A modular casing manifold for cooling fluids of a gas turbine engine is presented. The modular casing manifold has an annular shape including an axial inner plate, an axial outer plate, a radial forward plate and a radial aft plate. The forward plate is attached to the inner and outer plates at forward end. At least a portion of the aft plate is attachable to and removable from the inner and outer plates at aft end for enabling cooling fluid to cool turbine blades of the gas turbine engine. The modular casing manifold includes preswirler segments. At least a number of the preswirler segments are attachable to and removable from the forward plate for enabling cooling fluid to cool turbine blades of the gas turbine engine. The modular casing manifold enables alternative cooling fluids to cool turbine blades of the gas turbine engine with minimal cost and assembly flexibility.

The gas turbine engine includes a casing assembly located proximate a turbine section of the gas turbine engine, and a tangential on-board injector (TOBI) having a body defining a plurality of air passages extending in a radial direction, the plurality of air passages circumferentially distributed and directing cooling air toward a turbine rotor of the turbine section of the gas turbine engine. An interference fit is provided between a face of the body and a face of a member of the casing assembly, the interference fit defining a fastener-free engagement between the bearing housing and the TOBI to prevent relative movement between the member of the casing and the TOBI.

A passive flow modulation device for a machine defining an axial direction and a radial direction, the passive flow modulation device including: a first ring with a first coefficient of thermal expansion; a second ring disposed coaxially with the first ring and positioned at least partially inward of the first ring along the radial direction, spaced from the first ring along the axial direction, or both, the first ring, the second ring, or both defining at least in part one or more passages, the second ring with a second coefficient of thermal expansion that is less than the first coefficient of thermal expansion to passively modulate a size of the one or more passages during operation.

An airfoil assembly includes first and second fiber-reinforced composite airfoil rings that each have inner and outer platform sections, a suction side wall extending between the inner and outer platforms, a pressure side wall extending between the inner and outer platforms, and suction and pressure side mate faces along, respectively, edges of the suction and pressure side walls. The suction side mate face of the first fiber-reinforced composite airfoil ring and the pressure side mate face of the second fiber-reinforced composite airfoil ring mate at an interface to form an airfoil that circumscribes an internal cavity. A least one of the suction or pressure side mate faces includes protrusions along a trailing edge of the airfoil. The protrusions define a toothed exit slot for emitting cooling air from the internal cavity.

A gas turbine engine includes a fan, a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the fan and compressor.

An airfoil of either of a turbine blade or a turbine vane includes a cooling passage; at least one disk body disposed on an inner wall of the cooling passage and configured to reduce a flow cross-sectional area of the cooling passage to increase a fluid pressure of cooling fluid flowing through the cooling passage; and at least one through-hole formed in each of the at least one disk body such that the cooling fluid flows through the at least one through-hole and forms a vortex on a downstream side of the at least one through-hole. The cooling passage includes an inlet supplied with the cooling fluid and an end opposite to the inlet, and the at least one disk body is disposed at the inlet of the cooling passage and is configured to increase the fluid pressure of the cooling fluid flowing into the cooling passage.

A rotary machine includes a seal device capable of restricting a flow of a fluid in a clearance between a stationary member and a rotational member. The seal device includes a pressure loss element mounted to the stationary member, a first non-contact type seal protruding from the rotational member toward the pressure loss element and facing the pressure loss element via a first gap, and a second non-contact type seal protruding from the stationary member toward the rotational member, facing the rotational member via a second gap, and being positioned on one side of the pressure loss element in a flow direction of the fluid. The seal device also includes a contact type seal protruding from the stationary member toward the rotational member and being disposed downstream of the pressure loss element and the second non-contact type seal in the flow direction of the fluid.

An airfoil assembly for a gas turbine engine is disclosed and includes a platform portion defining a portion of a gas flow path and a root portion for attachment of the turbine airfoil, the root portion including a bottom surface including a bottom area and a plurality of inlets that define a total inlet area as a ratio of the inlet area to the bottom area. An airfoil extends from the platform and including a plurality of cooling air passages in communication with the plurality of inlets.

The present disclosure is directed to a nozzle cooling system for a gas turbine engine. An impingement plate is positioned radially inwardly from a radially inner surface of an inner side wall of a nozzle. The impingement plate and the inner side wall collectively define an inner chamber. The impingement plate includes a first portion defining one or more impingement apertures and a second portion defining one or more post-impingement apertures. A duct plate encloses the first portion of the impingement plate. The duct plate, the first portion of the impingement plate, and inner side wall collectively define an outer chamber in fluid communication with the inner chamber through the one or more impingement apertures. Compressed air from the outer chamber flows through the one or more impingement apertures into the inner chamber and exits the inner chamber through the one or more post-impingement apertures.

A rotor disk is provided. The rotor disk may comprise a disk lug and a trench. The disk lug may be fixed to a distal surface of the rotor disk. The trench may be disposed on a surface of the disk lug. The trench may extend radially inwards from a distal surface of the disk lug. The trench may be configured to at least partially define a flow path by which cooling air may reach a distal surface of the disk lug in order to provide disk lug cooling.