Abstract: Fan tray assemblies for cooling electronic devices in data processing units are described herein. In some embodiments, an apparatus includes a fan tray and a stator member. The fan tray is configured to be mounted within a data processing unit, and defines an opening. The fan tray is configured to be coupled to a fan such that the fan and the opening collectively define a portion of an air flow path. The stator member includes multiple stator blades. The stator member is separate from the fan and configured to be coupled to the fan tray such that the stator blades are within the air flow path.

Abstract: A fan shield for an air cycle machine includes a fan shield body in the general shape of a frustum of a cone having curved sides. The curved sides define a radius of curvature and a center point of curvature that corresponds to the radius of curvature. The center point of curvature is an axial distance from a large end of the fan shield body and a radial distance from the central axis such that a ratio of the radial distance to the axial distance is between 1.160 and 1.360. A bearing housing includes a body that defines a cylindrical portion and an annular flange at one end. The annular flange includes a first attachment opening, a second attachment opening and a third attachment opening that are non-uniformly circumferentially spaced around the flange.

Abstract: An example gas turbine engine shroud includes a first annular ceramic wall having an inner side for resisting high temperature turbine engine gasses and an outer side with a plurality of radial slots. A second annular metallic wall is positioned radially outwardly of and enclosing the first annular ceramic wall and has a plurality of tabs 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.

Abstract: A brush seal assembly for turbomachinery having a rotor can include a stationary seal component, a floating seal component coupled to the stationary seal component and circumferentially angled bristles arranged in a bristle pack, disposed in the floating seal component and extended axially with respect to the rotor.

Abstract: A method for forming a pressure measurement hole in a component includes the step of forming a hole in a body of the component, the hole extending from a body surface of the component. An insert having a longitudinal passage is fitted into the hole such that the insert protrudes from the body surface. The protruding end of the insert is machined to define an insert surface profile matched to the body surface profile and displaced from the body surface by a distance substantially equal to a thickness of a covering layer that is to be bonded onto the body surface. A blocking pin is inserted into the insert passage. The covering layer is then bonded to the body surface in the region of the hole and insert after which the blocking pin is removed from the insert to open the pressure measurement hole.

Abstract: A centrifugal fan is provided, in which the value of static pressure with respect to the flow rate, namely, the flow rate-static pressure characteristic may be set to a relatively arbitrary value without increasing noise. An impeller of the centrifugal fan comprises an impeller body, a plurality of stems, a blade mounting member, a plurality of main blades, and a plurality of sub blades. The main blades are shaped to suck air into a casing through a suction port when the impeller rotates in a direction of normal rotation. The sub blades are shaped to suck air into the casing through the suction port when the impeller rotates in a direction of reverse rotation opposite to the direction of normal direction.

Abstract: A fan includes sloping surfaces arranged at an inner peripheral surface of an air channel portion that are shaped such that an air passage is enlarged in a cross sectional area in a direction normal or substantially normal to a central axis. The inner peripheral surface of the air channel portion also includes a straight surface at which area the distance between the central axis and the inner peripheral surface of the air channel portion is substantially constant. Also, the straight surface of the air channel portion includes a plurality of slits each penetrating the air channel portion.

Abstract: A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: A system comprises an apparatus, an actuator and a processor. The apparatus defines a flow path through an aperture, the aperture defines a pressure drop along the flow path, and the actuator regulates fluid flow across the pressure drop. The processor comprises a flow module, a comparator, an estimator and a control law. The flow module maps a flow curve relating a flow parameter to a pressure ratio, and defines a solution point located on the flow curve and a focus point located off the flow curve. The comparator generates an error as a function of a slope defined between the focus and solution points. The estimator moves the solution point along the flow curve, such that the error is minimized. The control law directs the actuator to position the control element, such that the flow parameter describes the fluid flow and the pressure ratio describes the pressure drop.

Abstract: An airfoil part includes a plurality of cooling chambers that are spaces into which the inside of the airfoil part is partitioned, from a leading edge side to a trailing edge side, by a partition wall, that extend in a vane-longitudinal-section direction, and that include division parts on inner walls of a body; insert cylinders that are disposed in the cooling chambers and that have a plurality of impingement holes; and film holes that are provided in the body. The insert cylinders include partitioning parts that extend from the leading edge side to the trailing edge side and that extend in the vane-longitudinal-section direction. The insides of the insert cylinders are partitioned into pressure-surface-side insert spaces close to a pressure surface and suction-surface-side insert spaces close to a suction surface.

