Abstract: A turbine vane in a gas turbine engine includes an inner platform, an outer platform, and a vane airfoil positioned therebetween. The vane airfoil includes a first cooling passage extending between the outer platform and the inner platform, and a second cooling passage extending between the outer platform and the inner platform. The second cooling passage is arranged downstream of the first cooling passage with respect to a flow direction. The turbine vane includes a jumper tube disposed between the second cooling passage and the inner platform. The jumper tube includes an inlet, an outlet, and a tube wall enclosing a hollow interior. The inlet is positioned a distance within the second cooling passage. The outlet is positioned at least partially through an aperture of the inner platform.

Abstract: An assembly is provided for rotational equipment. This assembly includes a first rotatable body and an injector. The first rotatable body extends axially along and circumferentially about a rotational axis. The first rotatable body includes a first scoop with a first scoop aperture that extends obliquely through the first rotatable body. The injector includes a first nozzle orifice and a second nozzle orifice. The injector is configured to direct a first fluid jet from the first nozzle orifice into an inlet of the first scoop aperture. The injector is further configured to direct a second fluid jet from the second nozzle orifice into the inlet of the first scoop aperture.

Abstract: A rotating seal rotatable about a rotational axis is provided. The rotating seal includes a body having a first surface disposable to face the rotational axis and a second surface disposable to contact with a stationary element. The body defines a cooling channel including one or more entrance channels respectively extending from the first surface, one or more exit channels and a plenum. The plenum extends circumferentially through the body and has a hot side adjacent to the second surface. The plenum is fluidly interposed between the one or more entrance channels and the one or more exit channels whereby fluid exiting the one or more entrance channels and entering the plenum impinges against the hot side.

Abstract: A turbine airfoil includes a trailing edge coolant cavity between a pressure sidewall and a suction sidewall. The trailing edge coolant cavity is positioned adjacent to and extending out to a trailing edge of the turbine airfoil. The interior includes an internal arrangement comprising an array of discrete fins formed aft of the trailing edge coolant cavity along the trailing edge.

Abstract: A flow inducer assembly and a method for cooling turbine blades of a gas turbine engine are presented. The gas turbine engine includes a rotor disk having circumferentially distributed disk grooves and turbine blades. Each turbine blade includes a blade root inserted into blade mounting section of the disk groove. Seal plates are attached to an aft side circumference of the rotor disk. The flow inducer assembly is integrated to each seal plate at a side facing away from the rotor disk. The flow inducer assembly is configured to function as a paddle due to rotation of the rotor disk and the seal plate therewith during operation of the gas turbine engine to drive ambient air as a cooling fluid into the disk cavity and enter inside of the turbine blade from the blade root for cooling the turbine blade.

Abstract: A blade (10) for a turbine engine that includes an internal cooling system (56) formed from at least one cavity (58) positioned within a generally elongated airfoil (12). A squealer tip (36) and at least one densified oxide dispersion strengthened layer (38) extend radially from a radially outer tip cap (70) of the blade (10), the tip cap (70) having a tip cap upper surface (50).

Abstract: An assembly is provided for rotational equipment. This assembly includes a first rotatable body and an injector. The first rotatable body extends axially along and circumferentially about a rotational axis. The first rotatable body includes a first scoop with a first scoop aperture that extends obliquely through the first rotatable body. The injector includes a first nozzle orifice and a second nozzle orifice. The injector is configured to direct a first fluid jet from the first nozzle orifice into an inlet of the first scoop aperture. The injector is further configured to direct a second fluid jet from the second nozzle orifice into the inlet of the first scoop aperture.

Abstract: A seal land includes a seal land body that extends circumferentially about an axis and radially between an inner seal land side and an outer seal land side. The seal land body is configured with a plurality of fluid passages arranged about the axis. A first of the fluid passages includes an inner passage segment and an outer passage segment fluidly coupled with the inner passage segment. The inner passage segment extends along a first trajectory within the seal land body towards the outer passage segment. The outer passage segment extends along a second trajectory within the seal land body away from the inner passage segment and towards the outer seal land side. The second trajectory is different than the first trajectory and includes a radial component and a circumferential component.

