Abstract: A turbomachine includes a spool; and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame.

Abstract: This invention, the “Internal Combustion Boundary Layer Turbine Engine” (BLTE), embodies the description of a “flat-disk radial flow turbine engine”. The BLTE uses the effects of “working fluid” or “exhaust” drag to convert the pressure of fuel combustibles to kinetic output energy in the form of a driven shaft. The BLTE application of “differentially sized flat blades” solves the problem of internal combustion and multi-stage operation for this new category of engine. This engine offers the light weight and high power output capability of a continuous or pulsed burn-mode of a radial turbine engine. Relative to conventional radial flow turbine engines, this engine provides reduced exhaust flow, reduced emissions and offers simple, inexpensive construction with commonly available machine tools.

Abstract: An engine component for a gas turbine engine may include a radial channel and an axial channel disposed in the engine component. The radial channel may be configured to direct a cooling air in a radial direction. The axial channel may be configured to direct the cooling air in a direction substantially perpendicular to the radial direction. A cross-section area of the axial channel is greater than a cross-section area of the radial channel, such that the radial channel remains the metering channel, independent of the relative location due to radial movement of the engine component with respect to an adjacent engine component.

Abstract: A turbine blade for a gas turbine engine having an airfoil to platform fillet, wherein the fillet is contoured in accordance with the coordinates of Table 1.

Abstract: An airfoil includes first and second endwalls and an airfoil section having a dual airfoil profile. The airfoil section includes a double wall that has an outer wall that defines a primary leading end of the dual airfoil profile and an inner wall spaced from the outer wall. The outer wall is trapped between the first and second endwalls in mortise and tenon joints, and the inner wall defines a secondary leading end of the dual airfoil profile.

Abstract: This application provides controlled tip balance slits (200) for turbines. An example leakage flow control system (110) for a turbine may include a flow runner (150) with a tip shroud (152), a diaphragm or a guide blade (130), an extension ring (160) coupled to the diaphragm and positioned adjacent to the tip shroud (152), and a tip balance slit (200).

Abstract: A centrifugal compressor includes a housing which includes a scroll portion with a spiral scroll flow passage being formed on an outer peripheral side of an impeller, and a diffuser portion with a diffuser flow passage being formed, the diffuser flow passage extending along the scroll flow passage on a radially inner side of the scroll flow passage and communicating with the scroll flow passage. The diffuser flow passage includes an inner flow passage portion extending from an inlet portion of the diffuser flow passage to a throat portion with a flow passage height thereof decreasing, and an outer flow passage portion extending from the throat portion to an outlet portion of the diffuser flow passage.

Abstract: There is presented a method for damping an edgewise vibration of a rotor blade of a wind turbine, wherein the method comprises measuring at the rotor blade a motion parameter of the edgewise rotor blade vibration, generating based on said motion parameter a blade pitch angle control signal, and damping the edgewise vibration of the rotor blade by pitching the rotor blade according to the blade pitch angle control signal, wherein the blade pitch angle control signal is arranged so that a resulting force on a rotor blade pitched according to the blade pitch angle control signal, in a direction of the edgewise vibration of the rotor blade in a coordinate system, which rotates with a rotor of the wind turbine, is opposite and proportional to the edgewise rotor blade vibration velocity.

Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.

Abstract: Turbine blades for use in gas turbine engines are disclosed herein. Each blade includes an airfoil and a protective crown. The airfoil includes ceramic matrix composite materials. The protective crown includes ceramic-containing materials and is mounted to a radially-outer end portion of the airfoil.

Abstract: A scroll casing forms a scroll flow passage of a centrifugal compressor, and provided that, in a cross section of the scroll flow passage, Ei is an inner end of the scroll flow passage in a radial direction of the centrifugal compressor, and Mh is a middle point of a maximum flow-passage height Hmax of the scroll flow passage in the axial direction of the centrifugal compressor, the scroll flow passage has a separation suppressing cross section in which the inner end Ei is disposed on an inner side, in the radial direction, of a diffuser outlet, and the inner end Ei is disposed on a back side, in the axial direction, of the middle point Mh, in a section disposed at least partially in an upstream region of a connection position of a scroll start and a scroll end.

Abstract: An aviation turbine blade (10) includes at least a first lower surface cavity (C2) and a first upper surface cavity (C3), each adjacent to a first through-cavity (C1) and a second through-cavity (C4), the first upper surface cavity (C3) being adjacent to the upper surface wall (24), the first lower surface cavity (C2) being adjacent to the lower surface wall (22), each of the first and second through-cavities (C1, C4) extending from the lower surface wall (22) as far as the upper surface wall (24), the second through-cavity (C4) including a first inner wall (P1) extending from the upper surface wall (24) as far as the first through-cavity (C1), and a second inner wall (P2) extending from the lower surface wall (22) as far as the first through-cavity (C1). The first (P1) and second (P2) inner walls are not connected.

