Abstract: A gas turbine blade includes a plurality of guide ribs spaced apart from each other in a movement direction of a cooling fluid in order to guide movement of the cooling fluid flowing along a cooling passage formed in the turbine blade, and an opening formed in each of the guide ribs in order to guide a portion of the cooling fluid to a bottom of the cooling passage between the guide ribs or to side walls adjacent to the bottom.

Abstract: A compressor rotor blade for an axial-type compressor has a blade profile having a transonic section and a profile section which extends in the transonic section and has concave and convex suction-side regions on the suction side, the convex suction-side region arranged downstream of the concave suction-side region, and has convex and concave pressure-side regions on the pressure side, the concave pressure-side region arranged downstream of the convex pressure-side region. Curvature progressions on the pressure side and on the suction side are both applied in a continuous manner over a profile chord of the profile section, the positions of the minimum values of the curvature progressions deviate from each other by not more than 10% of the length of the profile chord, and the positions of the maximum values of the curvature progressions deviate from each other by not more than 10% of the length of the profile chord.

Abstract: An apparatus for cooling an engine component such as a turbine engine airfoil, including a wall bounding an interior extending axially between a leading edge and a trailing edge and radially between a root and a tip. A cooling circuit it located within the interior of the airfoil can include a flow enhancer permitting a volume of fluid, such as air, to pass around the flow enhancer.

Abstract: A centrifugal pump includes at least one pump stage (14). This pump stage (14) includes an impeller (18) which is mounted rotationally fixed on a pump shaft (26). Apart from the pump stage (14), the centrifugal pump is equipped with a turbine wheel (32) which is arranged on the pump shaft (26), without a movement coupling to the pump shaft, in the delivery flow of the centrifugal pump. This turbine wheel (32) forms a transducer of a flow measuring device. A blading of the turbine wheel (32) is such that a torque exerted by the delivery flow onto the turbine wheel (32?) is directed counter to a torque exerted via the pump shaft (26) onto the impeller (18).

Abstract: A system for an engine defined about an axial centerline includes an inner case that includes a bushing, a duct case radially outward of the inner case with respect to the axial centerline, and a seal located on the duct case. The system further includes a borescope plug assembly that traverses the seal and the bushing in mounting to the inner case. The borescope plug assembly includes a spring, a housing sleeve, and a washer sleeve at least partially nested within the housing sleeve. The spring is isolated from the seal by the housing sleeve and the washer sleeve such that the spring is contact-free with respect to the seal.

Abstract: A ceiling fan includes an axle, a hub, a plurality of blades, a plurality of connecting members, and a plurality of protective sleeves. The hub is rotatably coupled with the axle. The plurality of blades is coupled with the hub. Each of the plurality of blades has a first end and a second end. The first end is coupled with the hub. Each of the plurality of blades has a channel intercommunicating the first end with the second end. The plurality of connecting members is respectively received in the channels of the plurality of blades. Each of the plurality of connecting members has an end coupled with the hub, as well as another end coupled with the second end of the each of the plurality of blades. The plurality of protective sleeves respectively envelopes the plurality of connecting members.

Abstract: An apparatus and method for separating dust from a dirty air flow within an airfoil assembly for a turbine engine. The air foil assembly can include a pair of vanes defining a nozzle through which a flow of air can move. At least one of the vanes can include an insert located within an interior of the vane and having a set of holes.

Abstract: A case assembly is provided. The case assembly comprises a first flange and a spot face in the first flange. The spot face has a D-shaped perimeter. A jacking insert is disposed in the spot face and has a D-shaped geometry. A threaded cylinder extends from the jacking insert into the first flange. A jacking insert is also provided. The jacking insert comprises a flat portion having a D-shaped geometry and a cylindrical portion having an internal thread configured to interface with a bolt.

Abstract: A boundary layer propulsor comprises a rotor and a plurality of first aerofoil blades. The rotor has an axis of rotation. The plurality of first aerofoil blades extends radially from the rotor and is arranged in a circumferential array around the axis of rotation. Each of the first aerofoil blades has, in a radially outward sequence, a radially proximal portion, a middle portion, and a radially distal portion. The radially proximal portion has a first cambered cross-section, the middle portion has a second uncambered cross-section, and the radially distal portion has a third cambered cross-section. The first cambered cross-section is cambered in an opposite sense to the third cambered cross-section.

Abstract: An airfoil includes an airfoil structure that defines a portion of an airfoil profile and a panel that defines a different portion of the airfoil profile. The panel has perimeter edges that meet the airfoil structure in a perimeter joint, and there is a perimeter seal disposed in the perimeter joint.

Abstract: A turbine shroud assembly of a gas turbine engine for combustion of fuel mixed with air to produce exhaust products includes a blade track having an I-beam construction including ceramic materials and defining a flow surface to guide exhaust products through a turbine section of the gas turbine engine to expand the exhaust products across the turbine section to produce force.

