A method for extracting at least one foreign body lodged within a blade of a high-pressure distributor of a turbojet engine, the high-pressure distributor including hollow fixed blades between two annular shrouds forming a gas flow path, each blade being coated with a thermal barrier and provided with at least one recess at least partially obstructed by a first soldered closing plate, includes the following operations: cutting off the first closing plate, extracting the foreign body from the recess, carrying out an endoscopic inspection of an internal space of the recess in order to verify that no foreign body remains, positioning a second closing plate on the recess, and soldering the second closing plate directly onto the distributor with the blades coated with the thermal barrier.

An article of manufacture includes an article body portion (36); at least one pedestal (58A, 60A, 84, 86) integrally formed with the article body portion (36), and disposed at an outer periphery of (52), and structurally coupled to the article body portion (36); and at least one internal feature (72) disposed at least partially within the article body portion (36) and at least partially within the pedestal (58A, 60A, 84, 86). At least a portion of the internal feature (72) is hollow.

A dehydrogenation processing method for a turbine blade of a steam turbine. The method includes a step of heating the turbine blade by suppling heating steam into a casing of the steam turbine after a steam turbine plant is stopped. The heating steam supplied to the casing has a temperature that is higher than steam passing through the turbine blade during operation of the steam turbine plant. The method further includes repeating the process of supplying the heating steam into the casing a multiple of times.

An airfoil bonding system may comprise a mold tool configured to support an airfoil assembly during a bonding process. The bonding process may include applying heat and pressure to the airfoil assembly. A surface of the mold tool may complement a preselected airfoil parameter. The mold tool may maintain the airfoil assembly in the preselected airfoil parameter during the application of heat and pressure to the airfoil assembly.

A gas turbine engine (10) and method of operation. The gas turbine engine (10) comprises a heating device configured to heat a rotor disc (32, 72) of the engine (10). A method of operation the heating device comprises detecting an engine acceleration or deceleration event, or determining that an engine acceleration or deceleration event is imminent or may be imminent. On detection of an engine acceleration or deceleration event, or in advance of the engine acceleration or deceleration event, increasing turbine rotor disc heat input to raise a temperature of the turbine rotor disc or reduce a cooling rate of the rotor disc.

A method of sealing a first component to a second component comprising the steps of locating at least one fiber reinforced polyimide resin layer against a first sealing surface on a first component and against a second sealing surface on a second component. At least one fiber reinforced polyimide resin layer is compressed against the first sealing surface and the second sealing surface prior to curing at least one fiber reinforced polyimide resin layer. At least one fiber reinforced polyimide resin layer is heated to promote flow and conformation to the first sealing surface and the second sealing surface. At least one fiber reinforced polyimide resin layer is cured to provide a fluid tight seal between the first component and the second component.

In a method for manufacturing a turbine engine element such as a blade or vane, the element has an airfoil. The method includes: applying a load across an assembly of a first cast portion of the airfoil and a second cast portion of the airfoil; and applying current across a junction of the first cast portion and the second cast portion to fuse the second cast portion to the first cast portion.

A method of treating a component adapted for use in a gas turbine engine is described herein. The component may comprise ceramic matrix composite materials. The treatment to the ceramic matrix composite component may reduce or eliminate the wear or damage of crack propagation in the ceramic matrix composite component.

The present disclosure relates to an impeller and a method of manufacturing the same. The impeller includes: a hub in which a plurality of spiral first slots are formed; a shroud which is positioned opposite the hub, and has a plurality of spiral second slots formed therein; and a plurality of blades which is coupled to the hub and the shroud, and have an upper protrusion formed on one side and a lower protrusion formed on the other side; and wherein the upper protrusion is inserted into and coupled to a second hole formed in the second slot, and the lower protrusion is inserted into and coupled to a first hole formed in the first slot.

According to an embodiment, a method of correcting a bend of a joint type-turbine rotor comprises: measuring displacement of a convex portion of the bend at a joined portion of the joint type-turbine rotor or displacement of a surface opposite to the convex portion in a circumferential direction of the joint type-turbine rotor; heating the convex portion; and cooling the joined portion after the step of heating. The steps of heating and cooling are performed during the step of measuring.