A turbo shield with a slit, wherein the slit is configured to allow an inner diameter across the turbo shield to increase and decrease without altering the properties of fibers associated with the turbo shield.

Disclosed is an outer air seal, having: an axial member, the axial member extending axially from an axial front end to an axial aft end, and extending radially from a radial inner surface to a radial outer surface; a radial flange extending radially from the radial outer surface of the axial member to a radial outer tip, and extending axially from an axial front surface to an axial aft surface; and a first kerf slot defined through the axial member from the axial front end to the axial aft end and from the radial inner surface to the radial outer surface, and through the radial flange from the axial front surface to the axial aft surface, wherein a radial top end of the first kerf slot is radially spaced apart from the radial outer tip of the radial flange.

The invention is related to the gas turbine stators of the gas turbine engines applied in aviation. The gas turbine stator, in the outer housing of which sectors of the split honeycomb ring (made as double-layer one) are installed with support elements on the front and rear axial ends of the sector. In this invention, the layer of the sector facing the outer housing is made U-shaped in the plane, the support elements are made as separate rotary bodies distributed uniformly along the circumference and the front support elements (on the gas flow direction) are larger than rear ones in terms of geometrical dimensions by factor 1.1 . . . 1.5. Therefore, the implementation of the invention proposed with the characteristic features above, in conjunction with the known features of the invention claimed enables reduction of the gas turbine stator weight and improvement its reliability without compromising the turbine efficiency.

A secondary air system for an aircraft engine comprises an air flow path communicating between a source of pressurized cooling air and an air consuming component. A filter is disposed in the air flow path upstream from the air consuming component. The filter has at least one of: openings of a size selected for capturing suspended particles; and a filter surface material for binding with chemical contaminants.

A heat shielded assembly includes a fuel structure of a combustor of a gas turbine engine and a woven heat shield at least partially conformally surrounding the fuel structure and spaced from an exterior of the fuel structure by a distance where it surrounds the fuel structure. The fuel structure is configured to deliver fuel to the combustor. The woven heat shield comprises a first set of strands, a second set of strands interwoven with the first set of strands, and a weave pattern comprising the first set of strands and the second set of strands. Each strand of the first set of strands extends in a first direction, each strand of the second set of strands extends in a second direction transverse to the first direction, and the first set of strands and the second set of strands are not attached where they intersect in the weave pattern.

A turbocharger includes a variable nozzle unit, a bearing housing, a circular heat shield plate located between a turbine impeller and the bearing housing, and a water chamber formed in the bearing housing. The heat shield plate is fixed by being pressed against the variable nozzle unit by a disc spring and is radially aligned by being fitted into the bearing housing by a fitting portion. The heat shield plate includes a fitting surface formed in the fitting portion and an inner peripheral heat shield portion projecting radially inward from the fitting surface and located with an axial gap between the inner peripheral heat shield portion and the bearing housing. At least a part of the water chamber exists at the same radial position as a radial position of the fitting portion.

A fastener cover for a flanged joint including first and second annular flanges extending about an axis, comprising: an annular, axially-extending, inboard wall; an annular, axially-extending outboard wall positioned radially outboard of the inboard wall; and a first radial wall interconnecting the inboard and outboard walls, wherein, collectively, the inboard and outboard walls and the first radial wall define a cavity for receiving a portion of a fastener; at least one fastener pocket including sidewalls extending axially away from the first radial wall and defining a tubular shape, which is closed off opposite the first radial wall by a floor plate having a clearance hole passing therethrough for accepting a shank of the fastener; and wherein the cover includes a balance weight receptacle for accepting at least one balance weight.

A turbo shield with a slit, wherein the slit is configured to allow an inner diameter across the turbo shield to increase and decrease without altering the properties of fibers associated with the turbo shield.

Provided is a turbocharger with further improved thermal efficiency. The turbocharger includes a heat shielding plate disposed between a center housing and a turbine housing. The center housing rotatably and pivotally supports a rotating shaft that connects a turbine impeller and a compressor impeller, and the turbine housing houses the turbine impeller. The turbocharger includes: a first flange portion; a second flange portion formed corresponding to the first flange portion; a clamp member combining the first flange portion and the second flange portion and fixing the mutual positional relationship; and a heat insulating ring interposed between an end surface, which is a heat shielding plate fixing portion that fixes the heat shielding plate, and the heat shielding plate on an inner peripheral side with respect to the first flange portion and the second flange portion.

A turbomachinery stator apparatus includes: a compressor casing including a casing wall defining an arcuate flowpath surface and an opposed backside surface, the flowpath surface defining at least two spaced-apart rotor lands; and a stator vane row of stator vanes disposed inside the compressor casing; wherein the casing wall includes at least one hollow structure; and wherein the casing wall is a single monolithic whole, wherein the stator vanes are integrally formed as part of the monolithic whole.