The present disclosure is directed to an impingement cooling system for a gas turbine engine having a gas turbine engine component and an insert positioned within the gas turbine engine component. The insert includes an insert body that defines an inner cavity therein, a first impingement aperture, a first heat exchanger inlet aperture, and a first heat exchanger outlet aperture. A first baffle extends outwardly from an outer surface of the insert body. The first baffle, the gas turbine engine component, and the insert body define a first and a second cooling chamber therebetween. The first impingement aperture fluidly couples the inner cavity of the insert body and the first cooling chamber. A first heat exchanger wall couples to an inner surface of the insert body. The first heat exchanger wall and the insert body define a first heat exchanger chamber therebetween.

The disclosure pertains to a cooled wall for separating a hot gas flow path of a gas turbine from a cooling flow including at least one turbulator rib extending from the wall into the cooling flow, and having a height, a width for providing heat transfer enhancement for the cooled wall. The turbulator rib has filets at its root with a filet radius. In order to increase the heat transfer enhancement of the turbulator rib, the filet at the downstream side of turbulator rib is extending into the cooled wall with a penetration depth. Further, the disclosure relates to specific embodiments in which the cooled wall with turbulator ribs is configured as the sidewall of an airfoil, a combustor wall or a heat shield.

A cooling structure for a turbomachine. In one embodiment, the cooling structure is for a seal slot of the turbomachine. The cooling structure includes a body coupled to a surface of the seal slot. The body includes a passageway on a first surface of the body for providing a cooling fluid to the seal slot. In an other embodiment, a apparatus includes a first component and a second component adjacent the first component. The apparatus also includes a seal slot extending between the first component and the second component, and a cooling structure positioned within the seal slot. The cooling structure includes a body coupled to a surface of the seal slot. The body has a passageway on a first surface of the body for providing a cooling fluid to the seal slot.

A gas turbine engine system having a combustion section and a turbine section is provided. The turbine section includes at least one turbine stage having a plurality of turbine blades coupled to a rotor and an inner casing circumferentially disposed about the plurality of turbine blades. The turbine section includes an outer casing circumferentially disposed about at least a portion of the inner casing. The inner casing and the outer casing define a cavity comprising a volume configured to facilitate the distribution of air within the cavity to cool an outer surface of the inner casing and an inner surface of the outer casing. The outer casing comprises at least one air inlet and the inner casing comprises at least one air outlet. At least one flange is provided within the cavity, and the at least one flange flanks the air inlet and at least one flow guide.

An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface with at least one cavity. A second engine component is spaced from the cooling surface, and includes at least one cooling aperture. The cooling aperture is arranged such that cooling fluid impinges on the cooling surface at an angle.

A heat sink for location in a fluid flow, including a heat sink base and a plurality of heat dissipating elements, such as elongate fins, extending from the surface of the heat sink base. In certain arrangements the heat sink is provided with a diversion flow passageway for diverting a fraction of fluid flow away from the heat dissipating elements. In other arrangements there may be two arrays of elongate fins laterally offset. In yet a further arrangement the heat sink may be configured to promote the generation of at least one vortex.

A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and forming a radially extending coolant receiving chamber. A rib partitions the radially extending chamber into a first passage on a first side of the rib and an adjacent second passage on an opposing second side of the rib. Each passage is enclosed at an end of the radially extending chamber by an end member of the radially extending chamber. A turn opening is defined in an end of the rib through which the coolant passes between the first passage and the second passage within the end member of the radially extending chamber. A bulbous projection extends along the end of the rib and on opposing radially extending sides of the turn opening to reduce stress in the rib and/or connecting fillets.

A turbine blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting to the pressure side outer wall and the suction side outer wall and partitioning a leading edge passage from the radially extending chamber. The rib configuration may also include a first center transverse rib connecting to the pressure side outer wall and the suction side outer wall and partitioning an intermediate passage from the radially extending chamber directly aft of the leading edge passage. The intermediate passage is defined by the pressure side outer wall, the suction side outer wall, the leading edge transverse rib and the first center transverse rib, and thus spans airfoil between its outer walls.

A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.

An internal rib for a blade airfoil has a concave surface defined to ensure durability and provide desired heat transfer. A concave surface faces a pressure side or suction side outer wall. A width is between a first end and a second end, and a depth is a length of a normal depth line between a midpoint of the concave surface and an intersection point of the depth line with the pressure or suction side outer wall. An irregular arc is defined within an arc angle centered at the intersection point, the irregular arc has a first arc radius equivalent to the depth at the midpoint of the concave surface and a second arc radius where the arc angle intersects the concave surface equivalent to a product of the depth and a shape factor. The shape factor has a substantially linear relationship with the aspect ratio.