Abstract: An inclination angle between a direction perpendicular to a rotational axis and a tangential direction of a radially outer edge of a radially outermost concave arc portion, which is located outermost in the radial direction of an impeller among at least one concave arc portion, has a distribution along the circumferential direction of a scroll passage, and when a circumferential position in the scroll passage from a tongue of a scroll part to an outlet of the scroll passage is represented by a central angle about the rotational axis by using the tongue as a reference, the distribution of the inclination angle has a local minimum value or a minimum value in a range of the central angle of 30° to 210°.

Abstract: An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 1750 degree Fahrenheit, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, wherein the grit particles extend above the matrix material relative to the top surface; a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material and a thermal barrier coating material applied over said film of oxidant resistant coating.

Abstract: A bearing assembly for a drivetrain of a wind turbine includes at least one shaft having a circumferential outer surface. The bearing assembly also includes a bearing housing arranged circumferentially around the circumferential outer surface of the shaft. The bearing housing having at least deformation such that the bearing housing and the shaft have a corresponding deformation around a toroidal axis such that interfacing surfaces of the bearing housing and the shaft flex together and remain parallel during operation of the drivetrain, thereby distributing operational loads of the drivetrain. The bearing assembly further includes a bearing housed at least partially within the bearing housing and engaging the circumferential outer surface of the shaft.

Abstract: A centrifugal compressor operable in a wide operation range under a condition accompanied with pulsations of a pressure and a flow rate. The centrifugal compressor has a casing including at least one recirculation channel that includes a first inlet slit connected to an air flow passage on a downstream side of a leading edge in an air flow direction of the air flow passage, a second inlet slit connected to the air flow passage on a downstream side of the first inlet slit in the air flow direction of the air flow passage, a first vane disposed on a downstream side of the first inlet slit or in the first inlet slit in the at least one recirculation channel, and a second vane disposed on a downstream side of the second inlet slit or in the second inlet slit in the at least one recirculation channel.

Abstract: This method is for orientating the blades (40) of a turbine (4) past a non-reachable range of positions (?1, ?2) in a power plant (2), said blades (40) being rotatable around orientation axes (X40) distinct from a rotation axis (X) of the turbine (4), the turbine (4) comprising means (42, 44, 46) for orientating the blades (40), said means being adapted to exert an adjustable torque on the blades (40).

Abstract: A flow generator according to an embodiment of the present invention includes an upper fan configured to suction upper air and generate a first airflow, an upper fan housing configured to accommodate the upper fan from a lower side thereof and comprising a first discharge part through which the suctioned upper air is discharged, a lower fan configured to suction lower air and generate a second airflow, a lower fan housing configured to accommodate the lower fan from an upper side thereof and comprising a second discharge part through which the suctioned lower air is discharged, an air guide disposed between the upper fan and the lower fan to guide generation of a third airflow in which the first airflow and the second airflow are mixed with each other, and a control unit configured to control a rotational speed of the lower fan or the upper fan to adjust a discharge direction of the third airflow, wherein the first discharge part is disposed to face the second discharge part with respect to the flow guide par

Abstract: A gas turbine engine including a first frame including a first mount member defining a stiffness K1; a second frame including a second mount member defining a stiffness K2 and a third mount member defining a stiffness K3; and a gear assembly. The gear assembly includes a first rotatable component, a second rotatable component, and a torque transfer component. The first mount member is coupled to the first rotatable component. The second mount member is coupled to the second rotatable component. The third mount member is coupled to the torque transfer component. The stiffness K1 is less than or equal to 10% of the stiffness K3.

Abstract: The invention relates to an assembly of turbine engine (50) parts having a longitudinal axis (X), the assembly comprising at least two adjacent fan blades made of a 3D woven composite material, each blade (1) comprising a root (3), a vane (2) extending from the root (3), and an integrated platform (4) inserted between the root (3) and the vane (2), the platform (4) extending on either side of the vane (2) and forming a pressure face platform portion (4I) and a suction face platform portion (4E), the pressure face and suction face platform portions of adjacent blades being connected by a fin (14) extending at least radially at the outer side of the pressure face and suction face platform portions (4I, 4E), relative to the longitudinal axis (X), having a substantially triangular transverse cross section and extending axially and so as to upper overlap the longitudinal edges (11A, 11B) of the pressure face and suction face platform portions (4I, 4E) of the adjacent blades.