Abstract: A gas turbine engine component has an annular flange arm, a backing plate mounted to the flange arm and a bypass circuit formed between the flange arm and the backing plate. The bypass circuit includes one or more channels formed in one of the flange arm or the backing plate. When more than one channels are used, at least one connecting slot is provided between the channels. At least one inlet passage extends through the flange arm in fluid communication with the forward-most channel, and at least one outlet slot is formed between the flange arm and the backing plate in fluid communication with the aft-most channel.

Abstract: A gas turbine engine component has an annular flange arm, a backing plate mounted to the flange arm and a bypass circuit formed between the flange arm and the backing plate. The bypass circuit includes one or more channels formed in one of the flange arm or the backing plate. When more than one channels are used, at least one connecting slot is provided between the channels. At least one inlet passage extends through the flange arm in fluid communication with the forward-most channel, and at least one outlet slot is formed between the flange arm and the backing plate in fluid communication with the aft-most channel.

Abstract: A turbine airfoil includes a plurality of internal ribs defining at least two independent serpentine cooling circuits having outer and inner serpentine portions, respectively, in different longitudinal tiers with the outer serpentine position being disposed longitudinally above the inner tier serpentine position for differentially longitudinally cooling the airfoil. The outer and inner serpentine portions include outer and inner exits and entrances wherein the outer and inner exits are positioned aft of the outer and inner entrances, respectively, so as to have a chordal flow direction aftwards from the leading edge to the trailing edge within the serpentine portions.

Abstract: A coated article comprises a substrate, an inner environmental resistant coating portion including Al on the substrate, and an outer heat energy reflecting and oxygen diffusion inhibiting coating portion outward of the inner portion. The outer coating portion is multi-layer, comprising 6-48 discrete stacked layers and a total outer coating portion thickness in the range of about 2.5-25 microns.

Abstract: A turbine shroud includes a panel having a forward end, an opposite aft end, and a middle therebetween. Cooling holes extend through the panel for channeling cooling air therethrough. The holes are arranged in a pattern of greater density aft of the panel middle than forward of the panel middle for effecting preferential cooling.

Abstract: A turbine airfoil includes first and second sidewalls joined together at leading and trailing edges, and spaced apart to define first and second cavities separated by a septum therebetween. An aft bridge extends along the first cavity and includes a row of outlet holes therein. The septum includes a row of inlet holes. And, turbulators are disposed in rows inside the first cavity, and extend from the first sidewall toward the second sidewall. The turbulators are aligned with the inlet holes for multiple impingement cooling thereof.

Abstract: The present invention provides a gas turbine engine blade having a dovetail, a shank extending radially outward from the dovetail, and a platform joined to the shank. An inner surface of the platform faces radially inwardly and an opposite outer surface of the platform faces radially outwardly. An airfoil extends radially outwardly from the platform and has pressure and suction airfoil sides that define pressure and suction blade sides of the blade. The platform extends axially between leading and trailing platform edges and transversely between pressure and suction side platform edges of the platform. At least one transversely extending bracing rib is in a corner of the shank and the platform between one of the blade sides and the inner surface of the platform. The preferred embodiment further includes the bracing rib, the shank, and the platform being integrally cast. The bracing rib is preferably wider along the platform and the shank than at a distal edge of the rib.

Abstract: A turbine shroud includes a panel having inner and outer surfaces extending between forward and aft opposite ends. The panel includes forward and aft hooks for supporting the panel radially atop a row of turbine rotor blades. The panel includes a plurality of recesses in the inner surface thereof which face tips of the blades. The recesses extend only in part into the panel for reducing surface area exposed to the blade tips.

Abstract: A modulated flow transfer apparatus for transferring a fluid flow from a static element to a rotor of a gas turbine engine has an annular static inducer for accelerating the fluid flow in a substantially circumferential direction. The inducer has an annular row of identical first and second flow passages with first and second inlets respectively and outlets. First and second flow means direct first and second portions of the flow to the first and second flow passages, respectively. A valve is used for selectively modulating the second portion of the flow which together with a controller may be used for selectively preventing the second portion of flow from flowing through the second flow passages during a first cruise of engine operation and allowing substantially unrestricted flow therethrough during a takeoff mode of engine operation. The second flow means preferably includes an inducer manifold disposed between the valve and the second inlets.

Abstract: A turbine airfoil includes a plurality of internal ribs joined to laterally opposite first and second sidewalls to define a serpentine cooling circuit therein. A span rib extends longitudinally between a root and tip of the airfoil. And, a slant rib extends obliquely to the span rib to define respective portions of the serpentine circuit longitudinally above and below the slant rib.

Abstract: A seal assembly positioned between forward and aft rotor stages of a turbine separates a forward cavity and an aft cavity on each side thereof. The seal assembly includes a seal body connected to a platform portion of a stator nozzle located between the forward and aft rotor stages, wherein an inner seal cavity in flow communication with an insert in the stator nozzle is formed therebetween. A static seal member is arranged in sealing relationship with a rotary toothed member between the forward and aft cavities, with the static seal member being connected to the seal body. An intermediate member is positioned between the seal body and the static seal member to define a plenum therebetween in flow communication with the inner seal cavity, the intermediate member having a plurality of angled passages formed therein in which a first end thereof is in flow communication with the plenum and a second end thereof is in flow communication with the aft cavity.

Abstract: A turbine airfoil includes a plurality of internal ribs defining at least two independent serpentine cooling circuits arranged in part in different longitudinal tiers, with an outer tier circuit being disposed in part longitudinally above an inner tier circuit for differentially longitudinally cooling the airfoil.

Abstract: A hollow gas turbine vane is shown enclosing, in spaced relation, a vane insert for receiving cooling air. The insert has a plurality of apertures for selectively directing jets of the cooling air against the internal walls of the vane. A portion of the air is discharged from within the vane chamber through a slit in the trailing edge which contains cooling pins extending transversely thereacross to maintain the slit dimensionally stable and also induce turbulence in the exhausting cooling air to improve its cooling effectiveness. Certain apertures in the insert adjacent the trailing edge are selectively directed to cause jets of the cooling air to impinge at the base of certain of the pins in the inlet area of the slit to promote turbulence in the air entering the slit and adjacent the internal face, thereby maximizing heat transfer from the slit walls to the air.