Abstract: A fan blade includes a hub and a plurality of vanes. The vanes are connected to the hub. Each of the vanes includes a main body and a guide plate. The main body has an inflow surface and an outflow surface. The guide plate is disposed on the outflow surface. When the fan blade rotates, an airflow occurs and flows into a side of the fan blade via the inflow surface, and the guide plate guides part of the airflow to flow out of another side of the fan blade in a first direction and a second direction so as to cool an electronic component disposed adjacent to the another side of the fan blade.

Abstract: A gas turbine engine includes a coupling and an air seal attachment. The annular coupling extends along a centerline and has coupling teeth that extend axially rearward. The annular air seal attachment includes an air seal at an axially rearward end and air seal attachment teeth at an axially forward end that extend axially forward to interlock with the coupling teeth such that the air seal attachment teeth and the coupling teeth alternate in a circumferential direction.

Abstract: A fluid damping structure is provided that includes a damper ring. The damper ring includes an annular body a plurality of fluid check valves, and at least one fluid stop. The annular body extends circumferentially around an axial centerline, and is defined by a first end surface, a second end surface, an outer radial surface, and an inner radial surface. The outer radial surface and the inner radial surface extend axially from the first end surface toward the second end surface. The body includes one or more check valve passages. Each check valve passage extends axially from an open end disposed at the first end surface inwardly toward the second end surface, and is disposed between the inner radial surface and the outer radial surface. An inlet aperture extends between each check valve passage and the outer radial surface, and an outlet aperture extends between each check valve passage and the inner radial surface. Each fluid check valve is disposed in a check valve passage.

Abstract: In order to simplify the design of an aircraft turbo engine propeller while enhancing the safety function thereof related to control of the blade angle of attack, a propeller is provided comprising a secondary rotational coupling to couple in rotation, along the radial axis of the blade, the inner radial end of the blade root with a mechanical joining member of a blade angle of attack control device, the secondary coupling being designed and configured to be active in the event of failure of the main pin.

Abstract: A clearance-control-type seal structure including a plurality of arc-shaped grooves (23) formed side by side in the axial direction with respect to an inner circumferential surface of a housing (22) of a turbine; and abradable seal rings (11, 12) having fitting parts (11a, 12a) that are fitted into the grooves so as to leave a prescribed gap, that have extended parts (11b, 12b) that are exposed from the housing in the radial direction toward the inside and expand in the axial direction, and that, during operation, due to back pressure inside the grooves, receive a force that moves in the radial direction toward the inside. One extended part has a protruding part extending even further in the axial direction toward the upstream side, and the other extended part has formed in an outer circumferential surface of a downstream-side end part thereof a recessed part that corresponds to the protruding part.

Abstract: Rotor support structures for industrial machines are disclosed. The support structures may include a rigid base component including a top portion, a slide plate positioned above the rigid base component, and a bearing housing for a rotor, coupled to the slide plate. The bearing housing and the slide plate may be configured to slide or move over the rigid base component. The support structure may also include a plurality of retention blocks coupled to the bearing housing. Each of the plurality of retention blocks may include a moveable retention pin positioned through each of the plurality of retention blocks. The axial movement of the bearing housing and slide plate may compensate for thermal expansion of a turbine shell and/or may reduce vibrations of the rotor and bearing housing during operation of the industrial machines.

Abstract: There is provided a ventilation apparatus with counter-rotating impellers driven by long shaft, wherein an electric motor and a gearbox are placed outside the air duct by using a long shaft with an internally disposed slim shaft extending therefrom, and are connected with the first stage impeller and second stage impeller inside the air duct by using the long shaft and slim shaft extending therefrom. In this ventilation apparatus with counter-rotating impellers, the components of the ventilation apparatus are placed inside and outside the air duct respectively by using the transmission shaft, which is convenient for maintenance and operation. By remotely arranging the impellers at an axial distance, the hub of the impellers will no longer be affected by an internally disposed electric motor, so as to reduce the ventilation resistance to ventilation. The impellers can be switched between the single impeller rotation and the counter rotation of two impellers.

Abstract: Disclosed is a sealing ring for a turbomachine, which is constructed so as to be fastened at a radially inner region of a plurality of guide vanes and rotate around a rotor shaft. The sealing ring comprises a ring part that extends in the axial direction and has a plurality of stiffened portions in succession in the peripheral direction. Further disclosed is a seal for a turbomachine that comprises such a sealing ring as well as a brush and/or run-in coating sealing ring that is to face a rotor shaft, and a method for the manufacture of a sealing ring.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a fanlet and a track system configured to enable axial translation of the fanlet along a centerline between an open position and a closed position. The track system includes a first component, a second component and a lock. One of the first and the second components is configured as or otherwise includes a slider. The other one of the first and the second components is configured as or otherwise includes a track. The slider is mated with and configured to slide axially along the track. The lock is configured as or otherwise includes a bolt mounted with the first component. The lock is configured to move the bolt laterally into an aperture in the second component to prevent axial translation of the fanlet.