A vibration damping system for a turbine nozzle or blade includes a vibration damping element including a plurality of contacting members including a plurality of damper pins. Each damper pin includes a body. A wire mesh member surrounds the body of at least one of the plurality of damper pins. The wire mesh member has a first outer dimension sized for frictionally engaging within a body opening in the turbine nozzle or blade to damp vibration. Spacer members devoid of a wire mesh member may also be used. The damper pins can have different sizes to accommodate contiguous body openings of different sizes in the nozzle or blade. The body opening can be angled relative to a radial extent of the nozzle or blade.

A gas turbine engine includes a turbine section disposed about an engine axis. The turbine section includes inner and outer diameter ceramic support rings that define a gaspath there between. Each of the inner and outer diameter ceramic support rings is monolithic and continuous. Ceramic vane arc segments are disposed in the gaspath and supported by the inner and outer diameter ceramic support rings. Each of the ceramic vane arc segments includes inner and outer platforms and an airfoil section there between. At least one retainer engages the inner or outer diameter ceramic support ring with the ceramic vane arc segments to retain the ceramic vane arc segments between the inner and outer diameter ceramic support rings.

A gas turbine engine includes a turbine section that has a plurality of turbine vanes. Each of the turbine vanes includes inner and outer platforms and an airfoil section that extends there between. The airfoil section is hollow and rib-less and has a first end at the outer platform and a second end at the inner platform. The airfoil section is tangentially bowed from the first end to the second end with a radius of curvature that is from 17 centimeters to 130 centimeters.

An apparatus for oil lubrication of a rotationally fixed connection between two shafts. A first shaft engages with a hollow region of the second shaft. The shafts are operatively connected to each other in a form-fitting manner in the overlapping region. Oil is introduced into a first chamber in the hollow region, which chamber is connected to a second chamber in the hollow region. The second chamber is connectable to a third chamber is arranged in the overlapping region. The fluidic connection between the second chamber and the third chamber is separated above a defined oil volume in the second chamber and above a rotational speed threshold of the shafts via a sealing element. The sealing element is reversibly deformable by the oil volume in the second chamber and the centrifugal force acting thereon and, in the deformed state, seals the connection between the second and third chambers.

A fluid flow regulation assembly (1) includes: movable parts, for being actively mechanically driven, including at least one of a fluid flow regulating body for regulating a fluid flow and a rotor of a motor for driving the regulating body; and power electronics for controlling the motor. The movable parts and/or the power electronics are a source of vibration. Static parts are exposed to traveling vibrations originating from the source of vibration and include at least one of the group: a pump housing (3), a valve housing, a motor housing (5), a pump base and an electronics housing (7). The static parts include a structural element (11) with at least one vibration attenuation section (9) for attenuating vibrations: that originate from the source of vibration; travel along the structural element and have a vibration frequency above a pre-determined minimum vibration frequency (f.sub.min).

Turbine (1) comprising a casing, an outer metal shroud (9), an inner metal shroud (5) and an annular distributor (2) having a plurality of CMC ring sectors (20), each sector comprising a mast (6), an inner platform (24), an outer platform (26) and at least one blade (28) having a hollow profile that defines an inner housing (280), the inner and outer platforms each having an opening (245, 265) communicating with said inner housing, and the mast (6) passing through said openings and the inner housing and being secured to said casing and connected to said annular sector. Each blade comprises at least one first radial shoulder (72) projecting axially towards the inside of the blade, and each mast comprises at least one second shoulder (71) projecting axially towards the outside of the mast (6) configured to radially cooperate with a first shoulder (72) and radially press the blade (28) against the mast (6).

A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A rigid connection between a fan case and an inner core housing includes a plurality of A-frames connected at a connection point to the fan case. Legs in the A-frames extend away from the connection point in opposed circumferential directions to be connected to a compressor wall of the inner core housing. The rigid connection also includes a plurality of fan exit guide vanes rigidly connected to the fan case. A lateral stiffness ratio of the lateral stiffness of the plurality of fan exit guide vanes and a lateral stiffness of a combination of the plurality of A-frame, the compressor wall, and a fan intermediate case which is forward of the low pressure compressor being greater than or equal to 0.6 and less than or equal to 2.0.

A turbomachinery stator apparatus includes: a compressor casing including a casing wall defining an arcuate flowpath surface and an opposed backside surface, the flowpath surface defining at least two spaced-apart rotor lands, a stator vane row of stator vanes disposed inside the compressor casing, wherein the casing wall includes a heat shield positioned outboard of the rotor lands immediately upstream or downstream of the stator vane row, and wherein a) the casing wall includes the heat shield and b) the stator vanes form a single monolithic whole.

Disclosed is an aircraft turbine engine (10), comprising a gas generator (12) and a fan (14) arranged upstream from the gas generator (12) and configured to generate a gas inlet stream (F), part of which flows into a duct of the gas generator to form a primary stream (36), the turbine engine (10) comprising an electrical machine that is mounted coaxially downstream from the fan (14) and that comprises a rotor (62a) surrounded by a stator (62b) carried by an annular shroud (64), this shroud (64) being surrounded by a casing (40) of the gas generator that defines, with this shroud (64), a section of the flow duct for the primary stream (36), stationary vanes (42, 68) for straightening this primary stream (36) extending into this path.

A radial impeller having a cover plate with an inlet opening and a support plate, the plates being connected to one another by means of a vane ring having multiple vanes. The vanes each have two side edges opposite one another, one of which is connected to the cover plate and the other to the support plate. The side edges each extend between a vane inlet edge and a vane outlet edge which is opposite in a circumferential direction of the impeller. The vanes are each designed as a hollow profile and have two vane halves delimiting a cavity between them which are applied to one another and are each connected to one another in the region of the vane inlet edge and the vane outlet edge by means of a welded connection.