A heat insulating material assembly is provided with: a heat insulating material covering an outer surface of a casing of a gas turbine; and a guard part disposed so as to protrude from the outer surface of the casing and face an end surface of the heat insulating material. The heat insulating material is disposed outside an arrangement area of a plurality of openings for air intake from an external space into the casing and on an opposite side to the arrangement area across the guard part.

An annular fluid flow control or metering device comprises: first and second annular plates disposed in an annular flow path, the first annular plate and second annular plates being made of different first and second materials, the first annular plate having a lower first coefficient of thermal expansion than a second coefficient of thermal expansion of the second annular plate, the first annular plate abutting or in contact with the second annular plate, the first annular plate including at least one first metering aperture, and the second annular plate being more thermally responsive than the first annular plate wherein the second annular plate being configured to radially grow and shrink to at least partly obstruct the at least one first metering aperture for metering or controlling a flow of fluid through the at least one first metering aperture.

A gas turbine engine defining a centerline and a circumferential direction, the gas turbine engine including: a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining a working gas flowpath and a fan duct flowpath; a primary fan driven by the turbomachine defining a primary fan tip radius R.sub.1 and a primary fan hub radius R.sub.2; a secondary fan located downstream of the primary fan and driven by the turbomachine, at least a portion of an airflow from the primary fan configured to bypass the secondary fan, the secondary fan defining a secondary fan tip radius R.sub.3 and a secondary fan hub radius R.sub.4, wherein the secondary fan is configured to provide a fan duct airflow through the fan duct flowpath during operation to generate a fan duct thrust, wherein the fan duct thrust is equal to % Fn.sub.3S of a total engine thrust during operation of the gas turbine engine at a rated speed during standard day operating conditions; wherein a ratio of R.sub.1 to R.sub.3 equals $\sqrt{\left(\mathrm{EFP}\right)\frac{\left(1-Rq{R}_{\mathrm{Sec}.-{\mathrm{Fan}}^2}\right)}{\left(1-Rq{R}_{\mathrm{Prim}.-\mathrm{Fa}{n}^2}\right)}\left(\frac{1}{\%{\mathrm{Fn}}_{3S}}-1\right)}$

A tip shroud, comprising a plurality of tip shoes encircling a rotor assembly, in a turbine may deform due to thermal gradients experienced during operation of the turbine. Accordingly, a tip shoe is disclosed that utilizes an internal cooling cavity to supply coolant throughout the interior of the tip shoe, as well as to the slash faces of the tip shoe. In addition, features are described that increase the surface area exposed to the coolant, while remaining suitable for additive manufacturing.

An air inlet section for an enclosure for an aircraft engine is provided that includes an inner barrel panel, an outer barrel panel, a lipskin and a forward bulkhead. The lipskin extends between an inner barrel end and an outer barrel end. The inner barrel end is disposed proximate the forward end of the inner barrel panel and the outer barrel end is disposed proximate the forward end of the outer barrel panel. The forward bulkhead has a panel that extends between an outer radial end and an inner radial end. The inner barrel panel, the outer barrel panel, and the lipskin define an interior annular region, and the forward bulkhead defines a sub-portion of interior annular region. The outer radial end of the forward bulkhead panel is disposed forward of the inner radial end of the forward bulkhead panel.

A system includes a shaft body defining a longitudinal axis. A first internal fluid channel extends axially within the shaft body and includes an inlet opening through the shaft body for fluid communication of external fluid into the first internal fluid channel and an outlet opening through the shaft body for fluid communication of fluid from the first internal fluid channel to an area external of the shaft body. A second internal fluid channel extends axially within the shaft body and includes an inlet opening through the shaft body for fluid communication of external fluid into the second internal fluid channel and an outlet opening through the shaft body for fluid communication of fluid from the second internal fluid channel to an area external of the shaft body. The first and second internal fluid channels are in fluid isolation from one another within the shaft body.

A gas turbine engine includes a compressor section, a combustor section, and a turbine section operably coupled to the compressor section. A primary flow path is defined through the compressor section, the combustor section, and the turbine section. An engine case surrounds the compressor section, the combustor section, and the turbine section. The gas turbine engine also includes a means for providing an active variable cooling flow through a bypass duct external to the engine case to a secondary flow cavity of the turbine section.

A blade of a turbo machine, having a blade leaf, with a flow leading edge, a flow trailing edge, and flow conducting surfaces, and a cooling passage integrated in the blade leaf. In the region of the blade leaf cooling passage portions extend substantially in the radial direction. Adjacent cooling passage portions merge into one another via a diversion passage portion having a material web extending between the adjacent cooling passage portions. The respective material web ends in the region of the respective diversion passage portion. The respective material web has a defined axial width between the respective adjacent cooling passage portions and the respective material web in the region of the respective diversion passage portion has a material thickening enlarging the axial width by at least 20%.

A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.

Gas turbine engines and rotor arms thereof are described. The gas turbine engines include a first disk, a second disk, and a rotor arm arranged between and connecting the first disk to the second disk, wherein a cavity is defined at least between the rotor arm and the first disk. The rotor arm includes a radial portion having an inner diameter end and an outer diameter end, an axial portion having a first end and a second end, wherein the first end of the axial portion is connected to the outer diameter end of the radial portion, at least one entrance flow path defined within the radial portion extending from the inner diameter end to the outer diameter end, and at least one exit aperture arranged proximate the second end of the axial portion.