Abstract: A fan blade connection system and method for connecting at least one composite blade (110) to a rotor hub (120), more particularly, for fans used in industrial ventilation and cooling applications. The invention aims to provide a better connection, mainly in regard to the stresses distribution. The preferred embodiments are directed to a system and method for connecting a composite blade (110) to a rotor hub (120) comprising a fastener element (130) arranged in the blade root (111) and extending transversally to the longitudinal axis of the blade (110), said fastener element (130) being adapted for receiving one of the ends of a tensioning member (140) in a longitudinal position in relation to said blade (110). The tensioning member (140) may have an intermediary interface (160) between the blade (110) and the rotor hub (120), fixed by the end of the tensioning member, or fixed by at least one fastener component, which passes through holes in the rotor hub and in the intermediary interface.

Abstract: A ram air turbine (RAT) includes a movable turbine support structure that is prevented from moving to a stowed position by a stow abort mechanism when turbine blades are not locked in a desired position. The stow abort mechanism includes a pawl that is driven by a cam on a release lever. The release lever is movable in response to a position of a release pin that prevents rotation of a turbine drive shaft from a desired orientation that locks the turbine blades in a desired position required for stowage. Disengagement of the release pin causes the stow abort mechanism to maintain a position where the pawl blocks movement to the deployed position. Engagement of the release pin to prevent rotation results in movement of the pawl to a position that provides for movement to the stowed position.

Abstract: A wind power system including a wind turbine affixed to a support tower, and a wind deflector deployable relative to a direction of air flow and configured to control the movement of at least a portion of air flow passing through rotor blades of the wind turbine to reduce wind loads on the components of the wind turbine while maintaining the air flow in an operating power production range.

Abstract: A disclosed ram air turbine assembly includes a movable support structure that is prevented from moving to a stowed position by a stow abort mechanism that prevents movement to the stowed position when the turbine is not in a desired orientation.

Abstract: A fan housing includes a plastic casing having a skirt-board and a lateral wall. The skirt-board includes inner and outer peripheries spaced in a radial direction while the plastic casing further includes a first coupling portion formed along the inner periphery of the skirt-board. The lateral wall extends from a face of the skirt-board along the outer periphery of the skirt-board in an axial direction perpendicular to the radial direction. The fan housing includes a metal frame having a shaft coupling member and a second coupling portion. The second coupling portion of the metal frame is coupled to the first coupling portion of the plastic casing. A motor can be mounted to the metal frame of the fan housing, and an impeller can be rotatably coupled to the motor to form a heat dissipating fan.

Abstract: A method and system for a fan assembly that includes a fan casing having a longitudinal centerline axis extending from an upstream inlet opening to a downstream outlet opening is provided. The fan assembly also includes a first substantially cylindrical casing segment extending circumferentially about and substantially axially aligned with tips of a plurality of blades extending from a rotor hub, the first casing segment including a first inner diameter that is greater than the rotor diameter, a second casing segment configured to extend axially in a direction opposite a flow of fluid through the fan casing, the second casing segment including a second inner diameter, the second inner diameter less than the first inner diameter and the rotor diameter, and a third casing segment including the first inner diameter along a first circumferential edge, the second inner diameter along a second circumferential edge, and a surface extending therebetween.

Abstract: A stator vane assembly comprising inner and outer support rings connected by an annular array of stator vanes at locations around the supporting rings, at least one of said stator vanes in said array being a separate, pre-formed stator vane which is slidably connected to one or both of the supporting rings for radial movement relative to the respective support ring thereby to accommodate relative radial expansion of the support rings.

Abstract: Arrangements of turbines are described. The turbines are staggered or aligned in the downwind direction.

Abstract: A bucket assembly cooling apparatus is provided. The bucket assembly includes a platform, an airfoil, and a shank. The airfoil may extend radially outward from the platform. The shank may extend radially inward from the platform. The shank may include a pressure side sidewall, a suction side sidewall, an upstream sidewall, and a downstream sidewall. The sidewalls may at least partially define a cooling circuit. The cooling circuit may be configured to receive a cooling medium and provide the cooling medium to the airfoil. The upstream sidewall may at least partially define an interior cooling passage and at least partially define an exterior ingestion zone. The cooling passage may be configured to provide a portion of the cooling medium from the cooling circuit to the ingestion zone of an adjacent bucket assembly.

Abstract: An axial flow fan including a rotation shaft section to be mounted on the rotation shaft of rotation drive means, an inner blade group provided outside the rotation shaft section so as to be coaxial therewith, and an outer blade group provided outside the inner blade group so as to be coaxial therewith, wherein the inner blade group is formed of a plurality of inner blades provided radially around the rotation shaft section, the outer blade group is formed of a plurality of outer blades provided radially around the rotation shaft section, and the velocity V1 of the wind generated by the inner blade group and the velocity V2 of the wind generated by the outer blade group have a relationship of 1.5V1<V2 by designing the blades of the inner blade group and the outer blade group with respect to number, area, angle and shape.