Abstract: A pot for use with system for controlling soil moisture in a plurality of potted plants to perform water deficit experiments includes a body portion having an open top end and a bottom end, and a flange coupled to the body portion adjacent the top end. The flange is configured to engage a platform to hold the body portion within an opening of the platform. The pot also includes a fluid reservoir having a bottom portion located adjacent the bottom end of the body portion, a plurality of vertically extending fluid channels extending upwardly toward the top end of the body portion, a fill opening located at the bottom end of the body portion in communication with the bottom portion of the fluid reservoir, and a check valve coupled to the fill opening to permit fluid to be supplied to the fluid reservoir from the bottom end of the body portion through fill opening and the check valve.

Abstract: An automated gravimetric screening system and method controls soil moisture in a plurality of potted plants to perform water deficit experiments in a greenhouse using a stationary support platform and pot design that maintains the plants in a static location during the testing. By weighing and re-watering the pots from beneath the platform, the present system and method permits an upper gantry to capture high resolution images, temperature data, or other sensor data to quantify the plant stress level or plant canopy characteristics during the experiment.

Abstract: An automated gravimetric screening system and method controls soil moisture in a plurality of potted plants to perform water deficit experiments in a greenhouse using a stationary support platform and pot design that maintains the plants in a static location during the testing. By weighing and re-watering the pots from beneath the platform, the present system and method permits an upper gantry to capture high resolution images, temperature data, or other sensor data to quantify the plant stress level or plant canopy characteristics during the experiment.

Abstract: A ceramic matrix composite wall structure (20A) constructed of interlocking layers (22A, 24A) of woven material with integral cooling channels (28A, 32A). The CMC layer closest to the hot gas path (41) contains internal cooling tubes (26A, 30A) protruding into a ceramic insulating layer (40A). This construction provides a cooled CMC lamellate wall structure with an interlocking truss core.

Abstract: A ceramic matrix composite (CMC) anchor (20, 100) joining a metal substrate (40) and a ceramic thermal barrier (38). 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 (20) or other extending-into-and-interlocking geometry. A CMC honeycomb may be formed with first (22) and second (24) arrays of cells (26) with open distal ends (28) on respective opposite sides of a sheet (30). The cells may have walls (32) with transverse passages (36). A metal (40) 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 (38) 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.

Abstract: A ceramic matrix composite (CMC) anchor (20, 100) joining a metal substrate (40) and a ceramic thermal barrier (38). 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 (20) or other extending-into-and-interlocking geometry. A CMC honeycomb may be formed with first (22) and second (24) arrays of cells (26) with open distal ends (28) on respective opposite sides of a sheet (30). The cells may have walls (32) with transverse passages (36). A metal (40) 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 (38) 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.

Abstract: 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.

Abstract: A ceramic matrix composite wall structure (20A) constructed of interlocking layers (22A, 24A) of woven material with integral cooling channels (28A, 32A). The CMC layer closest to the hot gas path (41) contains internal cooling tubes (26A, 30A) protruding into a ceramic insulating layer (40A). This construction provides a cooled CMC lamellate wall structure with an interlocking truss core.

Abstract: A gas turbine airfoil (20) having a load-bearing core (30). A honeycomb structure (40A, 42A) is attached to pressure and/or suction sides (22, 24) of the core and is filled with ceramic insulation (50). A ceramic matrix composite boot (60A, 60B, 60C) may cover the leading edge (26) of the core. Edges (61, 62) of the boot may be attached to the core by rows of pins (63A, 63B) or by flanges (65) inserted in slots (69) in the core. The pins may be formed in place by forming pin holes (64) 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 (66) with the core. The boot may have a central portion (71) that is not bonded to the core to allow differential thermal expansion.

Abstract: An attachment method and flange for connecting a ceramic matrix composite (CMC) component, such as a gas turbine shroud ring (36, 68), to a metal support structure. A CMC flange (20A) may be formed by attaching a wedge-shaped block (26) of a ceramic material to a CMC wall structure (22), and wrapping CMC layers (24) of the wall structure (22) at least partly around the block (26), forming the flange (20A) with an inner oblique face (34) and an outer face (35) normal to the wall structure. An adjacent support structure, such as a metal support ring (40A), may abut the outer face (35) of the CMC flange (20A) and be clamped or bolted to the CMC flange (20A).

