Abstract: A disclosed gas turbine engine includes a shroud block including a mounting slot, a blade outer air seal supported within the mounting slot and a seal disposed within the mounting slot providing a seal between the blade outer air seal and the mounting slot. An anti-rotation tab is attached to the shroud block within the mounting slot for constraining movement of the seal within the mounting slot.

Abstract: A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. The speed change mechanism is an epicyclic gear train. A torque frame surrounds the speed change mechanism and includes a plurality of fingers. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted forward of the speed change mechanism and a second fan section bearing is mounted on the bearing support aft of the speed change mechanism. The second fan section bearing is a fan thrust bearing.

Abstract: A wind turbine blade has a vortex generator including a plurality of fins, and a height H(m) of each of the fins and a maximum chord length C (m) of the wind turbine blade satisfies 0.3×10?2?H/C?0.9×10?2. The height H of the fins may satisfy H?0.1?1, provided that ?1 is a boundary layer thickness at a rated tip speed ratio in a blade degradation state. A method for determining arrangement of a vortex generator on the wind turbine blade includes a pair of the fins arranged line-symmetrically with respect to a segment along a chordwise direction of the wind turbine blade.

Abstract: A corrugated lift fan rotor is disclosed. In various embodiments, a rotor includes an upper skin, a lower skin, and an at least partly corrugated core encased between the upper skin and the lower skin. In some embodiments, the core comprises a composite material, such as carbon fiber reinforced polymer composite material, and includes an upper cap portion, a lower cap portion, and a web portion extending between the upper and lower cap portions.

Abstract: An enclosure for a nacelle of a wind turbine is connected to a substructure in a manner that allows the enclosure to move relative to the substructure. An imaginary straight line extends over the panel and is aligned with an edge of the panel. The imaginary straight line defines a first sub-portion of the panel, said first sub-portion comprising the edge. The first sub-portion butts against the substructure. The first sub-portion is retained against the substructure by a tension element acting in a direction of tension. The first sub-portion can be displaced relative to the substructure in a direction which intersects the direction of tension. The invention facilitates the operation of assembling the enclosure.

Abstract: A method for manufacturing an impeller of a rotary machine, the impeller including at least one vane limiting an inner channel, which is at least partly closed, the method includes successively manufactured the impeller of several material layers by a build-up process from a powder. The powder is applied in each case to a processing plane for the production of each material layer, and then a solid material layer is produced from the powder by a selective energy input, and structural orientation is determined for the impeller, according to which the impeller is built up in layers, and the structural orientation is defined by a first and a second angle, which angles describe the relative position of the impeller to the processing plane.

Abstract: A component for a gas turbine engine may comprise a cooling channel. A first trip strip may extend from a wall of the cooling channel. A leg of the first trip strip and a first plane orthogonal to a direction of airflow through the cooling channel may form a first angle. A second trip strip may be downstream from the first trip strip and extending from the wall of the cooling channel. A leg of the second trip strip and a second plane orthogonal to the direction of airflow through the cooling channel may form a second angle different from the first angle.

Abstract: Joining an airfoil with a platform by mechanical keying can provide advantages in applications of ceramic materials, such as ceramic matrix composites.

Abstract: A rotor for a centrifugal compressor includes: a rotor main; an impeller; and a contact member. The rotor main body extends in an axis direction and includes a recessed part that is disposed on an outer circumferential surface. The impeller includes: a cylinder part having a cylindrical shape that extends around the axis direction and includes an inner circumferential surface with a fitting region tightly fitted to the outer circumferential surface of the rotor main body; an annular disc that extends from the cylinder part to a radial outer side with respect to the axis direction; a plurality of blades disposed at intervals in a circumferential direction on a surface facing one side in the axis direction of the annular disc; and a cover that covers the plurality of blades from the one side in the axis direction. The contact member is fitted into the recessed part.

