Airfoil assemblies for gas turbine engines include an airfoil body and a leading edge baffle installed within a leading edge cavity of the airfoil body. The airfoil body includes a plurality of radially extending rails configured to engage with the baffle and define radially extending channels therebetween. First and second forward radially extending rails are segmented in the radial direction and a showerhead radial channel is defined along the leading edge. Pressure and suction side radial flow channels are defined between an interior surface of the airfoil body, an exterior surface of the baffle, and radially extending rails. An aft channel is defined between an interior surface of the airfoil body along pressure and suction side walls, an interior rib, exterior surfaces of the baffle, and the radially extending rails.

A method of assembling a first part to a second part while applying thermal energy to at least one of the parts. The application of thermal energy is terminated when the first part and second part are in a completed assembly position relative to each other. The thermal energy absorbed by the at least one of: the first part; and the second part is then dissipated until the first part and second part are engaged in an interference fit.

A rotor assembly includes a rotor having a dovetail slot. The dovetail slot includes a plurality of recesses and a first radially innermost surface. A rotor blade includes an airfoil that extends radially outward from a platform and a dovetail that extends radially inward from the platform. The dovetail includes a plurality of projections extending in opposite directions that are received by the plurality of recesses of the dovetail slot. The dovetail further includes a leading edge surface, a trailing edge surface, and a second radially innermost surface. The second radially innermost surface defines a groove from the leading edge surface to the trailing edge surface. The shim is positioned within the groove and between the first radially innermost surface of the dovetail slot and the second radially innermost surface of the dovetail. The shim extends at least partially radially along both of the leading edge surface and the trailing edge surface to secure the rotor blade within the dovetail slot during various operating conditions of the turbomachine.

A thermal bridge forms a connection between a cold side and a hot side that is capable of withstanding a large temperature differential while high-pressure gas (e.g., air) flows between the two sides within an internal passageway. A cold-side region and hot-side region of the thermal bridge may each have a flange with a plurality of holes. The cold-side region may also include a conical fillet with counterbore recesses to provide access to each of the plurality of holes from a low radial position.

The invention relates to a bearing arrangement designed as a fixed/floating bearing for a rotor of a fan, having a bearing tube, a compression spring, a shaft arranged coaxially with respect to the bearing tube, and two identically formed ball bearings arranged between the bearing tube and the shaft, each ball bearing having an inner ring and an outer ring, wherein multiple different fit zones are formed axially along the bearing tube, wherein, in a first axial fit zone, one of the ball bearings as a fixed bearing is attached by its inner ring on the shaft and its outer ring is fixed with a press fit on a continuous, shoulder-free portion of the bearing tube and, in a second axial fit zone, another of the ball bearings as a floating bearing is attached by its inner ring to the shaft and its outer ring is axially displaceably arranged with a clearance fit on a continuous, shoulder-free portion of the bearing tube, wherein the compression spring is arranged in a third axial fit zone and, exerting a preload against the outer rings of the ball bearings, is positioned axially between the ball bearings and is designed to eliminate bearing play of the floating bearing.

An insert is disposable between an exterior surface of an annular body and an annular flange and between a support wall supportive of the annular flange and surface features of the exterior surface. The insert includes a forward section sized to fit between and to extend along respective arc-segments of the exterior surface and the annular flange and an aft section. The forward section includes a first end wall abuttable with the support wall, a second end wall and inner and outer diameter surfaces that extend between the first and second end walls for abutment with the exterior surface and the annular flange, respectively. The aft section extends from the second end wall to be engageable with the surface features.

A radial fan (1) is provided with a motor (2) and a fan housing, an outer part (4) and an inner part (5) that form a spiral-like pressure chamber (D). A pressure connector (33) which forms an outlet (44) of the radial fan (1) is arranged on the outer part. The fan housing is equipped with a fan wheel (3) which is arranged on a shaft (7) connected to the motor (2), wherein an annular flow divider (8) which surrounds the fan wheel (3) is arranged adjacently to the fan wheel (3) in a radial direction. The flow divider together with the fan housing forming a diffuser (9), which transitions directly into the pressure chamber (D), about the fan wheel (3).

Airfoil assemblies for gas turbine engines include an airfoil body and a leading edge baffle installed within a leading edge cavity of the airfoil body. The airfoil body includes a plurality of radially extending rails configured to engage with the baffle and define radially extending channels therebetween. First and second forward radially extending rails are segmented in the radial direction and a showerhead radial channel is defined along the leading edge. Pressure and suction side radial flow channels are defined between an interior surface of the airfoil body, an exterior surface of the baffle, and radially extending rails. An aft channel is defined between an interior surface of the airfoil body along pressure and suction side walls, an interior rib, exterior surfaces of the baffle, and the radially extending rails.

A integral or monolithic nozzle segment having airfoils According to an aspect of the invention a steam turbine has a casing supporting multiple nozzle segments forming a diaphragm with the airfoils located in a channel through which working fluid flows. The diaphragm surrounds a rotary axis of a steam turbine coaxially and consists of a plurality of individual nozzle segments. The nozzle segments and the casing of the steam turbine have substantially equal thermal expansion coefficients. The casing and the nozzle segments are made of different materials and particularly different martensitic steel types. Each nozzle segment may have a core comprising martensitic steel having a minimum creep strength that fulfills the following conditions at a temperature of 580° C.: at least 105 hours under a tensile stress of at least 100 MPa or at least 125 MPa or at least 150 MPa.

A pre-assembly method for an aircraft turbomachine, having preliminary assembling, outside the turbomachine, the following components with each other a reduction gear configured to transmit a rotation between at least two rotors of the turbomachine while modifying the speed and torque ratio from one to the other of said at least two rotors, a shaft kinematically coupled to the reduction gear and configured to be kinematically coupled to one of said at least two rotors, a bearing support, and at least one bearing mounted on the bearing support and configured to rotatably support the shaft.