Abstract: A flow inducer assembly and a method for cooling turbine blades of a gas turbine engine are presented. The gas turbine engine includes a rotor disk having circumferentially distributed disk grooves and turbine blades. Each turbine blade includes a blade root inserted into blade mounting section of the disk groove. Seal plates are attached to aft side circumference of the rotor disk. The flow inducer assembly is integrated to each seal plate at a side facing away from the rotor disk. The flow inducer assembly is configured to function as a paddle due to rotation of the rotor disk and the seal plate therewith during operation of the gas turbine engine to drive ambient air as a cooling fluid into the disk cavity and enter inside of the turbine blade from blade root for cooling the turbine blade.

Abstract: A blade airfoil for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits with a leading edge circuit and a trailing edge circuit. The entrance of a cavity in the leading edge circuit has a narrowing of a cavity width that expands further downstream to a consistent cavity width similar to the cavity width of the rest of the leading edge circuit.

Abstract: A rotating seal rotatable about a rotational axis is provided. The rotating seal includes a body having a first surface disposable to face the rotational axis and a second surface disposable to contact with a stationary element. The body defines a cooling channel including one or more entrance channels respectively extending from the first surface, one or more exit channels and a plenum. The plenum extends circumferentially through the body and has a hot side adjacent to the second surface. The plenum is fluidly interposed between the one or more entrance channels and the one or more exit channels whereby fluid exiting the one or more entrance channels and entering the plenum impinges against the hot side.

Abstract: Disclosed is a mid-turbine frame of a gas turbine engine, including: a vane extending along an axis; a first fitting; a second fitting spaced apart from the first fitting along the axis; a tube assembly located within the vane wherein a cavity is defined between the vane and the tube assembly, the tube assembly including: an outer tube coupled to the first fitting and extending therefrom to the second fitting; an inner tube located within the outer tube and extending from the first fitting to the second fitting; and an outer passage defined between the outer tube and the inner tube, and an inner passage defined within the inner tube, wherein the cavity, the outer passage and the inner passage are fluidly isolated from one another, and the cavity is configured to direct a cooling flow therethrough, and the outer tube is configured to direct a buffer flow therethrough.

Abstract: Disclosed is a mid-turbine frame of a gas turbine engine, including: a vane extending along an axis; a first fitting; a second fitting spaced apart from the first fitting along the axis; a tube assembly located within the vane wherein a cavity is defined between the vane and the tube assembly, the tube assembly including: an outer tube coupled to the first fitting and extending therefrom to the second fitting; an inner tube located within the outer tube and extending from the first fitting to the second fitting; and an outer passage defined between the outer tube and the inner tube, and an inner passage defined within the inner tube, wherein the cavity, the outer passage and the inner passage are fluidly isolated from one another, and the cavity is configured to direct a cooling flow therethrough, and the outer tube is configured to direct a buffer flow therethrough.

Abstract: A turbine airfoil includes a trailing edge coolant cavity between a pressure sidewall and a suction sidewall. The trailing edge coolant cavity is positioned adjacent to and extending out to a trailing edge of the turbine airfoil. The interior includes an internal arrangement comprising an array of discrete fins formed aft of the trailing edge coolant cavity along the trailing edge.

Abstract: A seal land includes a seal land body that extends circumferentially about an axis and radially between an inner seal land side and an outer seal land side. The seal land body is configured with a plurality of fluid passages arranged about the axis. A first of the fluid passages includes an inner passage segment and an outer passage segment fluidly coupled with the inner passage segment. The inner passage segment extends along a first trajectory within the seal land body towards the outer passage segment. The outer passage segment extends along a second trajectory within the seal land body away from the inner passage segment and towards the outer seal land side. The second trajectory is different than the first trajectory and includes a radial component and a circumferential component.

Abstract: A blade airfoil for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits with a leading edge circuit and a trailing edge circuit. The entrance of a cavity in the leading edge circuit has a narrowing of a cavity width that expands further downstream to a consistent cavity width similar to the cavity width of the rest of the leading edge circuit.

Abstract: A blade (10) for a turbine engine that includes an internal cooling system (56) formed from at least one cavity (58) positioned within a generally elongated airfoil (12). A squealer tip (36) and at least one densified oxide dispersion strengthened layer (38) extend radially from a radially outer tip cap (70) of the blade (10), the tip cap (70) having a tip cap upper surface (50).