Siemens Energy, Inc.

Siemens Power Generation, Inc.

Malberto Gonzalez

Jay Alan Morrison

Douglas A Keller

Anthony L Schiavo

David Charles Radonovich

Gary Brian Merrill

David James Wiebe

Christian X Campbell

Alexander Ralph Beeck

Jay Edgar Lane

Steven James Vance

Andrew Jeremiah Burns

Bonnie D Marini

Jerome H Katy

Kurt Augustus Plotts

Dougas A Keller

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 support structure in a gas turbine engine including an inner annular wall and an outer annular wall defining an annular flow path, a casing housing the structure defining the flow path, and a bearing compartment housing a rotor shaft bearing located radially inwardly from the inner annular wall. The support structure includes a plurality of circumferentially spaced radial support members extending radially inwardly from an outer mount connection at the casing to an inner mount connection at the bearing compartment housing. The radial support members provide structural support for radial bearing loads on the rotor shaft bearing. A plurality of circumferentially spaced axial support members extend radially and axially inwardly from an outer mount connection at the casing to an inner mount connection located on an annular structure extending radially between connection locations at the bearing compartment housing and the inner annular wall.

Gas turbine engine with angled and radial supports

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

A ceramic matrix composite wall structure (A) constructed of interlocking layers (A,A) of woven material with integral cooling channels (A,A). The CMC layer closest to the hot gas path () contains internal cooling tubes (A,A) protruding into a ceramic insulating layer (A). This construction provides a cooled CMC lamellate wall structure with an interlocking truss core.

CMC wall structure with integral cooling channels

A ceramic matrix composite (CMC) anchor () joining a metal substrate () and a ceramic thermal barrier (). The CMC anchor extends into and interlocks with the ceramic barrier, and extends into and interlocks with the metal substrate. The CMC anchor may be a honeycomb () or other extending-into-and-interlocking geometry. A CMC honeycomb may be formed with first () and second () arrays of cells () with open distal ends () on respective opposite sides of a sheet (). The cells may have walls () with transverse passages (). A metal () may be deposited into the cells and passages on one side of the sheet, forming a metal substrate locked into the honeycomb. A ceramic insulation material () may be deposited into the cells and passages on the opposite side of the sheet, forming a layer of ceramic insulation locked into the honeycomb.

CMC anchor for attaching a ceramic thermal barrier to metal

A structure for use in high temperature applications is provided. The structure may include an inner ceramic matrix composite (CMC) material (). At least a portion of this CMC material includes waves that define a first wavy surface (and an opposed second wavy surface (). A ceramic insulation material () may be bonded with the first wavy surface and includes a distal surface () for exposure to a high temperature environment. A core material () is bonded with at least a portion of the second wavy surface. One or more cooling channels () are disposed in the core material. An outer CMC material () may be joined to a portion of the inner CMC material. The core material is a material different than a matrix material of the inner CMC material.

Hybrid ceramic structure with internal cooling arrangements

A configuration of seals disposed around and between a plurality of ring segments () arrayed annularly about the periphery of moving blades in a gas turbine engine. The seals function to retain coolant in the plenum () within each of the ring segments (). The seals are disposed atop a substrate (A), which forms the top of the plenum (). The first seal () is made of a piece of sheet material and seals the gap between adjacent ring segments. This seal has an edge (A) thereof creased for mating with a similar seal on an adjacent ring segment. A second seal (), which is also made of sheet material, seals the ends of the plenum () of the ring segments (). Lastly, a third seal (), which is also made of a piece of sheet material, seals the sides of the second seal ().

Ring segment coolant seal configuration

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

An apparatus for mounting a refractory component such as a turbine shroud ring segment () with a ceramic core () onto a combustion turbine engine structure (). The ring segment has a ceramic matrix composite skin (), and optionally, a thermal insulation layer (). A pin () is inserted through a bore () in the core and through an attachment bar () with ends received in wells () in the core. The attachment bar may be attached to a backing member, or tophat (), by a biasing device () that urges the refractory component snugly against the backing member to eliminate vibration. The backing member and refractory component have mating surfaces that may include angled sides (S,). The backing member is attached to the engine structure. Turbine shroud ring segments can be attached by this apparatus to a surrounding structure to form a shroud ring.

Pin-loaded mounting apparatus for a refractory component in a combustion turbine engine

The claimed invention relates to a method for determining the extent of an oxidation reaction of a coated metallic turbine component within a turbine, comprising determining a plurality of reference oxidation rates for a plurality of locations on the turbine component for a plurality of different turbine operating conditions. The invention also relates to selecting an appropriate oxidation rate from a family of reference oxidation rate data and estimating the oxidation of the coated turbine blade or vane.

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Orlando, FL, United States of America

Malberto Gonzalez