A nosecone assembly having an axially extending centerline is provided. The assembly includes a nosecone body and at least one access panel. The nosecone body has at least one wall that defines an interior cavity. The wall has an interior surface contiguous with the interior cavity, and at least one window aperture extending through the wall. The access panel has first and second face surfaces. The access panel is attached to the wall interior surface within an attachment region that includes first and second attachment region portions partially contiguous with one another. The first and second attachment region portions define an interior unattached region, and the interior unattached region is aligned with the window aperture.

An airfoil includes an airfoil wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The airfoil wall circumscribes an internal core cavity. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has an inlet orifice through the inner portion of the airfoil wall to receive cooling air from the internal core cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion. The outer portion of the airfoil wall has a protrusion in the cooling passage network that faces toward the inlet orifice.

A microturbine comprising a turbine. a compressor, and an electric generator operating on a single shaft. The microturbine is designed segmenting the assembly into three subassemblies: a micro turbine engine subassembly, a turbine air sourcing housing subassembly, and a compressor air supply and electronics subassembly. The configuration enables efficient assembly, maintenance and repairs, as the operational components can be diagnosed at a high level and the subassembly can be exchanged quickly to optimize uptime. The micro turbine engine subassembly includes an integrated ceramic compressor and turbine assembly and a generator installed in a single unit that is slideably inserted within an interior of the turbine air sourcing housing subassembly. The compressor air supply and electronics subassembly is assembled to a respective end of the turbine air sourcing housing subassembly. The microturbine creates compressed air, heated air, and electrical power.

A gas turbine engine article includes an article wall that defines a cavity, a cooling passage network embedded between inner and outer portions of the article wall, and at least one conical passage through at least a portion of the inner portion of the article wall. The cooling passage network has an inlet orifice through the inner portion of the article wall to receive cooling air from the cavity, an outlet orifice through the outer portion of the article wall, and an intermediate region of passages that connects the inlet orifice to the outlet orifice. The conical passage has a first end that is proximate the cavity and a second end that opens at the intermediate region of passages.

A fiber-reinforced component for use in a gas turbine engine includes a fiber sleeve forming a cooling channel and a plurality of fiber plies enclosing the fiber sleeve, with the plurality of fiber plies forming first and second walls separated by the fiber sleeve. The fiber-reinforced component further includes a matrix material between fibers of the fiber sleeve and the plurality of fiber plies.

The present invention relates in general to the field of fluid reaction surfaces, and more specifically, to a fluid-foil impeller and method of use. One aspect of the fluid-foil impeller utilizes a plurality of fluid-foil discs that may be of uniform and/or variable thickness and configured to rotate rapidly in series to produce propulsion. Each fluid-foil disc comprises a leading edge, a trailing edge, a chord and a fixed pitch. The fluid-foil impeller may further include a standard or Venturi shroud that is designed to encompass the plurality of fluid-foil discs. The plurality of fluid-foil discs are configured to act in cooperation with the shroud to reduce losses incurred from turbulence and the conversion of mechanical work to fluid movement. Fluid may be acted upon by the plurality of fluid-foil discs and/or shroud, singly or in an array. A purpose of the invention is to provide a fluid-foil impeller and method of use that reduces harmful cavitation effects typically encountered by traditional propeller blades when operating at high revolutions per minute. An additional purpose of the invention is to provide a fluid-foil impeller that may be used efficiently and safely in a variety of industrial applications that requires successful propulsion a fluid.

A gas turbine exhaust casing includes a tubular casing wall, a bearing box housed in the casing wall, a diffuser portion forming an annular exhaust gas flow passage between the casing wall and the bearing box, a plurality of struts disposed at intervals in a circumferential direction of the casing wall, and coupling the casing wall and the bearing box, and a plurality of fastening bolts disposed on the casing wall. The casing wall includes an upper half casing forming an upper half of the casing wall and a lower half casing forming a lower half of the casing wall. The plurality of fastening bolts fasten the upper half casing and the lower half casing. The plurality of struts include a penetrated strut which has an end penetrated by at least one fastening bolt of the plurality of fastening bolts.

A nozzle assembly for a gas turbine engine and methods for assembling a nozzle assembly are provided. In one example aspect, the nozzle assembly includes an outer wall and an inner wall radially spaced from the outer wall. The outer wall defines a plurality of mounting openings spaced circumferentially from one another. The inner wall defines a plurality of mounting openings spaced circumferentially from one another. The mounting openings defined by the inner wall are positioned circumferentially between adjacent mounting openings defined by the outer wall. The nozzle assembly includes vanes that are inserted through the mounting openings of the outer wall in a radially inward direction and vanes that are inserted through the mounting openings of the inner wall in a radially outward direction in an alternating manner.

A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier assembly. The turbine outer case is arranged around an axis. The blade track segment is configured to define a portion of a gas path of the gas turbine engine. The carrier assembly is coupled to the turbine outer case and supports the blade track segment.

A blower has a blower housing of clamshell construction, including two housing members having a scroll back wall molded with radial draft, an impeller and a motor within the housing, and a static tap connected to the housing. The impeller has a backplate with a backplate back surface region of substantially the same radially converging shape as that of a front surface region of the scroll back wall formed by the radial draft, providing a substantially uniform axial gap between the backplate back surface region and the scroll back wall. The impeller has a ring connected by a skirt to the back plate to define a stepped area behind the ring. The impeller includes impeller blades extending forwardly from the impeller backplate and the ring and back fins extending rearwardly from the ring. The blower has a scroll width of about twice an impeller exhaust width.