Thermal insulation blankets and methods of using the same to repair articles, such as components of turbine engines are disclosed. The thermal insulation blankets are a multilayer composite material that includes: a first flexible fiberglass fabric layer having two sides that are coated with a coating that covers the fiberglass fibers; an intermediate second fiberglass insulation blanket layer made of continuous glass fibers; and a third layer of flexible heat reflective material. The method involves wrapping a component, such as a component of a turbine engine, with one or more thermal insulation blankets in order to retain heat within the confines of a prescribed area for installing or removing parts with a precision fitment. The blankets allow enough heat to induce even thermal expansion of the components.

An end surface-contact mechanical seal that is configured so as to seal by means of a relative rotational sliding contact action of sealing end surfaces (5a, 6a) which are opposing end surfaces of a fixed sealing ring (6), which is fixed to a rotating shaft (4), and a movable sealing ring (5), which is held by a seal case (3) so as to be movable in an axial direction, the mechanical seal being provided with a flushing means (8) for discharging a flushing liquid (F) from a flushing passage (81) formed in the seal case (3) toward the relative rotational sliding contact portions (5a, 6a) of the sealing rings (5, 6), wherein coating layers (9a, 10a) and (9b, 10b), which are composed of a material having a higher heat conduction coefficient and hardness than the constituent material of the sealing rings (5, 6), are formed continuously on portions of the surfaces of the sealing rings (5, 6) where the flushing liquid (F) makes contact with and on the sealing end surfaces (5a, 6a), and the relative rotational sliding contact portions (5a, 6a) of the sealing rings (5, 6) are configured to be uniformly and sufficiently cooled by the flushing liquid (F) for their entire periphery.

High temperature stable thermal barrier coatings useful for substrates that form component parts of engines such as a component from a gas turbine engine exposed to high temperatures are provided. The thermal barrier coatings include a multiphase composite and/or a multilayer coating comprised of two or more phases with at least one phase providing a low thermal conductivity and at least one phase providing mechanical and erosion durability. Such low thermal conductivity phase can include a rare earth zirconate and such mechanical durability phase can include a rare earth a rare earth aluminate. The different phases are thermochemically compatible even at high temperatures above about 1200° C.

An axial compressor comprises a plurality of compressor stages positioned axially adjacent one another within a casing. Each of the plurality of compressor stages comprise a rotor segment and a banded stator segment positioned axially adjacent the rotor segment. An annulus is formed between the casing and an outer flowpath ring of the stator segment. A vane of each stator segment comprises a member extending into the annulus.

A component for a gas turbine engine includes a first region formed substantially of a first CMC material, wherein first region defines a first thermal conductivity. The component further includes a second region formed substantially of a second CMC material, wherein the second region defines a second thermal conductivity. Further, the component defines a thickness and the first region is positioned adjacent to the second region along the thickness, wherein the first thermal conductivity is different than the second thermal conductivity to alert a thermal profile of the component.

An electronic speed regulator having a built-in fan. The electronic speed regulator comprises an aluminum part (10),a frameless fan (20), and screws (30); the frameless fan (20) is mounted on the aluminum part (10) by means of the screws (30); the aluminum part (10) comprises a base (11) and a heat dissipation fence (12); the heat dissipation fence (12) is located at the top of the base (11); and at least one hole position structure region (121) consisting of several hole positions is formed in the outer side wall of the heat dissipation fence (12).

A heat shield (100) and method for assembling such is disclosed. The heat shield (100) may comprise an outer wall (122) and an inner wall (124). The outer wall (122) includes a first member (130), a flange (132) extending outward from the first member (130) and a first inner edge (134). The first member (130) extends from the flange (132) to the first inner edge (134). The inner wall (124) includes a second member (140), a rim (142) extending outward from the second member (140) and a second inner edge (144). The second member (140) extends from the rim (142) to the second inner edge (144). The inner wall (124) is spaced apart from the outer wall (122), the first and second edges form an air gap (146) between them, and the inner wall (124) and the outer wall (122) form a cavity (148).

A turbocharger includes a turbine housing, an annular metal plate, and a scroll passage defining plate. The metal plate defines a connecting passage in the turbine housing. The connecting passage connects a turbine chamber and a turbine scroll passage to each other. The scroll passage defining plate includes a passage defining portion that defines the turbine scroll passage and an inner circumferential edge portion that extends from the inner circumferential edge portion of the passage defining portion and along the metal plate. The scroll passage defining plate has an inner circumferential edge that is fixed between the turbine housing and the metal plate. The scroll passage defining plate is arranged in the turbine housing such that the outer circumferential edge portion of the passage defining portion is movable relative to the turbine housing.

A turbocharger includes a turbine housing adapted to be arranged in the middle of an engine exhaust passage, a bearing housing coupled to the turbine housing, a turbine wheel located inside the turbine housing, a rotary shaft that is connected to the turbine wheel and is rotationally supported by the bearing housing, and a cooling water passage that is provided inside the turbine housing. The cooling water passage is located around the turbine wheel. The turbine housing includes a first connection portion joined to the bearing housing, a second connection portion joined to a part of the engine exhaust passage located on a downstream side of the turbine housing, and a heat insulating portion located between the cooling water passage and at least one of the first connection portion and the second connection portion.

An internal combustion engine has a cylinder head with at least one cylinder and a cooled turbine. Each cylinder has at least one outlet opening adjoined by an exhaust line for discharging exhaust gases from the cylinder. The exhaust line issues into an inlet region transitioning into an exhaust gas-conducting flow duct of the turbine. The turbine has at least one rotor mounted on a rotatable shaft in a turbine housing. The turbine has at least one coolant duct which is integrated in the housing and which is delimited and formed by at least one wall of the housing to form a cooling arrangement. The at least one wall of the turbine housing that delimits the at least one coolant duct is provided, at least in regions, with a thermal insulation.