Abstract: An airfoil fairing shell for a gas turbine engine includes an airfoil section between an outer vane endwall and an inner vane endwall, at least one of the outer vane endwall and the inner vane endwall including a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face.

Abstract: The present disclosure is directed to a blade track assembly used in a gas turbine engine. The blade track assembly includes blade track segments made from ceramic matrix composite materials and a tip clearance control system for adjusting the inner diameter of the blade track assembly during use in an engine.

Abstract: The invention relates to comprising a blade body (9) made of composite material having a polymer matrix reinforced by fibers and a leading edge shield (10) made of material having greater ability to withstand point impacts than the composite material of the blade body. The leading edge shield (10) is assembled on the blade body (9) by means of a first adhesive (16) and a second adhesive (17), both adhesives (16, 17) being deposited between the blade body (9) and the leading edge shield (10). Both adhesives (16, 17) form respective continuous films between the blade body (9) and the leading edge shield (10).

Abstract: A turbine blade having a base and an airfoil, the base including cooling air inlets and an internal cooling air passageway, and the airfoil including an internal multi-bend heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a “skin” that encompasses a tip wall, an inner spar, and a tip flag cooling system.

Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Impingement tubes direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

Abstract: A steam turbine cooling unit for a steam turbine includes a coolant steam path provided to penetrate a casing along a superheated steam supply tube to reach a gap; and a coolant steam supplying unit configured to supply coolant steam flowing through the coolant steam path along the superheated steam supply tube to reach the gap, and having: (i) a pressure higher than a pressure of superheated steam to be supplied by the superheated steam supply tube; and (ii) a temperature lower than a temperature of the superheated steam to be supplied by the superheated steam supply tube.

Abstract: Airfoil assemblies for gas turbine engines are provided. For example, an airfoil assembly comprises an airfoil, an inner band defining an inner opening shaped complementary to an inner end of the airfoil, and an outer band defining an outer opening shaped complementary to an outer end of the airfoil. The airfoil inner end is received with the inner opening, and the airfoil outer end is received within the outer opening. A strut extends radially through an airfoil cavity. A first pad is defined at a first radial location within the cavity. A second pad is defined within the cavity at a second, different radial location. In some embodiments, the airfoil assembly inner band includes a first inner flange, through which the inner band is secured to a support structure, and the outer band includes a first outer flange, through which the outer band is secured to a support structure.

Abstract: A casting plug for a vane of a gas turbine engine includes a plug body a flow control feature and a support that extends between the plug body and the flow control feature.

Abstract: A gas turbine component, for forming part of a stage of the turbine, operable to change cooling scheme, includes an airfoil profiled section, a cooling passageway, film holes and interchangeable connectors. The profiled section includes pressure and suction sides joined together at chordally opposite leading and trailing edges. The cooling passageway extends between the pressure and suction sides along the leading edge to enabling cooling fluid to flow therefrom. The film holes are configured on the cooling passageway to enable the flow of a portion of the cooling fluid to a portion of the profiled section. The interchangeable connectors configured to the cooling passageway, one at a time, to change the cooling scheme. An insert may also be provided to close and open the film holes.

Abstract: A compressor includes impellers each having its chord angle less than its stall angle. The impellers can be used in a contra-rotating impeller arrangement without static diffusers. The contra-rotating impeller arrangement provides for much larger nominal flow rates than conventional single rotating impeller arrangements with the same chord angles. Accordingly, a surge free design is provided without excessively compromising the nominal flow rate. Techniques for enhancing stall characteristics of the impellers are also described.

Abstract: Provided is a centrifugal compressor impeller that includes blades extending from an inlet to an outlet for a fluid. Each of the blades of the impeller includes, when a distribution of blade angles of a tip is viewed in a direction in which the tip extends from a tip inlet to a tip outlet for the tip, a constant blade angle region in which the blade angles are constant. A start point on the inlet side of the constant blade angle region is set at a position spaced apart from the tip inlet.