Abstract: A compressor system includes a gas compressor with dry gas seals about a driveshaft. The compressor system also includes a fugitive gas system having a gas conduit in fluid communication with a collection cavity in a collector coupled to the gas compressor to receive fugitive gas leaked through a pressurized gas leakage path. The fugitive gas system may be structured for flaring the gas, and includes a pressure control system with an accumulator tank, and a vent line for venting gas pressure and having a backpressure regulator therein. Fugitive combustible gas is conveyed through a flow restriction orifice downstream of the compressor.

Abstract: A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed.

Abstract: An example integrated support and sensor includes a longitudinal member to support an inner duct relative to an outer duct, and a sensor received within a bore of the longitudinal member and configured to collect a measurement from a flow path bounded by the inner duct.

Abstract: A radial blade impeller for an industrial fan assembly may include a cylindrical impeller hub having a hub outer surface and a hub shaft bore, a plurality of impeller blade assemblies circumferentially spaced about the hub outer surface and extending outward from the hub outer surface. A first sprocket disposed on a first end of the impeller hub engages a lateral edge of each of the impeller blade assemblies and has a plurality of first sprocket teeth extending outward from a first sprocket outer edge. Each of the first sprocket teeth corresponds to one of the impeller blade assemblies and engages and is secured to the first lateral edge of the corresponding one of the impeller blade assemblies. A second sprocket disposed on a second end of the impeller hub has a similar configuration with second sprocket teeth aligning with and engaging opposite lateral edges of the impeller blade assemblies.

Abstract: A wind control blade (31) of a wind guide (30) of the present invention forms a 20° wind control blade lateral curved surface gradient angle (32), a 30° wind control blade longitudinal spiral twist angle (33), a 180° wing control blade alignment angle (34), and a 15° wind control blade rear gradient angle (35). In addition, a turbine blade (41) forms a 30° turbine blade lateral curved surface gradient angle (42), a 40° turbine blade longitudinal spiral twist angle (43), and a 120° turbine blade alignment angle (44). The 20° wind control blade lateral curved surface gradient angle (32) and the 30° wind control blade longitudinal spiral twist angle (33) of the wind control blade (31) have more gradual and wider incidence angles than the 30° turbine blade lateral curved surface gradient angle (42) and the 40° turbine blade longitudinal spiral twist angle (43) of the turbine blade (41).

Abstract: A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. At least one of the tubular spokes accommodates a service line. The remaining spokes with no service line have an internal architecture which mimics an air cooling scheme of the at least one spoke housing a service line in order to provide temperature uniformity across all spokes.

Abstract: An assembly for a turbine engine, the assembly including a casing and an impeller rotatably movable inside the casing, the impeller including at least one blade having a tip edge opposite the casing, wherein the tip edge includes a magnet and wherein the casing includes an electrical conductor suitable for generating between the terminals thereof an electric voltage induced by the magnet of the tip edge opposite same and representing vibrations sustained by the tip edge of the blade when the impeller is rotated.

Abstract: A turbomachine includes a spool and a turbine section including a turbine rear frame, a turbine, and a support member. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The support member extends between the first plurality of turbine rotor blades and the spool and couples the first plurality of turbine rotor blades to the spool. The turbomachine also includes a bearing assembly including a bearing, the bearing rotatably supporting the support member and supported by the turbine rear frame, the bearing spaced apart from the spool along the radial direction.

Abstract: A rotary machine for an aeronautical device includes a thrust generator. The rotary machine additionally includes a rotary component rotatable with the thrust generator. Moreover, the rotary machine of the present disclosure includes a plurality of gas bearings, with the plurality of gas bearings substantially completely supporting the rotary component of the rotary machine.

Abstract: A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. The spokes are used as air feed pipe to provide cooling to different engine systems, such as an oil scupper line and a disc cavity of an adjacent turbine disc.

Abstract: A fan blade for a gas turbine engine includes an airfoil that has a first chord line that extends from a leading edge to a trailing edge. The first chord line is at 0% at the leading edge and at 100% at the trailing edge. The airfoil has a first local maximum thickness defined between about 85% of a span to a tip, a second local maximum thickness defined between about 40% to about 85% of the span and a third local maximum thickness defined between a root to about 40% of the span. The second local maximum thickness is positioned at about 10% to about 30% of the first chord line so as to be offset from the first local maximum thickness in the chordwise direction toward the leading edge. Each of the first, second and third local maximum thicknesses are different.

