Siemens Energy, Inc.

Siemens Power Generation, Inc.

Other

Stryker Corporation

Douglas A Keller

Jay Alan Morrison

Malberto Gonzalez

David Charles Radonovich

Anthony L Schiavo

Kenneth A Stevens

Gary Brian Merrill

Christian X Campbell

Steven James Vance

Bonnie D Marini

Cory Patrick Herbst

Jay Edgar Lane

Walter Ray Laster

Michael Anthony Burke

Daniel George Thompson

John P Zerbel

Stefan Mazzola

Eugene L Keller, Iii

Joan Mae Baer

Mike Brubaker

Vijay Parthasarathy

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 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 movable patient support includes a frame, a patient support surface supported at the frame, a base supporting the frame and having a plurality of bearing assemblies for moving the base along a floor surface. The support also includes a brake, a brake actuator for actuating the brake of at least one bearing assembly, and a brake bar coupled to the brake actuator. The brake bar is movable between a non-braking position and a braking position wherein the actuator causes the brake to move to its braking position. Further, the brake bar extends between the head end and the foot end of the frame and further has a portion extending outwardly from the brake actuator to at least close proximity to the bearing footprint defined by the bearing assemblies but within the frame footprint to thereby provide relatively easy access to the brake bar to an attendant standing adjacent one of the longitudinal sides of the frame.

Patient support brake system

A gas turbine airfoil () having a load-bearing core (). A honeycomb structure (A,A) is attached to pressure and/or suction sides () of the core and is filled with ceramic insulation (). A ceramic matrix composite boot (A,B,C) may cover the leading edge () of the core. Edges () of the boot may be attached to the core by rows of pins (A,B) or by flanges () inserted in slots () in the core. The pins may be formed in place by forming pin holes () in the boot, clamping the boot onto the core, filling the pin holes with metal or ceramic and metal particles, and heating the particles for internal cohesion and solid-state diffusion bonding () with the core. The boot may have a central portion () that is not bonded to the core to allow differential thermal expansion.

Gas turbine airfoil

An attachment method and flange for connecting a ceramic matrix composite (CMC) component, such as a gas turbine shroud ring (), to a metal support structure. A CMC flange (A) may be formed by attaching a wedge-shaped block () of a ceramic material to a CMC wall structure (), and wrapping CMC layers () of the wall structure () at least partly around the block (), forming the flange (A) with an inner oblique face () and an outer face () normal to the wall structure. An adjacent support structure, such as a metal support ring (A), may abut the outer face () of the CMC flange (A) and be clamped or bolted to the CMC flange (A).

Ceramic matrix composite attachment 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 hybrid structure () that includes a wavy ceramic matrix composite (CMC) wall () bonded with a ceramic insulating layer () having a distal surface () that may define a hot gas passage () or otherwise be in proximity to a source of elevated temperature. In various embodiments, the waves () of the CMC wall () may conform to the following parameters: a thickness () between 1 and 10 millimeters; an amplitude () between one and 2.5 times the thickness; and a period () between one and 20 times the amplitude. The uninsulated backside surface () of the CMC wall () provides a desired stiffness and strength and enhanced cooling surface area. In various embodiments the amplitude (), excluding the thickness (), may be at least 2 mm.

Wavy CMC wall hybrid ceramic apparatus

A turbine engine ring seal for sealing gaps between turbine engine outer seal segments and turbine blade tips. The turbine engine ring segment may have an inner radial surface that defines a portion of a gap gas flow path where the inner radial surface may be formed of an abradable ceramic coating and includes a plurality of gas flow protrusions that are oriented transverse to the gap gas flow path. The gas flow protrusions may induce vortices in the gas flow in the gap gas flow path. Additionally, the gas flow protrusions may be series of peaks and depressions between two adjacent peaks, where the depressions have an approximate semicircular shape. The distance between two adjacent peaks may be equal or greater than a width of the depression and the height of a single peak may be six percent or greater than the distance between two adjacent peaks.

Ring seal for a turbine engine

A ceramic seal element () for use in a turbo-machine comprises a first, rigid portion () comprising ceramic fibers () bound within a ceramic matrix binder (), a second, flexible portion () comprising ceramic fibers (), and a third, rigid portion () comprising ceramic fibers () bound within a ceramic matrix binder (). Ceramic fibers () retain a desired flexibility because they are not bound in ceramic matrix binder. In some embodiments the ceramic fibers () are stacked as horizontally disposed layers (). Also, the fibers () of any layer () comprise bundles of fibers wherein some of the bundles extend continuously across portions (). An alternative sealing element () comprises a first, rigid portion () comprising ceramic fibers () that are bound within a ceramic matrix binder (), and a second, flexible portion () that comprises ceramic fibers () that retain a desired flexibility. Methods of manufacture are disclosed.

Flexible, high-temperature ceramic seal element

Aspects of the invention relate to a ring seal for a turbine engine. The ring seal can be made up of a plurality of circumferentially abutted ring seal segments. Each ring seal segment can comprise a plurality of individual channels. The channels can be generally U-shaped in cross-section with a forward span, and aft span and an extension connecting therebetween. The channels can be positioned such that the aft span of one channel can substantially abut the forward span of another channel. The plurality of separate channels can be detachably coupled to each other by, for example, a plurality of pins. The ring seal segment according to aspects of the invention can facilitate numerous advantageous characteristics including greater material selection, selective cooling, improved serviceability, and reduced blade tip leakage. Moreover, the configuration is well suited to handle the operational loads of the turbine.

Turbine engine ring seal

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

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

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.

Growing community of inventors

Kalamazoo, MI, United States of America

Douglas A Keller