There is provided a jet engine air inlet arrangement having a front annular casing arrangement and a heating pipe arrangement. The heating pipe arrangement is supported onto an annular internal bulkhead, wherein the annular internal bulkhead provides a back wall to the cavity. The annular internal bulkhead is fabricated from deformed metal sheet, and includes a plurality of radially disposed stiffening projections and recesses in the back wall, and wherein the annular internal bulkhead includes inner and outer circumferential flanges that engage onto inside surfaces of the front annular casing arrangement behind the back wall. The plurality of radially disposed stiffening projections and recesses result in the flanges being disposed at a distance of more than 60 mm behind the plurality of radially disposed stiffening projections and recesses.

A heat shield may include a base portion, wherein the base portion bounds a triangular void, a top portion, wherein the top portion bounds an ovular void, and a tapered portion, wherein the tapered portion extends between the base portion and the top portion, the top portion having a smaller cross-sectional area than the base portion.

A method of controlling a transition from a laminar flow to a turbulent flow for an airfoil of a turbomachine includes forming an airfoil. The airfoil defines a span extending between a root and a tip and a chord extending between a leading edge and a trailing edge. The airfoil includes a suction side surface and a pressure side surface, opposite the suction side surface, each extending between the leading edge, the trailing edge, the root, and the tip. The method also includes finishing a majority of the suction and pressure side surfaces in order to form a finished surface. The finished surface defines a first roughness. The method additionally includes leaving at least a portion of the suction side surface and/or pressure side surface unfinished in order to form an unfinished surface. Furthermore, the unfinished surface defines a second roughness greater than the first roughness.

A turbine blade includes: a platform; an airfoil portion extending from the platform in a blade height direction and having a pressure surface and a suction surface extending between a leading edge and a trailing edge; a blade root portion positioned opposite to the airfoil portion across the platform in the blade height direction and having a bearing surface; and a shank positioned between the platform and the blade root portion. The shank has a cross-section which is perpendicular to the blade height direction of the airfoil portion, and in which a line segment connecting a widthwise center position of a leading-edge-side end portion of the shank and a widthwise center position of a trailing-edge-side end portion of the shank is sloped to a center line between a pressure-surface-side contour of the blade root portion and a suction-surface-side contour of the blade root portion.

An apparatus for transporting a turbine engine with a transportation fixture including a turbine engine jig having mounts for securing the turbine engine, a rotor with a drive shaft rotationally supported by a bearing, the method includes supplying a lubricant to the bearing and rotating the drive shaft while the turbine engine is in transport.

Systems and methods of forming a ceramic matrix composite vane with profiled endwalls are provided using a multi-piece tooling. The multi-piece tooling includes core tools as well as profiled endwall tools having three dimensional contours formed in the tools that correspond to the three dimensional shape to be formed on the vane endwalls.

A magnetorheological support method for blisk processing is disclosed. In the method, a fork structure and a soft film are used to wrap magnetorheological fluid. The magnetorheological fluid is used for flow filling under certain pressure. The bulged soft film can conduct shape matching on the surface of a blisk blade. The magnetorheological fluid can be cured through magnetic field excitation, thereby ensuring the flexible support for a weak rigid component. Electric permanent magnets are symmetrically arranged at both ends of the fork structure to construct a uniform magnetic field that can realize a global excitation of magnetorheological fluid, so that the magnetorheological fluid works in a shear mode to achieve damping force controlling by magnetic field. The solid-liquid conversion of the magnetorheological fluid is controlled by an electric permanent magnet field.

Composite components and methods for forming composite components are provided. For example, a composite component of a gas turbine engine comprises a composite material, a plurality of piezoelectric fibers, and an anti-icing mechanism. The anti-icing mechanism is in operative communication with the piezoelectric fibers such that the anti-icing mechanism is activated by one or more electrical signals from the piezoelectric fibers. In exemplary embodiments, the composite component is a composite airfoil and the anti-icing mechanism is one or more heating elements. Methods for forming composite components may comprise forming piezoelectric plies comprising piezoelectric fibers embedded in a matrix material; forming reinforcing plies comprising reinforcing fibers embedded in the matrix material; laying up the piezoelectric and reinforcing plies to form a ply layup; and processing the ply layup to form the composite component. Methods including forming a piece of piezoelectric material that is adhered to a composite component also are provided.

A magnetorheological support method for blisk processing is disclosed. In the method, a fork structure and a soft film are used to wrap magnetorheological fluid. The magnetorheological fluid is used for flow filling under certain pressure. The bulged soft film can conduct shape matching on the surface of a blisk blade. The magnetorheological fluid can be cured through magnetic field excitation, thereby ensuring the flexible support for a weak rigid component. Electric permanent magnets are symmetrically arranged at both ends of the fork structure to construct a uniform magnetic field that can realize a global excitation of magnetorheological fluid, so that the magnetorheological fluid works in a shear mode to achieve damping force controlling by magnetic field. The solid-liquid conversion of the magnetorheological fluid is controlled by an electric permanent magnet field.

A gas turbine engine for an aircraft including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; and a fan located upstream of the engine core, the fan including a plurality of fan blades, wherein the gas turbine engine is configured such that a flow velocity ratio between a first flow velocity at an exit of the engine core and a second flow velocity at an inlet of the engine core is within a range from around 0.82 to around 1.1 at cruise conditions.