Abstract: A ceramic hybrid structure (207, 502, 602, 608) that includes a wavy ceramic matrix composite (CMC) wall (214, 532, 603, 609) bonded with a ceramic insulating layer (230, 538, 604, 610) having a distal surface (242) that may define a hot gas passage (250, 550, 650) or otherwise be in proximity to a source of elevated temperature. In various embodiments, the waves (216, 537, 637) of the CMC wall (214, 532, 603, 609) may conform to the following parameters: a thickness (222) between 1 and 10 millimeters; an amplitude (224) between one and 2.5 times the thickness; and a period (226) between one and 20 times the amplitude. The uninsulated backside surface (218) of the CMC wall (214) provides a desired stiffness and strength and enhanced cooling surface area. In various embodiments the amplitude (224), excluding the thickness (222), may be at least 2 mm.

Abstract: 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.

Abstract: A ceramic seal element (200) for use in a turbo-machine comprises a first, rigid portion (210) comprising ceramic fibers (212) bound within a ceramic matrix binder (214), a second, flexible portion (220) comprising ceramic fibers (222), and a third, rigid portion (230) comprising ceramic fibers (232) bound within a ceramic matrix binder (234). Ceramic fibers (222) retain a desired flexibility because they are not bound in ceramic matrix binder. In some embodiments the ceramic fibers (212, 222, 232) are stacked as horizontally disposed layers (225). Also, the fibers (212, 222, 232) of any layer (225) comprise bundles of fibers wherein some of the bundles extend continuously across portions (210, 220, 230). An alternative sealing element (300) comprises a first, rigid portion (310) comprising ceramic fibers (312) that are bound within a ceramic matrix binder (314), and a second, flexible portion (320) that comprises ceramic fibers (313) that retain a desired flexibility. Methods of manufacture are disclosed.

Abstract: 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.

Abstract: A CMC wall (20F) may be attached to a metal wall (22F) by a plurality of bolts (28A, 28B, 28C) passing through respective holes (24A, 24B, 24C) in the CMC wall (20F) and holes in the metal wall (22F), clamping the walls (20F, 22F) together with a force that allows sliding thermal expansion but does not allow vibrational shifting. Distal ones of the holes (24A, 24B) in the CMC wall (20F) or in the metal wall (22F) are elongated toward a central one of the bolts (24C) or at alternate angles to guide differential thermal expansion (20T) of the CMC wall (20F) versus the metal wall (22F) between desired cold and hot geometries. A second CMC wall (20R) may be mounted similarly to a second metal wall (22R) by pins (39A, 39B, 39C) that allow expansion of the CMC component (201) in a direction normal to the walls (20F, 20R).

Abstract: 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.

Abstract: A gas turbine airfoil (20) having a load-bearing core (30). A honeycomb structure (40A, 42A) is attached to pressure and/or suction sides (22, 24) of the core and is filled with ceramic insulation (50). A ceramic matrix composite boot (60A, 60B, 60C) may cover the leading edge (26) of the core. Edges (61, 62) of the boot may be attached to the core by rows of pins (63A, 63B) or by flanges (65) inserted in slots (69) in the core. The pins may be formed in place by forming pin holes (64) 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 (66) with the core. The boot may have a central portion (71) that is not bonded to the core to allow differential thermal expansion.

Abstract: 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.

Abstract: An apparatus for a gas turbine engine, such as a transition (225, 325), includes a metal shell (200, 300) surrounding a body (230, 330) that is comprised of a ceramic matrix composite (CMC)-comprising structure (231) and a ceramic insulating layer (265) bonded thereto. The metal shell (200, 300) defines a space (250) adapted to contain the transition body (230, 330), and comprises at least one protrusion (220) adapted to contact the transition body (230, 330). A pin (255) passes through the transition body (230, 330) and the metal shell (200, 300) at their forward ends, and a compliant porous element (240) is adapted to fit in the space (250) between the metal shell (200, 300) and the transition body (230, 330).

Abstract: A structure for use in high temperature applications is provided. The structure may include an inner ceramic matrix composite (CMC) material (12). At least a portion of this CMC material includes waves that define a first wavy surface (140 and an opposed second wavy surface (16). A ceramic insulation material (18) may be bonded with the first wavy surface and includes a distal surface (20) for exposure to a high temperature environment. A core material (22) is bonded with at least a portion of the second wavy surface. One or more cooling channels (24) are disposed in the core material. An outer CMC material (26) 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.