Abstract: A turbine may include a blade coupled to a rotor, a vane upstream from the blade and coupled to a vane support that defines a metering hole, and a blade outer air seal disposed radially outward from the blade and downstream from the vane support. An impingement surface may be disposed between the vane support and the blade outer air seal. The impingement surface may be oriented at an angle to the metering hole of between 50 degrees and 5 degrees.

Abstract: Gas turbine engine (GTE) airfoils, such as rotor and turbofan blades, having multimodal thickness distributions are provided. In one embodiment, the GTE airfoil includes an airfoil tip, an airfoil root opposite the airfoil tip in a spanwise direction, and first and second airfoil halves extending between the airfoil tip and the airfoil root. The first airfoil half has a first multimodal thickness distribution, as taken in a cross-section plane extending in the spanwise direction and in a thickness direction substantially perpendicular to the spanwise direction. The first multimodal thickness distribution may be defined by multiple locally-thickened airfoil regions, which are interspersed with multiple locally-thinned airfoil regions. The second airfoil half may or may not have a multimodal thickness distribution.

Abstract: The variable vane device maintenance method includes: a preparation step of preparing a ring including a first connection portion at which an attachment bracket is attached to the ring and a second connection portion at which the attachment bracket is attached at a position shifted from the first connection portion in a circumferential direction, the ring having the attachment bracket attached at the first connection portion; a release step of releasing a connection between a plurality of variable vanes and the ring and a connection between the ring and the attachment bracket at the first connection portion; a rotation step of rotating the ring by a predetermined angle; and a connection step of connecting the plurality of variable vanes to the ring at positions different from positions before the release step and connecting the ring to the attachment bracket at the second connection portion.

Abstract: The invention relates to a device (2) for cooling a turbine casing, preferably of a low-pressure turbine of a turbomachine, with air jets, the device comprising a pressurised air supply housing (3) and at least two curved cooling pipes (40) arranged on either side of the housing (3), around and spaced apart from a part of the casing and provided with air injection holes (41), the housing comprising, in particular, a bottom (31) and two longitudinal side walls (32, 33), and the bottom being pierced by air injection holes. The device is characterised in that each of the side walls extends outwards as at least one single-piece tubular sleeve, to which a cooling pipe is joined, the bottom of the sleeve being located at the same level as the bottom of the housing at the point where they are joined together.

Abstract: An inlet frame and a method of additively manufacturing the same are provided. The inlet frame includes a forward annular body spaced apart from a rear annular body to define an inlet passageway in fluid communication with a compressor inlet. The inlet frame may define integral wash manifolds and discharge ports for directing a flow of wash fluid directly through the compressor inlet. In addition, inlet frame may define one or more integral annular heating plenums in fluid communication with a hot air source for heating regions of the inlet frame that are prone to icing conditions.

Abstract: A guide vane for a turbomachine is disclosed. The guide vane includes a heat pipe wall that is interpenetrated by a capillary system, which has a continuous material transition from a first surface, which delimits the guide vane toward the outside, to a second surface, which lies opposite to the first surface and delimits an evaporation cavity in the interior of the guide vane. Further disclosed is a method for producing a guide vane having a heat pipe wall, wherein at least the heat pipe wall is formed by additive manufacture.

Abstract: A method for controlling a wind turbine during a safety operation is disclosed. A safety pitch control system is provided to pitch the blades individually at a number of pre-set approximately constant pitch rates including a first pitch rate and a second pitch rate lower than the first pitch rate. In response to a command for initiating the safety operation the blades are pitched towards a feathering position by the safety pitch control system including the blades being pitched according to a safety pitch strategy wherein for all the blades the pitch rate is changed between the first pitch rate and the second pitch rate according to a function of each blade azimuthal position. This is done such that each blade in turn is closer to the feathering position than the others.

Abstract: A vane system includes vane segments that each have a platform, a connector box, and at least one airfoil extending between the platform and the connector box. The connector box has a first circumferential side in the form of a male connector and a second circumferential side in the form of a female socket. The vane segments are connected together in a circumferential row with the male connector of each said vane segment being received in the female socket of the next vane segment in the circumferential row. A majority of the male connectors are of a first, common connector length, and at least one of the male connectors is of a second connector length that is different than the common connector length.

Abstract: A blade outer air seal (BOAS) is provided. The BOAS comprising: a seal body having a forward side, an aft side opposite the forward side, a radially inward side, and a radially outward side opposite the radially inward side; and a relief gap within the seal body to allow a portion of the radially inward side to expand into the relief gap when the seal body is heated.