matrix composite, such as a hybrid oxide ceramic matrix composite or an oxide-oxide ceramic matrix composite. The central layer can be made of a material that has high shear strength relative to the inner and outer layers. The ring seal segment according to aspects of the invention can take advantage of the benefits of the different materials so as to better withstand the operational loads of the turbine.

Multi-layer ring seal

A system for attaching a ring seal to a vane carrier in a turbine engine can allow the ring seal to radially expand and contract at least partially independently of the vane carrier. The system can also be configured to substantially restrict axial and/or circumferential movement of the ring seal. In one embodiment, the ring seal can include a plurality of radial slots circumferentially spaced about the ring seal. A pin can extend substantially through each of the slots and into operative engagement with isolation rings, which are connected to the vane carrier. In another embodiment, the ring seal and the isolation rings can include a series of axially-extending protrusions extending substantially circumferentially about each component. The protrusions on the ring seal can substantially matingly engage the protrusions on the isolation rings. The protrusions can be configured as a Hirth coupling.

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Winter Park, FL, United States of America

David Charles Radonovich